Requirements and traceability¶
The Apollo 11 requirements at four levels, from stakeholder needs down to component-level technical requirements, and the trace that links them: which requirement refines which, and which operation, function or piece of hardware satisfies each one. For systems engineers, requirement owners and reviewers who need to find a requirement, check its coverage, or follow a need down to the hardware.
294
requirements at 4 levels
369
refinement links
272
satisfy statements
95%
of mission, functional and technical requirements satisfied
95%
of requirements with a complete trace
50
requirements with quantified thresholds
Requirements tree¶
Product Requirements tree
The four requirement levels, how each level refines the one above, and what kind of architecture element satisfies each level.
Use it to understand how the requirement set is layered and where a given requirement sits in it.
The four requirement levels, how each level refines the one above, and what kind of architecture element satisfies each level.
Use it to understand how the requirement set is layered and where a given requirement sits in it.
| Level | Requirements | ID range | Refines | Specified for | Satisfied by | Satisfied |
|---|---|---|---|---|---|---|
| Stakeholder need | 22 | SHN-N001 … SHN-N022 | — | — | — (refined by capabilities) | — |
| Mission requirement | 43 | HLR-R001 … HLR-R069 | Capability (57) | Apollo11Mission | Operation | 43 of 43 |
| Functional requirement | 112 | FLR-R001 … FLR-R112 | Mission requirement (108), Capability (4) | PerformLunarMission | Function | 112 of 112 |
| Technical requirement | 117 | CLR-R001 … CLR-R117 | Functional requirement (106) | Apollo11MissionSystem | Hardware, Interface | 103 of 117 |
- Stakeholder needs are satisfied directly by no element: 42 refinement links from capabilities reach them, and 57 links from mission requirements refine the capabilities.
- Below the mission level, 1 of 217 requirements refines more than one parent (FLR-R092); 4 links skip the mission level (functional requirements refining a capability directly, listed in the gap report).
- Each level is satisfied in its own layer: mission requirements by operations, functional requirements by functions, technical requirements by hardware and interfaces.
Requirements register¶
Product Requirements register
Every requirement with its identifier, title, level, statement and rationale, the elements that satisfy it, and the requirements or capabilities it refines.
Use it to look up a requirement by ID or keyword (type in the filter box, e.g.
Every requirement with its identifier, title, level, statement and rationale, the elements that satisfy it, and the requirements or capabilities it refines.
Use it to look up a requirement by ID or keyword (type in the filter box, e.g.
abort, F-1, CLR-R046).| ID | Title | Level | Statement | Rationale | Satisfied by | Refines |
|---|---|---|---|---|---|---|
| SHN-N001 | Mission Success | Need | The mission shall succeed in all its technical and operational objectives. | The primary responsibility of the agency is to successfully execute the missions it is tasked with, thereby fulfilling its national mandate. | ||
| SHN-N002 | Astronaut Safety | Need | The mission shall ensure the safety and survival of the astronauts throughout all phases. | The agency has a fundamental duty of care for its personnel, and the success of the human spaceflight program depends on ensuring crew safety. | ||
| SHN-N003 | Programmatic Funding | Need | The mission's execution and public profile shall be managed to maintain continued public and political support and funding. | The Apollo program's existence is contingent on a massive financial commitment, which requires sustained political and public approval. | ||
| SHN-N004 | International Prestige | Need | The mission shall demonstrate technological superiority and achieve its primary objectives before any competing nation. | A core driver of the Apollo program was to win the Space Race, a key element of the Cold War geopolitical landscape. | ||
| SHN-N005 | Scientific Return | Need | The mission shall yield significant scientific data, primarily through the return of lunar samples. | Beyond the political goals, a key justification for the mission is the unique opportunity for scientific discovery. | ||
| SHN-N006 | Planetary Protection | Need | The mission shall prevent the contamination of Earth's biosphere by potential extraterrestrial life forms. | As a matter of public safety and scientific integrity, the agency must ensure that no harm comes from introducing unsterilized materials to Earth. | ||
| SHN-N007 | Crew Survival | Need | The mission systems and procedures shall ensure the crew can survive all mission phases. | The most fundamental need of any human participant in a high-risk endeavor is to survive the experience. | ||
| SHN-N008 | Procedural Success | Need | The mission shall provide the tools, training, and systems necessary for the successful execution of all assigned procedures. | The crew's professional responsibility and the mission's success depend on their ability to perform their tasks correctly. | ||
| SHN-N009 | Performance Under Pressure | Need | The mission environment and crew selection shall enable the management of extreme stress and pressure to ensure peak performance. | The psychological demands of a lunar mission are extreme; the crew's ability to cope is critical to success and safety. | ||
| SHN-N010 | Training Fidelity | Need | The mission training program shall adequately prepare the crew for all nominal and contingency scenarios. | High-fidelity training is the primary tool for mitigating risks and ensuring the crew can respond correctly to any situation. | ||
| SHN-N011 | Environmental Hazard Protection | Need | The mission systems shall protect the crew from the known and unknown hazards of the lunar environment. | Hazards such as abrasive dust and unstable ground pose a direct threat to the crew and equipment on the lunar surface. | ||
| SHN-N012 | Realtime Problem Solving | Need | The mission systems shall provide the necessary data and communication links to enable real-time problem solving from the ground. | Unforeseen anomalies are expected, and Mission Control's ability to analyze and solve them in real-time is a critical safety function. | ||
| SHN-N013 | Data Accuracy | Need | The mission shall provide accurate and reliable telemetry to support critical ground-based decision making. | The safety of the crew and success of the mission depend on ground controllers making decisions based on correct data. | ||
| SHN-N014 | Continuous Support | Need | The mission shall enable continuous communication to provide uninterrupted support to the flight crew. | The crew in space relies on the ground team for information, calculations, and support that they cannot manage alone. | ||
| SHN-N015 | Operational Coordination | Need | The mission shall be executed with a high degree of coordination between all flight and ground control teams. | A complex mission requires flawless teamwork and communication across multiple specialized teams to function correctly. | ||
| SHN-N016 | Lunar Module Performance | Need | The Lunar Module vehicle shall perform all its functions successfully, including landing, life support, and ascent. | As the manufacturer, the company's primary interest is the successful and reliable performance of its product. | ||
| SHN-N017 | Programmatic Adherence | Need | The development and delivery of the Lunar Module shall adhere to the programmatic schedule and budget. | Meeting contractual obligations regarding schedule and budget is a primary business need for any contractor. | ||
| SHN-N018 | Reputational Success | Need | The success of the Lunar Module shall enhance the company's reputation as a leading aerospace contractor. | A successful high-profile mission provides immense reputational value and secures opportunities for future contracts. | ||
| SHN-N019 | National Prestige | Need | The mission shall achieve its goal of a crewed lunar landing to demonstrate national technological supremacy. | The mission was a central element of the Cold War Space Race, and achieving the landing was a primary geopolitical objective. | ||
| SHN-N020 | Public Confidence | Need | The mission shall be conducted successfully and safely to bolster public confidence and morale. | A successful mission serves as a unifying national event and a demonstration of the government's capabilities. | ||
| SHN-N021 | Investment Justification | Need | The mission shall produce sufficient scientific and symbolic returns to justify the significant national financial investment. | The high cost of the program necessitates tangible results, such as scientific knowledge and national prestige, to be considered a worthwhile expenditure. | ||
| SHN-N022 | National Security Demonstration | Need | The mission shall demonstrate advanced technological capabilities relevant to national security. | The capabilities required for a lunar mission (e.g., large rockets, global tracking, precision guidance) are inherently linked to national security interests. | ||
| HLR-R001 | Crew Return Safety Requirement | Mission | The Apollo 11 Mission shall safely return all three crew members to Earth, with no life-threatening injuries or long-term health impacts, by July 24, 1969. | This requirement is paramount for fulfilling the core mission objective (Go to Moon) and directly addresses the primary concern of all stakeholders (NASA, Astronauts, Families, Public, U.S. Government) regarding human life safety. | retrieveCrewAndCM | Atmospheric Reentry And Landing; Contingency Planning And Rapid Response; Deep Space Habitation And Life Support |
| HLR-R002 | Lunar Lander Soft Landing Requirement | Mission | The Apollo 11 Mission shall achieve a soft landing of the crewed lunar lander on the lunar surface within the designated landing zone (Tranquility Base), by July 20, 1969. | A soft and precise lunar landing is fundamental to the 'Go to Moon' goal and ensures the integrity of the lander and safety of the crew for surface operations and subsequent ascent. | executePoweredDescentBurn | Autonomous And Assisted Navigation Guidance And Control; Lunar Surface Landing And Ascent; Precision Orbital Mechanics |
| HLR-R003 | Trans Lunar Injection Accuracy Requirement | Mission | The Apollo 11 Mission launch system shall successfully place the spacecraft into a Trans-Lunar Injection (TLI) trajectory with a delta-V accuracy of +/- 0.5 meters per second and a path leading to lunar orbit insertion within 75 hours from launch, on July 16, 1969. | Accurate Trans-Lunar Injection is essential for reaching the Moon efficiently and correctly, directly supporting the 'Go to Moon' goal and minimizing the need for costly and time-consuming mid-course corrections. | executeTLIBurn | Heavy Lift Launch; Multi Stage Propulsion; Precision Orbital Mechanics |
| HLR-R004 | Communication Uptime Requirement | Mission | The Apollo 11 Mission's communication system shall maintain continuous voice and telemetry contact with ground control for >= 95% of the mission duration, with no single blackout exceeding 10 minutes during lunar farside passes, throughout the 8-day mission. | Reliable communication is vital for real-time mission control, astronaut safety, and public engagement, addressing concerns of Mission Control, NASA, and the public. | communicateWithMissionControl | Global Tracking And Communication; Robust Communication And Telemetry |
| HLR-R005 | Sustained Cabin Habitability | Mission | The spacecraft system shall maintain an internal environment that supports crew health and cognitive performance for the mission duration. | Human life cannot be sustained in the vacuum of space without an artificial environment. Proper habitability is critical for the crew to perform complex tasks. | monitorSpacecraftSystems | Deep Space Habitation And Life Support |
| HLR-R006 | Lunar Sample Collection Quantity Requirement | Mission | The Apollo 11 Mission shall collect a minimum of 20 kilograms of documented lunar surface material, including contingency and bulk samples, and return them to Earth within the Mobile Quarantine Facility, by July 24, 1969. | This requirement directly fulfills the 'samples' goal, providing crucial scientific data for understanding the Moon's origin and geology, and supports the scientific community's objectives. | collectLunarSamples | Extravehicular Activity Support; Scientific Data Acquisition And Sample Return |
| HLR-R007 | Scientific Instrument Deployment Requirement | Mission | The Apollo 11 Mission shall deploy a visual transmission system and at least two scientific experiment packages on the lunar surface, and these packages shall transmit data to Earth for a minimum of 1 month post-landing. | This requirement is essential for achieving the 'deploy' goal, providing long-term scientific data from the lunar surface and enabling public engagement through visual broadcasts. | deployScientificInstruments | Extravehicular Activity Support; Scientific Data Acquisition And Sample Return |
| HLR-R008 | Lunar Visual Documentation Requirement | Mission | The Apollo 11 Mission shall capture and return to Earth at least 1,000 high-resolution still photographs and at least 30 minutes of motion picture footage documenting the lunar terrain, deployed equipment, and crew activities, by July 24, 1969. | This requirement directly supports the 'pictures' goal, providing vital visual data for scientific analysis, historical record, and public inspiration and engagement. | performLunarEVA | Scientific Data Acquisition And Sample Return |
| HLR-R009 | National Symbol Deployment Requirement | Mission | The Apollo 11 Mission shall successfully plant a national symbol on the lunar surface, ensuring it remains upright and visible for subsequent observation (if possible), during the initial Extravehicular Activity on July 20, 1969. | This requirement directly fulfills the 'flag' goal, serving as a powerful symbolic demonstration of national achievement and technological prowess, addressing the U.S. Government's and American Public's interests. | performLunarEVA | Extravehicular Activity Support; Lunar Mobility |
| HLR-R010 | Planetary Protection Quarantine Requirement | Mission | The Apollo 11 Mission shall implement and adhere to Level V biological quarantine procedures for the crew and extraterrestrial samples upon return, ensuring no detectable extraterrestrial biological contamination is released into Earth's biosphere, throughout the 21-day quarantine period. | This requirement is critical for protecting Earth's environment and public health from potential unknown hazards from the Moon, addressing concerns of the U.S. Government and the global public. | initiateQuarantineProcedures | Planetary Protection |
| HLR-R011 | Trajectory Navigation Precision | Mission | The mission shall maintain the capability to determine spacecraft position with sufficient accuracy to ensure a safe lunar arrival. | Precise navigation is required to intercept the Moon and enter the correct lunar orbit. Errors in trajectory determination can lead to mission loss. | conductMidCourseCorrections | Autonomous And Assisted Navigation Guidance And Control; Autonomous And Assisted Navigation Guidance And Control |
| HLR-R026 | Waste Management Effectiveness | Mission | The Apollo 11 Mission's waste management system shall effectively collect and store all solid and liquid waste for the entire mission, preventing contamination of the cabin environment. | Effective waste management is essential for maintaining a hygienic and safe crew cabin environment, preventing health hazards and equipment contamination. | monitorSpacecraftSystems | Deep Space Habitation And Life Support |
| HLR-R028 | Crew Sleep Environment Quality | Mission | The Apollo 11 Mission's crew's sleep environment shall allow for at least 6 hours of undisturbed sleep per 24-hour period, characterized by noise levels below 60 decibels. | Adequate and undisturbed sleep is crucial for maintaining crew physical and mental performance, especially during high-stress and long-duration missions. | manageCrewRestPeriods | Deep Space Habitation And Life Support |
| HLR-R030 | Crew Alarm Response Time | Mission | The Apollo 11 Mission's crew interface system shall provide visual and auditory alarms for all critical system failures, with an alarm response time of <= 1 second. | Rapid and clear alarming is essential for the crew to quickly identify and respond to critical system failures, mitigating risks and ensuring safety. | monitorSpacecraftSystems | Deep Space Habitation And Life Support |
| HLR-R032 | Lunar Lander To Orbiter Voice Comm | Mission | The Apollo 11 Mission's lunar lander's communication system shall enable voice communication between the crew on the surface and the crew in lunar orbit, with a signal clarity of 90% (subjective scoring). | Reliable voice communication between the lander and orbiter crews is crucial for coordinating critical operations like rendezvous and docking, ensuring safety and mission success. | performLunarEVA | Robust Communication And Telemetry |
| HLR-R033 | Extravehicular Mobility Unit Life Support Duration | Mission | The Apollo 11 Mission's Extravehicular Mobility Unit shall provide life support for a minimum of 4 hours of continuous Extravehicular Activity in the lunar environment. | Sufficient life support duration for the Extravehicular Mobility Unit is necessary to enable astronauts to perform required tasks on the lunar surface, supporting scientific and symbolic goals. | performLunarEVA | Extravehicular Activity Support |
| HLR-R035 | Extravehicular Mobility Unit Dexterity For Tasks | Mission | The Apollo 11 Mission's Extravehicular Mobility Unit shall allow for manual dexterity sufficient to operate small tools and manipulate samples with gloved hands, demonstrating a 90% success rate for task completion during Extravehicular Activity simulations. | Adequate dexterity in the Extravehicular Mobility Unit is essential for astronauts to effectively perform scientific and operational tasks on the lunar surface, directly impacting mission success. | performLunarEVA | Extravehicular Activity Support; Tool Development |
| HLR-R036 | Lunar Surface Mobility Range | Mission | The Apollo 11 Mission's lunar surface mobility system shall enable astronauts to traverse distances of up to 50 meters from the lander during Extravehicular Activity with less than 10% fatigue impact on subsequent tasks. | Ensuring efficient and manageable astronaut mobility on the lunar surface is important for maximizing the scientific return and operational effectiveness of Extravehicular Activities. | performLunarEVA | Lunar Mobility |
| HLR-R037 | Extravehicular Activity Tool Security | Mission | All Extravehicular Activity tools used in the Apollo 11 Mission shall be operable with a minimum of two points of contact (e.g., tethered or hand-held) to prevent loss in lunar gravity. | Securing tools during Extravehicular Activity is vital to prevent loss in the low lunar gravity environment, ensuring tools are available for all planned tasks and do not become debris. | performLunarEVA | Extravehicular Activity Support |
| HLR-R038 | Sample Pristine Preservation | Mission | Apollo 11 Mission's lunar samples shall be collected and stored in a manner that preserves their pristine lunar environment and prevents terrestrial contamination, ensuring less than 0.1% terrestrial material contamination by mass. | Maintaining the pristine state of lunar samples is crucial for their scientific value, as contamination would compromise the integrity of geological analysis and understanding of lunar composition. | collectLunarSamples | Planetary Protection; Scientific Data Acquisition And Sample Return |
| HLR-R040 | Sample Geological Context | Mission | The Apollo 11 Mission shall obtain geological context for all collected samples through photographic documentation with clear scale references, ensuring >= 90% of samples are correlated with their collection location. | Providing accurate geological context for samples is vital for interpreting their scientific significance and understanding the Moon's stratigraphy and formation. | collectLunarSamples | Scientific Data Acquisition And Sample Return |
| HLR-R045 | Critical Component Redundancy | Mission | The Apollo 11 Mission shall have redundancy (N+1 or greater) for all critical single-point-of-failure components in propulsion, Guidance, Navigation, and Control, and life support systems, ensuring continued operation after a single failure. | Redundancy for single points of failure is a fundamental safety and reliability measure, allowing the mission to continue even if a critical component fails. | executeLOIBurn | Contingency Planning And Rapid Response |
| HLR-R046 | Abort Sequence Execution Time | Mission | Apollo 11 Mission Control shall be capable of initiating and executing an abort sequence from any point during ascent or Trans-Lunar/Earth Coast within 5 minutes of an abort decision. | Rapid abort capability is a critical safety net, allowing the mission to be terminated and the crew safely returned in response to unforeseen catastrophic failures. | executeLaunchSequence | Contingency Planning And Rapid Response; Realtime Mission Control |
| HLR-R047 | Manual Override Response Time | Mission | The Apollo 11 Mission's crew shall be able to manually override automated flight control systems for all major maneuvers (e.g., Trans-Lunar Injection, Lunar Orbit Insertion, Powered Descent Initiation) with a response time of <= 1 second. | Manual override capability provides a crucial human element of control and contingency in case automated systems fail or encounter unexpected conditions, directly enhancing safety. | performManualPiloting | Human Performance Under Extreme Stress |
| HLR-R048 | Ground Segment Data Update Frequency | Mission | The Apollo 11 Mission's ground segment shall provide up-to-date trajectory and state vector information to the flight crew at least every 10 minutes during dynamic flight phases. | Frequent and up-to-date information from ground control is essential for the crew's situational awareness, navigation, and ability to execute maneuvers safely and accurately. | communicateWithMissionControl | Realtime Mission Control |
| HLR-R049 | Lunar Lander Ascent Readiness Time | Mission | The Apollo 11 Mission's lunar lander's ascent stage shall be capable of launching from the lunar surface within 24 hours of landing, to align with rendezvous opportunities in lunar orbit. | A limited readiness time for ascent ensures the crew can depart the lunar surface within favorable orbital mechanics windows for rendezvous, crucial for their return. | executeLunarAscentBurn | Lunar Surface Landing And Ascent |
| HLR-R050 | Flight Software Update Time | Mission | Apollo 11 Mission Control shall be able to reconfigure and uplink flight software updates to the spacecraft's primary computers within 1 hour in response to critical in-flight anomalies. | The ability to rapidly update flight software in-flight provides a vital corrective capability to address unforeseen bugs or adapt to changing mission conditions. | communicateWithMissionControl | Complex Software Development |
| HLR-R052 | Crew Emergency Medical Proficiency | Mission | The Apollo 11 Mission crew shall demonstrate proficiency in emergency medical procedures to handle common in-flight illnesses or minor injuries without external assistance for up to 72 hours. | Crew self-sufficiency in basic medical emergencies is essential given the vast distances and isolation of lunar missions, where immediate external medical aid is impossible. | transferCrewToVehicle | Crew Training And Simulation |
| HLR-R053 | In Flight Procedure Error Rate | Mission | The Apollo 11 Mission crew shall be capable of performing all critical in-flight procedures (e.g., docking, re-entry preparation) with an error rate of <= 0.5% under nominal conditions. | A very low error rate for critical procedures is paramount for mission success and crew safety, as failures in these steps could have catastrophic consequences. | conductLMCSMDocking | Human Performance Under Extreme Stress |
| HLR-R054 | Crew Nutrition And Hydration | Mission | Apollo 11 Mission astronauts shall be able to consume all provided food and water throughout the mission without experiencing significant gastrointestinal issues or nutrient deficiencies. | Adequate nutrition and hydration are fundamental for maintaining astronaut health, energy levels, and cognitive function throughout the demanding mission. | manageCrewRestPeriods | Deep Space Habitation And Life Support |
| HLR-R055 | Crew Psychological State | Mission | The Apollo 11 Mission crew shall maintain a positive psychological state as assessed by structured psychological evaluations throughout the mission. | Crew psychological well-being is vital for effective teamwork, decision-making, and overall mission performance, especially during long periods of isolation and stress. | manageCrewRestPeriods | Human Performance Under Extreme Stress |
| HLR-R057 | Micrometeoroid Penetration Risk | Mission | The Apollo 11 Mission spacecraft shall be designed to minimize micro-meteoroid penetration risk to critical habitable volumes to less than 1 event in 1,000 missions. | Minimizing micrometeoroid penetration risk is a key safety requirement to protect the crew and critical systems from space debris impacts that could cause depressurization or damage. | monitorSpacecraftSystems | Deep Space Habitation And Life Support |
| HLR-R059 | Lunar Element Environmental Resistance | Mission | All external mission elements left on the lunar surface by the Apollo 11 Mission shall be designed to withstand lunar thermal cycles (approx. +/- 150°C) and lunar dust exposure for a minimum of 3 months while maintaining structural integrity. | Ensuring the long-term survival of deployed lunar elements in the harsh lunar environment is crucial for extended scientific data collection and mission legacy. | deployScientificInstruments | Scientific Data Acquisition And Sample Return |
| HLR-R060 | Post Flight Data Archiving | Mission | The Apollo 11 Mission shall ensure post-flight data retention and archiving of all telemetry, voice, video, and scientific data, maintaining 99.99% data availability for future analysis for a minimum of 50 years. | Long-term data archiving ensures that valuable mission data is preserved for future scientific research, engineering analysis, and historical purposes, benefiting future generations. | recoveryQuarantineOperations | Complex Logistics And Integration |
| HLR-R061 | Propulsion System Mission Reliability | Mission | The mission's major maneuvers shall be executed using highly reliable propulsive systems to ensure mission success and return. | Failure during critical maneuvers like LOI or TEI would leave the crew stranded. Engine systems must be highly predictable. | executeLOIBurn | In Space Propulsion |
| HLR-R062 | Mechanical Load Resilience | Mission | All primary structures shall withstand the flight environment without compromising mission functionality. | The spacecraft must survive extreme mechanical stresses during launch and reentry to protect internal subsystems. | executeLaunchSequence | Heavy Lift Launch |
| HLR-R063 | Live Visual Broadcast | Mission | The mission shall provide a live visual record of lunar surface operations to satisfy public and scientific return goals. | Real-time coverage is vital for fulfilling national prestige and providing visual context for Mission Control. | communicateWithMissionControl | Robust Communication And Telemetry |
| HLR-R064 | Extended Scientific Operation | Mission | Deployed lunar elements shall remain operational post-landing to provide long-term data return. | Scientific value is maximized by instruments that continue to collect data long after the crew departs. | deployScientificInstruments | Scientific Data Acquisition And Sample Return |
| HLR-R065 | Critical System Availability | Mission | All mission-critical systems shall be designed for maximum uptime to prevent catastrophic mission loss. | High availability is the cornerstone of safety, ensuring that single-point failures do not result in the loss of crew or spacecraft. | monitorSpacecraftSystems | Complex Logistics And Integration |
| HLR-R066 | Public Support And Affairs Management | Mission | The Apollo 11 program shall maintain a public affairs office to provide real-time updates and educational materials to the global public, ensuring a favorable public opinion rating of at least 60% throughout the mission duration. | Sustained political and public support is necessary to maintain the massive financial commitment required for the program's existence. | communicateWithMissionControl | Programmatic And Public Affairs Management |
| HLR-R067 | Electrical Power Availability | Mission | The spacecraft electrical power system shall provide a continuous supply of regulated DC power to all primary bus systems, maintaining a minimum of 25% energy reserve at all times during the nominal mission profile. | Reliable power distribution is fundamental to the operation of all other spacecraft systems and is a prerequisite for mission success. | monitorSpacecraftSystems | Power Generation And Distribution |
| HLR-R068 | Launch Window Precision | Mission | Launch operations shall execute the final countdown and ignition sequence within a ±2.5-second launch window to ensure the spacecraft meets the required planetary alignment for the Trans-Lunar Injection. | Precise management of ground-based launch activities is required to ensure the launch system places the spacecraft into the correct trajectory efficiently. | performPreLaunchCountdown | Launch Operations Management |
| HLR-R069 | Operational Workaround Protocol | Mission | The mission architecture shall provide the crew and ground controllers with 'workaround' protocols for all non-critical system anomalies, enabling mission continuation despite minor hardware or software deviations. | The inherent human capacity to adjust to unexpected challenges is a critical safety function that allows for mission success when automated systems encounter unforeseen conditions. | performManualPiloting | Adaptability And Problem Solving |
| FLR-R001 | Propellant Loading Requirement | Functional | The system shall enable the loading of all required propellants and consumables into the vehicle's storage systems. | All propulsive stages and life support systems must be fully supplied to perform their functions for the mission's duration. | load | HLR-R001 Crew Return Safety Requirement |
| FLR-R002 | Consumable Conditioning Requirement | Functional | The system shall maintain all loaded propellants and consumables at their required temperature and pressure prior to launch. | Cryogenic propellants and other consumables must be kept in a stable state to ensure vehicle integrity and readiness for engine start. | load | HLR-R005 Sustained Cabin Habitability |
| FLR-R003 | Crew Ingress Requirement | Functional | The system shall provide a safe method for the flight crew to enter and be secured within the crew cabin. | The crew must be safely positioned and secured within the vehicle to withstand the forces of launch. | board | HLR-R001 Crew Return Safety Requirement |
| FLR-R004 | Cabin Pressurization Requirement | Functional | The system shall verify the pressure integrity of the crew cabin after crew ingress. | A sealed cabin is fundamental for providing a habitable, life-sustaining environment for the crew. | board | HLR-R005 Sustained Cabin Habitability |
| FLR-R005 | Countdown Sequencing Requirement | Functional | The system shall execute a synchronized sequence of pre-launch checks and configurations. | A precisely timed sequence is necessary to ensure thousands of vehicle and ground systems are correctly configured for launch. | countdown | HLR-R068 Launch Window Precision |
| FLR-R006 | Countdown Abort Requirement | Functional | The system shall be capable of holding or aborting the countdown if any critical system parameter violates pre-defined limits. | This capability is a critical safety function to prevent launching a vehicle that is not in a nominal state. | countdown | HLR-R046 Abort Sequence Execution Time |
| FLR-R007 | Stage1 Thrust Initiation Requirement | Functional | The system shall initiate first stage main propulsion upon receiving a valid, authenticated launch command. | Reliable and timely initiation of ascent thrust is critical for leaving the launch pad and beginning the flight profile as planned. | provideThrust1 | HLR-R062 Mechanical Load Resilience |
| FLR-R008 | Stage1 Thrust Magnitude Requirement | Functional | The system shall generate a propulsive force from the first stage that results in a positive vertical acceleration at liftoff. | A thrust-to-weight ratio greater than one is the fundamental condition required to overcome gravity and lift the vehicle off the launch pad. | provideThrust1 | HLR-R062 Mechanical Load Resilience |
| FLR-R009 | Stage2 Thrust Initiation Requirement | Functional | The system shall initiate second stage propulsion following the clean separation of the first stage. | Continuous acceleration is required to achieve the velocity needed to reach the upper atmosphere. | provideThrust2 | HLR-R062 Mechanical Load Resilience |
| FLR-R010 | Stage2 Propulsion Requirement | Functional | The system shall provide continuous thrust from the second stage to propel the vehicle through the upper atmosphere. | The second stage is optimized to provide efficient thrust in near-vacuum conditions. | provideThrust2 | HLR-R062 Mechanical Load Resilience |
| FLR-R011 | Orbit Insertion Thrust Initiation Requirement | Functional | The system shall initiate third stage propulsion to provide the final thrust needed to achieve a stable Earth orbit. | A final, precise propulsive burn is required to circularize the orbit and prevent the vehicle from falling back to Earth. | provideThrust3 | HLR-R003 Trans Lunar Injection Accuracy Requirement |
| FLR-R012 | Orbit Insertion Thrust Termination Requirement | Functional | The system shall terminate third stage thrust upon receiving a cutoff command. | Precise thrust termination is critical for achieving the correct orbital parameters. | provideThrust3 | HLR-R003 Trans Lunar Injection Accuracy Requirement |
| FLR-R013 | Ascent Guidance Requirement | Functional | The system shall autonomously control the vehicle's trajectory during ascent according to a pre-programmed flight plan. | Automated guidance is necessary to manage the complex, high-speed ascent profile with precision. | guide | HLR-R003 Trans Lunar Injection Accuracy Requirement |
| FLR-R014 | Ascent Staging Command Requirement | Functional | The system shall issue commands to separate expended stages at pre-determined points in the ascent profile. | Jettisoning mass is essential for maximizing the efficiency of the upper stages. | guide | HLR-R003 Trans Lunar Injection Accuracy Requirement |
| FLR-R015 | Crew Ascent Monitoring Requirement | Functional | The system shall display critical vehicle parameters to the flight crew during ascent. | The crew must have situational awareness to monitor vehicle health and make manual control or abort decisions. | observe | HLR-R001 Crew Return Safety Requirement |
| FLR-R016 | Crew Ascent Abort Requirement | Functional | The system shall provide an interface for the crew to manually initiate a launch abort sequence. | Manual abort is a key safety feature that provides the crew with ultimate control in a contingency. | observe | HLR-R046 Abort Sequence Execution Time |
| FLR-R017 | Ground Telemetry Analysis Requirement | Functional | The system shall receive, process, and display real-time telemetry from the launch vehicle to ground personnel. | Ground teams must have accurate, real-time data to monitor vehicle health and provide support. | analyze | HLR-R048 Ground Segment Data Update Frequency |
| FLR-R018 | Ground Performance Verification Requirement | Functional | The system shall compare vehicle performance against pre-defined limits and provide go/no-go recommendations. | This function provides an independent verification of vehicle performance, enhancing mission safety. | analyze | HLR-R048 Ground Segment Data Update Frequency |
| FLR-R019 | Tli Thrust Initiation Requirement | Functional | The system shall provide a propulsive force to cause the vehicle to escape Earth's orbit. | A major propulsive maneuver is required to increase velocity from orbital to escape speed. | burn | HLR-R003 Trans Lunar Injection Accuracy Requirement |
| FLR-R020 | Tli Thrust Control Requirement | Functional | The system shall guide the translunar injection burn to achieve the required trajectory accuracy. | The accuracy of this burn is critical to ensure the spacecraft arrives at the correct position and time near the Moon. | control | HLR-R003 Trans Lunar Injection Accuracy Requirement |
| FLR-R021 | Module Separation Requirement | Functional | The system shall enable the primary spacecraft to separate from its launch vehicle adapter. | Separation is required before the spacecraft can be reconfigured for the journey to the Moon. | executeTransposition | HLR-R001 Crew Return Safety Requirement |
| FLR-R022 | Module Repositioning Requirement | Functional | The system shall enable the controlled repositioning of the primary spacecraft after separation. | The spacecraft must be turned around to face the stowed lunar module for docking. | executeTransposition | HLR-R001 Crew Return Safety Requirement |
| FLR-R023 | Module Connection Requirement | Functional | The system shall enable the physical connection and sealing of two separate spacecraft modules in space. | A rigid, pressurized connection is required to allow for crew transfer and to form the complete translunar vehicle. | reconfigure | HLR-R001 Crew Return Safety Requirement |
| FLR-R024 | In Space Propulsion Requirement | Functional | The system shall provide a propulsive force for major in-space trajectory changes. | A restartable, high-thrust engine is required for critical maneuvers like lunar orbit insertion and transearth injection. | burn | HLR-R061 Propulsion System Mission Reliability |
| FLR-R025 | Attitude Control Requirement | Functional | The system shall provide low-thrust propulsive forces to control the orientation of the spacecraft. | Precise attitude control is required for thermal regulation, communications antenna pointing, and alignment for main engine burns. | provideAttitudeControlAndThrust | HLR-R061 Propulsion System Mission Reliability |
| FLR-R026 | Navigational Data Acquisition Requirement | Functional | The system shall enable the acquisition of celestial navigation data. | Regular position fixes are necessary to maintain an accurate understanding of the vehicle's trajectory. | trackAndRelay | HLR-R011 Trajectory Navigation Precision |
| FLR-R027 | Trajectory Calculation Requirement | Functional | The system shall calculate the vehicle's current trajectory based on navigational data. | The current trajectory must be known in order to calculate necessary course corrections. | calculate | HLR-R011 Trajectory Navigation Precision |
| FLR-R028 | Course Correction Calculation Requirement | Functional | The system shall calculate the required propulsive maneuver to correct any deviations from the planned trajectory. | This function is essential for ensuring an accurate arrival at the Moon and minimizing fuel usage. | calculate | HLR-R011 Trajectory Navigation Precision |
| FLR-R029 | Course Correction Execution Requirement | Functional | The system shall execute a calculated course correction maneuver. | The ability to act on calculated corrections is required to maintain the proper flight path. | correct | HLR-R011 Trajectory Navigation Precision |
| FLR-R030 | Crew System Monitoring Requirement | Functional | The system shall display the status of all critical subsystems to the crew. | Continuous situational awareness of system health is required for the crew to manage the mission and respond to anomalies. | monitorOnboard | HLR-R030 Crew Alarm Response Time |
| FLR-R031 | Ground System Monitoring Requirement | Functional | The system shall transmit the status of all critical subsystems to the ground. | Ground controllers provide a vital support and analysis function that depends on receiving continuous, accurate telemetry. | monitorGround | HLR-R004 Communication Uptime Requirement |
| FLR-R032 | Spacecraft Data Transmission Requirement | Functional | The system shall transmit voice, telemetry, and video data to the ground network. | Data transmission is required to support ground control functions and meet public engagement objectives. | comms | HLR-R004 Communication Uptime Requirement |
| FLR-R033 | Spacecraft Data Reception Requirement | Functional | The system shall receive and process commands and voice data from the ground network. | The crew must be able to receive updated plans, information, and commands from Mission Control. | comms | HLR-R004 Communication Uptime Requirement |
| FLR-R034 | Ground Tracking Requirement | Functional | The system shall track the spacecraft's position and velocity from Earth. | Continuous tracking is the primary source of navigational data for Mission Control. | trackAndRelay | HLR-R048 Ground Segment Data Update Frequency |
| FLR-R035 | Ground Communication Relay Requirement | Functional | The system shall relay communications between the spacecraft and Mission Control. | A global network is required to maintain a continuous communications link as the Earth rotates. | trackAndRelay | HLR-R004 Communication Uptime Requirement |
| FLR-R036 | Crew Activity Scheduling Requirement | Functional | The system shall provide a structured timeline for all crew activities, including work, meals, and sleep. | A managed schedule is essential for ensuring crew members are rested and prepared for critical mission events. | rest | HLR-R028 Crew Sleep Environment Quality |
| FLR-R037 | Crew Rest Provision Requirement | Functional | The system shall provide an environment that allows for crew sleep. | Adequate rest is a fundamental requirement for maintaining crew cognitive performance and health. | rest | HLR-R028 Crew Sleep Environment Quality |
| FLR-R038 | Loi Thrust Requirement | Functional | The system shall provide a retrograde propulsive force sufficient to reduce the vehicle's velocity for lunar capture. | A major braking maneuver is the only way to transition from a fly-by trajectory to a stable lunar orbit. | burn | HLR-R061 Propulsion System Mission Reliability |
| FLR-R039 | Loi Guidance Requirement | Functional | The system shall guide the lunar orbit insertion burn to achieve the target orbital parameters. | The accuracy of the lunar orbit is critical for all subsequent operations, including rendezvous and landing. | control | HLR-R011 Trajectory Navigation Precision |
| FLR-R040 | Lander System Verification Requirement | Functional | The system shall enable the crew to activate and verify the health of all Lunar Module systems prior to separation. | The lander's systems must be confirmed to be fully operational before committing to the landing. | checkout | HLR-R002 Lunar Lander Soft Landing Requirement |
| FLR-R041 | Lander Interface Verification Requirement | Functional | The system shall confirm all interfaces between the lander and the main vehicle are ready for separation. | A clean separation requires that all physical and data connections are properly configured. | checkout | HLR-R002 Lunar Lander Soft Landing Requirement |
| FLR-R042 | Lander Crew Transfer Requirement | Functional | The system shall allow the crew to transfer from the primary vehicle to the landing vehicle. | The landing crew must be inside the lander before it can be configured for independent flight. | prep | HLR-R001 Crew Return Safety Requirement |
| FLR-R043 | Lander Configuration Requirement | Functional | The system shall allow the crew to configure the landing vehicle for independent flight. | The lander must be switched from a stowed, dormant state to a fully operational one. | prep | HLR-R049 Lunar Lander Ascent Readiness Time |
| FLR-R044 | Module Disengagement Requirement | Functional | The system shall disengage all docking latches connecting two vehicles. | This is the primary physical action required to allow two docked vehicles to separate. | undock | HLR-R002 Lunar Lander Soft Landing Requirement |
| FLR-R045 | Module Separation Maneuver Requirement | Functional | The system shall provide a controlled, low-velocity maneuver to create distance between two separated vehicles. | A controlled maneuver is required to ensure the two vehicles separate cleanly without re-contact. | undock | HLR-R002 Lunar Lander Soft Landing Requirement |
| FLR-R046 | Descent Propulsion Requirement | Functional | The system shall provide a continuous, throttleable propulsive force to control the rate of descent to the lunar surface. | A variable thrust is essential for precisely managing the landing profile, from braking out of orbit to a soft touchdown. | burn | HLR-R002 Lunar Lander Soft Landing Requirement |
| FLR-R047 | Descent Data Display Requirement | Functional | The system shall provide real-time altitude and velocity data to the crew and ground controllers. | Accurate, real-time data is critical for both automated guidance and manual piloting during the hazardous landing phase. | monitor | HLR-R002 Lunar Lander Soft Landing Requirement |
| FLR-R048 | Descent Data Processing Requirement | Functional | The system shall process sensor data to provide accurate navigation information during landing. | Raw sensor data must be processed into actionable information for the guidance system and crew. | monitor | HLR-R002 Lunar Lander Soft Landing Requirement |
| FLR-R049 | Manual Attitude Control Requirement | Functional | The system shall allow the crew to take manual control of the lander's attitude. | Manual control is a critical function for making fine adjustments to the landing site. | pilot | HLR-R047 Manual Override Response Time |
| FLR-R050 | Manual Position Control Requirement | Functional | The system shall enable horizontal repositioning to avoid hazards. | The ability to fly over unexpected hazards like craters or boulder fields is essential for landing safety. | pilot | HLR-R047 Manual Override Response Time |
| FLR-R051 | Post Landing Safing Requirement | Functional | The system shall allow the crew to place all lander systems into a safe, quiescent state after touchdown. | Securing the vehicle's systems, especially propulsion, is the first priority after a successful landing. | postLand | HLR-R001 Crew Return Safety Requirement |
| FLR-R052 | Post Landing Verification Requirement | Functional | The system shall allow the crew to verify that the vehicle is in a stable state and ready for surface operations. | The health of the vehicle must be confirmed before committing to an extravehicular activity. | postLand | HLR-R049 Lunar Lander Ascent Readiness Time |
| FLR-R053 | Egress Preparation Requirement | Functional | The system shall allow the crew to don and check out their spacesuits. | Spacesuit integrity must be confirmed before the crew is exposed to vacuum. | prepEva | HLR-R033 Extravehicular Mobility Unit Life Support Duration |
| FLR-R054 | Cabin Depressurization Requirement | Functional | The system shall be capable of depressurizing the lander cabin to the external vacuum environment. | Depressurization is a prerequisite for opening the hatch to the lunar surface. | prepEva | HLR-R033 Extravehicular Mobility Unit Life Support Duration |
| FLR-R055 | Surface Mobility Requirement | Functional | The system shall enable astronauts to traverse the lunar surface. | Mobility is fundamental to exploring the area around the lander and performing scientific tasks. | eva | HLR-R036 Lunar Surface Mobility Range |
| FLR-R056 | Symbolic Deployment Requirement | Functional | The system shall enable the crew to deploy a national symbol on the lunar surface. | Fulfilling this key political and public objective of the mission was a primary requirement. | eva | HLR-R009 National Symbol Deployment Requirement |
| FLR-R057 | Sample Collection Requirement | Functional | The system shall enable the collection of lunar material. | The primary scientific objective of the mission was to return physical samples from the Moon. | collect | HLR-R006 Lunar Sample Collection Quantity Requirement |
| FLR-R058 | Sample Storage Requirement | Functional | The system shall provide storage for collected samples that prevents terrestrial contamination. | The scientific value of the samples depends on them remaining in a pristine, uncontaminated state. | collect | HLR-R038 Sample Pristine Preservation |
| FLR-R059 | Instrument Deployment Requirement | Functional | The system shall enable the crew to deploy scientific experiment packages on the lunar surface. | Leaving behind long-term experiments was a key scientific goal to gather data after the crew departed. | deploy | HLR-R007 Scientific Instrument Deployment Requirement |
| FLR-R060 | Visual Transmission Requirement | Functional | The system shall enable the deployment of a visual transmission system. | Transmitting live images from the Moon was a critical public engagement and historical documentation requirement. | deploy | HLR-R063 Live Visual Broadcast |
| FLR-R061 | Eva Ingress Requirement | Functional | The system shall allow the crew to re-enter the lander cabin with all collected samples and equipment. | A safe return to the pressurized cabin is required to conclude the surface exploration. | conclude | HLR-R001 Crew Return Safety Requirement |
| FLR-R062 | Cabin Repressurization Requirement | Functional | The system shall allow the crew to re-pressurize the lander cabin. | A breathable atmosphere must be restored before the crew can doff their spacesuits. | conclude | HLR-R005 Sustained Cabin Habitability |
| FLR-R063 | Surface Habitation Requirement | Functional | The system shall provide a habitable environment for the crew to sleep and eat on the lunar surface. | Crew rest is essential for performance and safety, especially before the critical ascent phase. | rest | HLR-R028 Crew Sleep Environment Quality |
| FLR-R064 | Surface Timeline Management Requirement | Functional | The system shall manage the timeline to ensure readiness for ascent within the required orbital mechanics window. | The ascent must be timed precisely to allow for a successful rendezvous with the orbiting primary vehicle. | rest | HLR-R049 Lunar Lander Ascent Readiness Time |
| FLR-R065 | Ascent Thrust Initiation Requirement | Functional | The system shall initiate the ascent engine using the descent stage as a launch platform. | A successful ignition is the single most critical event for getting the crew off the Moon. | ascend | HLR-R049 Lunar Lander Ascent Readiness Time |
| FLR-R066 | Ascent Propulsion Requirement | Functional | The system shall provide a continuous, non-throttleable propulsive force to achieve lunar orbit. | A fixed, highly reliable thrust profile was designed to place the ascent stage into a predictable orbit. | ascend | HLR-R049 Lunar Lander Ascent Readiness Time |
| FLR-R067 | Rendezvous Calculation Requirement | Functional | The system shall process tracking data to compute the required maneuvers for rendezvous. | Precise calculations are required to ensure the complex orbital mechanics of the rendezvous are successful. | calculate | HLR-R011 Trajectory Navigation Precision |
| FLR-R068 | Rendezvous Execution Requirement | Functional | The system shall execute a series of precise burns to match the orbit of and approach the target vehicle. | The execution of the rendezvous plan is what brings the two vehicles into close proximity for docking. | rendezvous | HLR-R011 Trajectory Navigation Precision |
| FLR-R069 | Docking Approach Requirement | Functional | The system shall allow the crew to pilot the final approach to the target vehicle. | Manual control during the terminal phase of docking provides the fine control necessary for a safe connection. | dock | HLR-R011 Trajectory Navigation Precision |
| FLR-R070 | Docking Latching Requirement | Functional | The system shall achieve a successful capture and rigid latching of the two vehicles. | A secure, rigid connection is essential for the safe transfer of crew and materials. | dock | HLR-R053 In Flight Procedure Error Rate |
| FLR-R071 | Intervehicular Crew Transfer Requirement | Functional | The system shall allow the crew to move between two docked vehicles. | This is the primary function enabled by docking and is required to get the landing crew back into the return vehicle. | transfer | HLR-R001 Crew Return Safety Requirement |
| FLR-R072 | Intervehicular Sample Transfer Requirement | Functional | The system shall allow the crew to transfer all collected lunar samples to the return vehicle. | The scientific goals of the mission are not met until the samples are safely stowed for the journey home. | transfer | HLR-R006 Lunar Sample Collection Quantity Requirement |
| FLR-R073 | Ascent Stage Separation Requirement | Functional | The system shall allow the crew to seal the hatches and disengage the docking latches. | The ascent stage must be separated from the primary vehicle before the journey back to Earth. | jettison | HLR-R001 Crew Return Safety Requirement |
| FLR-R074 | Ascent Stage Disposal Requirement | Functional | The system shall provide a controlled separation from the ascent stage. | The no-longer-needed ascent stage must be disposed of in a safe manner that does not interfere with the primary vehicle. | jettison | HLR-R001 Crew Return Safety Requirement |
| FLR-R075 | Tei Propulsion Requirement | Functional | The system shall provide a propulsive force to cause the vehicle to escape lunar orbit and enter a trans-Earth trajectory. | This major propulsive maneuver is the critical event required to start the journey home. | burn | HLR-R061 Propulsion System Mission Reliability |
| FLR-R076 | Reentry Configuration Requirement | Functional | The system shall allow the crew to perform final system checks and configure the vehicle for atmospheric entry. | The vehicle must be in a specific configuration to survive the stresses of reentry. | prep | HLR-R001 Crew Return Safety Requirement |
| FLR-R077 | Service Module Jettison Requirement | Functional | The system shall execute a pyrotechnic separation of the primary crew vehicle from its main support module. | The main support module is not designed for reentry and must be discarded. | separate | HLR-R001 Crew Return Safety Requirement |
| FLR-R078 | Clean Separation Requirement | Functional | The system shall ensure the two separated modules do not re-contact. | Re-contact after separation could damage the primary crew vehicle and jeopardize the safety of reentry. | separate | HLR-R001 Crew Return Safety Requirement |
| FLR-R079 | Reentry Guidance Requirement | Functional | The system shall use the vehicle's shape and orientation to control its trajectory through the atmosphere. | Guidance is required to manage extreme heating and to steer the vehicle toward the target landing zone. | guide | HLR-R001 Crew Return Safety Requirement |
| FLR-R080 | Heat Dissipation Requirement | Functional | The system shall protect the crew and vehicle structure from the extreme heat of atmospheric entry. | Without a method to dissipate thermal energy, the vehicle would be destroyed during reentry. | guide | HLR-R001 Crew Return Safety Requirement |
| FLR-R081 | Decelerator Deployment Requirement | Functional | The system shall deploy a sequence of aerodynamic decelerators at pre-defined altitudes. | Parachutes are required to slow the vehicle from supersonic speeds to a safe landing velocity. | deploy | HLR-R001 Crew Return Safety Requirement |
| FLR-R082 | Final Velocity Requirement | Functional | The system shall slow the vehicle to a safe landing velocity. | The final velocity must be low enough to ensure the integrity of the vehicle and the safety of the crew upon impact. | deploy | HLR-R002 Lunar Lander Soft Landing Requirement |
| FLR-R083 | Water Landing Requirement | Functional | The system shall execute the final water landing. | The mission was designed for a water landing in a pre-determined location. | splashdown | HLR-R001 Crew Return Safety Requirement |
| FLR-R084 | Post Landing Systems Requirement | Functional | The system shall automatically deploy flotation devices and beacons after landing. | These systems are required to keep the vehicle upright and to aid recovery forces in locating it. | splashdown | HLR-R001 Crew Return Safety Requirement |
| FLR-R085 | Crew Recovery Requirement | Functional | The system shall allow recovery forces to locate, secure, and retrieve the crew and crew vehicle from the ocean. | The final phase of ensuring crew safety is their successful recovery from the landing site. | retrieve | HLR-R001 Crew Return Safety Requirement |
| FLR-R086 | Vessel Transfer Requirement | Functional | The system shall transport the crew and crew vehicle to the primary recovery ship. | The crew and vehicle must be brought into a controlled environment for post-mission procedures. | retrieve | HLR-R010 Planetary Protection Quarantine Requirement |
| FLR-R087 | Quarantine Implementation Requirement | Functional | The system shall implement Level V biological quarantine procedures for the crew upon recovery. | This was a critical planetary protection requirement to prevent potential contamination of Earth's biosphere. | quarantine | HLR-R010 Planetary Protection Quarantine Requirement |
| FLR-R088 | Quarantine Habitation Requirement | Functional | The system shall place the crew into a specialized quarantine facility for a 21-day period. | The duration and facility were specified to ensure any potential extraterrestrial organisms could be detected. | quarantine | HLR-R010 Planetary Protection Quarantine Requirement |
| FLR-R089 | Sample Preservation Requirement | Functional | The system shall place the returned lunar samples into secure, contamination-free containers. | The scientific value of the samples depends on them being handled and stored correctly. | secure | HLR-R038 Sample Pristine Preservation |
| FLR-R090 | Sample Transport Requirement | Functional | The system shall transport the samples to a designated receiving laboratory for analysis. | The ultimate goal of sample collection is their analysis by the scientific community. | secure | HLR-R006 Lunar Sample Collection Quantity Requirement |
| FLR-R091 | TGNC Navigation Accuracy | Functional | The Apollo 11 Mission's navigation system shall determine spacecraft position with an accuracy of +/- 5 kilometers during Trans-Lunar Coast, at least once every 6 hours. | Accurate and frequent navigation updates are essential for maintaining the correct trajectory to the Moon, ensuring efficiency and safety during the long Trans-Lunar Coast phase. | trackAndRelay | |
| FLR-R092 | Manual Piloting Logic | Functional | The Apollo 11 Mission's control system shall enable manual piloting of the lunar lander to allow for horizontal repositioning of +/- 200 meters within the landing ellipse to avoid hazards. | Manual piloting capability is essential for avoiding unexpected surface hazards (e.g., boulders, craters) at the chosen landing site, directly enhancing mission safety and probability of successful landing. | pilot | Adaptability And Problem Solving; Human Performance Under Extreme Stress |
| FLR-R093 | System Interface Compatibility | Functional | All major system interfaces of the Apollo 11 Mission (e.g., spacecraft stacking, docking mechanisms) shall demonstrate 100% compatibility through full-scale integrated fit checks and electrical interface tests prior to final assembly. | Perfect interface compatibility is critical to prevent physical or electrical malfunctions between joined spacecraft components, ensuring safe and functional assembly and operation. | load | Complex Logistics And Integration |
| FLR-R094 | Training Simulator Hours | Functional | All flight crew members for the Apollo 11 Mission shall complete a minimum of 200 hours of specialized lunar lander simulator training prior to launch. | Extensive simulator training is crucial to ensure astronauts are highly proficient and prepared for complex and critical operations like lunar landing, enhancing safety and success. | board | Crew Training And Simulation |
| FLR-R095 | Course Correction Capability | Functional | The guidance system shall calculate and execute trajectory adjustments to maintain the designated mission corridor. | The mission needs the ability to correct course deviations; the technical accuracy is delegated to technical requirements. | correct | HLR-R011 Trajectory Navigation Precision |
| FLR-R096 | Spacecraft Orientation Control | Functional | The system shall autonomously maintain the commanded orientation for thermal regulation and communications. | Logical function of attitude control. Specific stability metrics belong in the technical level. | provideAttitudeControlAndThrust | HLR-R061 Propulsion System Mission Reliability |
| FLR-R097 | Descent Data Acquisition | Functional | The landing system shall acquire real-time altitude and velocity telemetry during the powered descent phase. | Functional bridge for sensor logic. Specific radar precision metrics are moved to the technical level. | monitor | HLR-R002 Lunar Lander Soft Landing Requirement |
| FLR-R098 | Launch Vehicle Ascent Thrust | Functional | The launch system shall provide sufficient total impulse to overcome Earth's gravity and achieve orbit insertion. | Functional logic for ascent. The specific force magnitude value belongs in the technical layer. | provideThrust1 | HLR-R062 Mechanical Load Resilience |
| FLR-R099 | Descent Rate Modulation | Functional | The lander shall provide the capability to vary engine thrust to control the rate of descent to the lunar surface. | Functional behavior for landing. Throttling percentages are defined in the technical level. | burn | HLR-R002 Lunar Lander Soft Landing Requirement |
| FLR-R100 | Thermal Protection Logic | Functional | The entry vehicle shall dissipate aerodynamic heat to protect internal volumes during atmospheric return. | Functional logic of the heat shield. Internal temperature rise limits belong at the technical level. | guide | HLR-R062 Mechanical Load Resilience |
| FLR-R101 | Touchdown Energy Dissipation | Functional | The landing gear system shall mechanically attenuate landing forces to prevent structural damage to the spacecraft. | Functional description of energy absorption. Velocity metrics are moved to the technical level. | burn | HLR-R002 Lunar Lander Soft Landing Requirement |
| FLR-R102 | Atmospheric Scrubbing Function | Functional | The life support system shall remove metabolic byproducts and particles from the cabin air. | Functional behavior for the ECS. Specific filter efficiencies and levels belong in technical requirements. | monitorOnboard | HLR-R005 Sustained Cabin Habitability |
| FLR-R103 | Telemetry Stream Integrity | Functional | The communication system shall ensure the fidelity of transmitted data between the spacecraft and ground segment. | Functional description of data link quality. Integrity metrics belong in technical specifications. | comms | HLR-R063 Live Visual Broadcast |
| FLR-R104 | EMU Pressure Maintenance | Functional | The Extravehicular Mobility Unit shall provide a constant pressurized volume for the astronaut in a vacuum environment. | Functional requirement for suit logic. The specific pressure setpoint belongs in the technical level. | eva | HLR-R064 Extended Scientific Operation |
| FLR-R105 | Software Mission Proficiency | Functional | The flight software shall be verified to perform all guidance and control functions without mission-critical errors. | Functional goal for software quality. The verification defect rate belongs in the technical level. | guide | HLR-R065 Critical System Availability |
| FLR-R106 | Space Environment Resilience | Functional | Spacecraft materials shall maintain their structural and functional properties under vacuum and thermal cycling. | Functional resilience goal. Exposure constraints belong in the technical layer. | monitorOnboard | HLR-R062 Mechanical Load Resilience |
| FLR-R107 | Visual Data Capture | Functional | The system shall capture high-resolution still and motion imagery of lunar operations. | Required to meet scientific and public documentation goals. | deploy | HLR-R008 Lunar Visual Documentation Requirement |
| FLR-R108 | Waste Containment Function | Functional | The life support system shall provide localized collection and sealed storage for all metabolic waste. | Essential for maintaining cabin hygiene and crew health. | monitorOnboard | HLR-R026 Waste Management Effectiveness |
| FLR-R109 | Cross Vehicle Audio Link | Functional | The communication system shall establish a dedicated VHF audio link between the LM and CSM during lunar operations. | Required for coordination during critical mission phases. | eva | HLR-R032 Lunar Lander To Orbiter Voice Comm |
| FLR-R110 | Component Fault Tolerance | Functional | Critical systems shall maintain nominal output levels despite the loss of any single primary component. | Implements the redundancy philosophy required for safety. | burn | HLR-R045 Critical Component Redundancy |
| FLR-R111 | Human Medical Self Sufficiency | Functional | The system shall provide medical kits and diagnostic guides enabling the crew to treat minor injuries. | Necessary due to the extreme delay in Earth-based assistance. | rest | HLR-R052 Crew Emergency Medical Proficiency |
| FLR-R112 | Data Redundancy Archiving | Functional | The ground segment shall mirror all incoming telemetry to multiple geographic locations for permanent archival. | Ensures mission data remains available for future generations. | retrieve | HLR-R060 Post Flight Data Archiving |
| CLR-R001 | SIC Engine Configuration | Technical | The S-IC stage shall incorporate five F-1 engines. | This configuration is required to generate the necessary thrust to lift the massive Saturn V vehicle off the launch pad. | stage1 | FLR-R008 Stage1 Thrust Magnitude Requirement |
| CLR-R002 | SIC Propellant Compatibility | Technical | The S-IC stage shall be designed to store and deliver RP-1 (Kerosene) and Liquid Oxygen (LOX) to its engines. | The choice of the F-1 engine dictates the required propellant types for the first stage. | stage1 | FLR-R001 Propellant Loading Requirement |
| CLR-R003 | SIC Gimbal Capability | Technical | The S-IC stage shall provide a gimbaling mechanism for its engines to enable thrust vector control. | Gimbaling is the primary means of steering the vehicle during the first stage of ascent, as aerodynamic surfaces are ineffective at low speeds. | stage1 | FLR-R013 Ascent Guidance Requirement |
| CLR-R004 | SII Engine Configuration | Technical | The S-II stage shall incorporate five J-2 engines. | This configuration provides the required thrust for second-stage flight in the upper atmosphere and vacuum where efficiency is paramount. | stage2 | FLR-R010 Stage2 Propulsion Requirement |
| CLR-R005 | SII Propellant Type | Technical | The S-II stage shall use Liquid Hydrogen (LH2) and Liquid Oxygen (LOX) propellants. | The high specific impulse of hydrolox propellant is critical for the efficiency of the upper stages to minimize vehicle mass. | stage2 | FLR-R001 Propellant Loading Requirement |
| CLR-R006 | SIVB Engine Configuration | Technical | The S-IVB stage shall incorporate a single J-2 engine. | A single, highly reliable engine provides the required thrust for both Earth orbit insertion and the subsequent Translunar Injection maneuver. | stage3 | FLR-R011 Orbit Insertion Thrust Initiation Requirement |
| CLR-R007 | SIVB Restart Capability | Technical | The S-IVB's J-2 engine shall be capable of restarting in a zero-gravity environment. | Engine restart is a critical capability, as the stage must fire once for orbit insertion and again for the TLI burn hours later. | stage3 | FLR-R019 Tli Thrust Initiation Requirement |
| CLR-R008 | IU Guidance Computer | Technical | The SaturnVInstrumentUnit shall house the primary guidance and navigation computer for the launch vehicle. | A dedicated computer is required to process trajectory data and execute the complex ascent flight plan autonomously. | instrumentUnit | FLR-R013 Ascent Guidance Requirement |
| CLR-R009 | IU Command Authority | Technical | The SaturnVInstrumentUnit shall issue all primary commands for engine ignition, cutoff, and stage separation during ascent. | A single, authoritative control unit is necessary to ensure precise and synchronized execution of mission-critical events. | instrumentUnit | FLR-R014 Ascent Staging Command Requirement |
| CLR-R010 | LES Propulsion Type | Technical | The ApolloLaunchEscapeSystem shall utilize a high-thrust solid rocket motor. | Solid rockets provide the rapid, high-impulse thrust needed to pull the crew capsule away from a failing launch vehicle with minimal delay. | launchEscapeSystem | FLR-R016 Crew Ascent Abort Requirement |
| CLR-R011 | LES Jettison Capability | Technical | The ApolloLaunchEscapeSystem shall be capable of being safely jettisoned from the spacecraft after the period of maximum atmospheric stress. | The LES is dead weight after the initial ascent phase and must be discarded to ensure mission efficiency. | launchEscapeSystem | FLR-R016 Crew Ascent Abort Requirement |
| CLR-R012 | CM Habitable Volume | Technical | The ApolloCommandModule shall provide a pressurized, habitable volume for a crew of three. | The Command Module serves as the primary living and working quarters for the crew for the majority of the mission. | commandModule | FLR-R004 Cabin Pressurization Requirement |
| CLR-R013 | CM Heat Shield | Technical | The ApolloCommandModule shall incorporate a heat shield capable of protecting the crew and structure from the heat of atmospheric reentry. | Protection from the extreme temperatures of reentry is a fundamental requirement for crew survival. | commandModule | FLR-R080 Heat Dissipation Requirement |
| CLR-R014 | CM Parachute System | Technical | The ApolloCommandModule shall house a system of parachutes to decelerate the vehicle for a safe water landing. | Aerodynamic decelerators are required to reduce the capsule's velocity to survivable limits for splashdown. | commandModule | FLR-R081 Decelerator Deployment Requirement |
| CLR-R015 | SM Main Propulsion | Technical | The ApolloServiceModule shall provide a restartable main engine for major in-space maneuvers. | A high-thrust, reliable main engine is required for critical mission events like Lunar Orbit Insertion and Trans-Earth Injection. | serviceModule | FLR-R024 In Space Propulsion Requirement |
| CLR-R016 | SM Attitude Control | Technical | The ApolloServiceModule shall provide a reaction control system for attitude control and minor velocity changes. | The RCS is essential for orienting the spacecraft for thermal control, communications, and main engine burns. | serviceModule | FLR-R025 Attitude Control Requirement |
| CLR-R017 | SM Power Generation | Technical | The ApolloServiceModule shall house fuel cells to generate the primary electrical power for the Command/Service Module. | A continuous and reliable source of electrical power is required to operate all onboard systems, including life support. | serviceModule | FLR-R030 Crew System Monitoring Requirement |
| CLR-R018 | LMDS Throttleable Engine | Technical | The LunarModuleDescentStage shall provide a main engine with a throttleable thrust range. | A variable thrust is essential for the powered descent, allowing the crew to precisely control the rate of descent for a soft landing. | lunarModuleDescentStage | FLR-R046 Descent Propulsion Requirement |
| CLR-R019 | LMDS Landing Gear | Technical | The LunarModuleDescentStage shall incorporate a landing gear system capable of absorbing the energy of a lunar touchdown. | The landing gear must prevent structural damage to the lander and protect the crew from the forces of the final landing impact. | lunarModuleDescentStage | FLR-R002 Consumable Conditioning Requirement |
| CLR-R020 | LMAS Ascent Engine | Technical | The LunarModuleAscentStage shall provide a fixed-thrust engine capable of lifting the stage from the lunar surface into orbit. | A highly reliable, non-throttleable engine provides the simplest and most robust means of achieving lunar orbit for rendezvous. | lunarModuleAscentStage | FLR-R066 Ascent Propulsion Requirement |
| CLR-R021 | LMAS Crew Cabin | Technical | The LunarModuleAscentStage shall provide a pressurized cabin for a crew of two. | The ascent stage serves as the flight deck and habitat for the crew during lunar orbit and surface operations. | lunarModuleAscentStage | FLR-R062 Cabin Repressurization Requirement |
| CLR-R022 | PSA Pressure Containment | Technical | The PressureSuiteAssembly shall maintain a positive internal pressure environment for the astronaut. | Maintaining pressure is the most fundamental requirement for keeping an astronaut alive in the vacuum of space. | psa | FLR-R053 Egress Preparation Requirement |
| CLR-R023 | PSA Mobility | Technical | The PressureSuiteAssembly shall allow sufficient mobility for the crew to perform required EVA tasks. | The suit must not be so rigid that it prevents the crew from walking, bending, and using tools effectively. | psa | FLR-R055 Surface Mobility Requirement |
| CLR-R024 | PLSS Oxygen Supply | Technical | The PortableLifeSupportSystem shall contain and supply breathable oxygen to the crew member. | A finite supply of oxygen is required for the duration of the extravehicular activity. | plss | FLR-R054 Cabin Depressurization Requirement |
| CLR-R025 | PLSS Contaminant Removal | Technical | The PortableLifeSupportSystem shall remove carbon dioxide and other contaminants from the suit's atmosphere. | Recirculating the suit's atmosphere requires the continuous removal of harmful metabolic byproducts like CO2. | plss | FLR-R053 Egress Preparation Requirement |
| CLR-R026 | SIC Separation System | Technical | The S-IC stage shall incorporate a pyrotechnic separation system to cleanly detach from the S-II stage. | A reliable separation system is critical to jettison the massive first stage and allow the second stage to ignite without obstruction. | stage1 | FLR-R014 Ascent Staging Command Requirement |
| CLR-R027 | SII Structural Integrity | Technical | The S-II stage shall maintain structural integrity under the loads of its own thrust and the mass of the upper stages. | The S-II stage structure must not fail under the combined stresses of acceleration and the weight of the fully fueled third stage and spacecraft. | stage2 | FLR-R010 Stage2 Propulsion Requirement |
| CLR-R028 | SIVB Attitude Control System | Technical | The S-IVB stage shall incorporate an attitude control system to maintain stable orientation during coast phases. | The stage must maintain a correct and stable attitude in orbit to ensure proper thermal conditions and alignment for the TLI burn. | stage3 | FLR-R020 Tli Thrust Control Requirement |
| CLR-R029 | IU Telemetry System | Technical | The SaturnVInstrumentUnit shall gather and transmit vehicle health and status data to ground telemetry systems. | Real-time data on the launch vehicle's performance is critical for ground controllers to monitor the ascent. | instrumentUnit | FLR-R017 Ground Telemetry Analysis Requirement |
| CLR-R030 | CM Docking Mechanism | Technical | The ApolloCommandModule shall incorporate a probe and drogue docking mechanism. | A reliable and proven docking mechanism is required to physically connect with the Lunar Module in Earth and Lunar orbit. | commandModule | FLR-R023 Module Connection Requirement |
| CLR-R031 | SM Thermal Control System | Technical | The ApolloServiceModule shall incorporate radiators to reject waste heat from the spacecraft into space. | An active thermal control system is necessary to prevent onboard systems and the crew cabin from overheating. | serviceModule | FLR-R031 Ground System Monitoring Requirement |
| CLR-R032 | LMDS Launch Platform | Technical | The LunarModuleDescentStage shall provide a stable, structurally sound platform for the ascent stage to launch from. | The descent stage must serve as a one-time launch pad on the Moon, withstanding the forces of the ascent engine ignition. | lunarModuleDescentStage | FLR-R065 Ascent Thrust Initiation Requirement |
| CLR-R033 | LMAS Rendezvous Radar | Technical | The LunarModuleAscentStage shall incorporate a radar system to track the Command Module during rendezvous. | An independent tracking capability is required for the LM to compute its trajectory relative to the CSM for a successful rendezvous. | lunarModuleAscentStage | FLR-R067 Rendezvous Calculation Requirement |
| CLR-R034 | PSA Helmet Visibility | Technical | The PressureSuiteAssembly shall provide a helmet with a wide, unobstructed field of view and protective visors. | Clear and wide visibility is essential for navigation, task performance, and hazard identification on the lunar surface. | psa | FLR-R055 Surface Mobility Requirement |
| CLR-R035 | PLSS Cooling System | Technical | The PortableLifeSupportSystem shall circulate cooling fluid to regulate astronaut body temperature. | An active cooling system is required to remove excess body heat and prevent overheating during strenuous activity in the suit. | plss | FLR-R053 Egress Preparation Requirement |
| CLR-R036 | Staging Interface Load Transfer | Technical | The StagingInterface shall be capable of transferring all structural loads from the upper stage to the lower stage during powered ascent. | Failure to transfer loads would result in catastrophic structural failure of the launch vehicle. | stage1ToStage2, stage2ToStage3 | FLR-R008 Stage1 Thrust Magnitude Requirement |
| CLR-R037 | Staging Interface Clean Separation | Technical | The StagingInterface shall ensure a clean separation with no re-contact between stages upon receiving a valid separation command. | Re-contact or debris could damage the upper stage engine, preventing ignition and causing mission failure. | stage1ToStage2, stage2ToStage3 | FLR-R014 Ascent Staging Command Requirement |
| CLR-R038 | Guidance Interface Command Integrity | Technical | The GuidanceInterface shall transmit control commands with a data integrity of 99.999% or greater. | Corrupted guidance commands could lead to loss of vehicle control. | iuToStage3 | FLR-R013 Ascent Guidance Requirement |
| CLR-R039 | Guidance Interface Telemetry Latency | Technical | The GuidanceInterface shall provide real-time telemetry from the stage to the controller with a latency of less than 10 milliseconds. | Low latency is critical for the guidance computer to make timely adjustments to the vehicle's trajectory. | iuToStage3 | FLR-R017 Ground Telemetry Analysis Requirement |
| CLR-R040 | CSM Interface Power Transfer | Technical | The CSMInterface shall transfer electrical power from the supplier to the consumer with a voltage drop of less than 2%. | Efficient power transfer is necessary to ensure all Command Module systems are adequately powered. | cmSMUmbilical | FLR-R030 Crew System Monitoring Requirement |
| CLR-R041 | CSM Interface Life Support Integrity | Technical | The CSMInterface shall transport life support consumables with zero leakage. | Any leakage of oxygen or water would be a critical, life-threatening failure. | cmSMUmbilical | FLR-R025 Attitude Control Requirement |
| CLR-R042 | Docking Interface Structural Rigidity | Technical | The DockingInterface shall form a rigid structural connection capable of withstanding attitude control maneuvers. | The two docked spacecraft must behave as a single, rigid body to ensure stable flight control. | cmLMDocking | FLR-R023 Module Connection Requirement |
| CLR-R043 | Docking Interface Pressurized Seal | Technical | The DockingInterface shall create a pressurized seal between the two vehicle cabins. | A secure, pressurized tunnel is required to allow for the safe transfer of crew members between vehicles without spacesuits. | cmLMDocking | FLR-R071 Intervehicular Crew Transfer Requirement |
| CLR-R044 | LM Staging Interface Separation | Technical | The LMStagingInterface shall execute a clean pyrotechnic separation of the Ascent Stage from the Descent Stage. | A reliable separation is critical for the Ascent Stage to lift off from the lunar surface unimpeded. | lmInterstage | FLR-R065 Ascent Thrust Initiation Requirement |
| CLR-R045 | EVA Interface Secure Connection | Technical | The EVAInterface shall provide secure, quick-disconnect fittings for all fluid and data connections. | Connections must be reliable and easy for a gloved astronaut to operate, while preventing accidental disconnection during an EVA. | suitToPLSSUmbilical | FLR-R053 Egress Preparation Requirement |
| CLR-R046 | LV Payload Interface Structural | Technical | The interface between the SaturnVInstrumentUnit and the ApolloSpacecraftLMAdapter shall withstand all structural loads during launch and ascent. | This interface bears the entire mechanical load of the 45-ton Apollo spacecraft stack during its most violent flight phase. | instrumentUnit, spacecraftLMAdapter | FLR-R008 Stage1 Thrust Magnitude Requirement |
| CLR-R047 | SLALM Deployment | Technical | The ApolloSpacecraftLMAdapter shall deploy the Lunar Module upon command with sufficient force to prevent re-contact. | A successful and clean deployment of the LM after transposition and docking is critical to beginning the lunar phase of the mission. | spacecraftLMAdapter | FLR-R022 Module Repositioning Requirement |
| CLR-R048 | LES Interface Structural Integrity | Technical | The interface between the ApolloCommandModule and the ApolloLaunchEscapeSystem shall maintain structural integrity under all launch and ascent aerodynamic loads. | A structural failure of this interface could cause the LES to detach prematurely, endangering the crew and the mission. | lesConnection | FLR-R016 Crew Ascent Abort Requirement |
| CLR-R049 | LES Interface Command Reliability | Technical | The interface between the ApolloCommandModule and the ApolloLaunchEscapeSystem shall reliably transmit abort and jettison commands to the LES motors. | The failure to transmit an abort command in an emergency would be catastrophic. The failure to jettison the LES would prevent mission continuation. | lesConnection | FLR-R016 Crew Ascent Abort Requirement |
| CLR-R050 | LMDS Velocity Limits | Technical | The LunarModuleDescentStage shall command thrust to ensure that at the moment of footpad touchdown, the vehicle's velocities do not exceed the following limits: Vertical Velocity: <= 3.05 meters per second (10 feet per second) Horizontal Velocity: <= 1.22 meters per second (4 feet per second) | These limits prevent structural damage to the ascent stage interface or a post-impact tip-over of the LM. | lunarModuleDescentStage | FLR-R082 Final Velocity Requirement |
| CLR-R051 | Cabin Environmental Control Requirement | Technical | The Apollo 11 Mission's spacecraft environmental control system shall maintain cabin temperature between 20°C and 25°C and oxygen partial pressure between 2.5 pounds per square inch and 4.0 pounds per square inch for all 8 days of the mission, for a crew of three. | Maintaining a stable and safe cabin environment is crucial for astronaut health, comfort, and performance throughout the mission duration, directly supporting the 'Go to Moon' goal and human safety. | commandModule | FLR-R102 Atmospheric Scrubbing Function |
| CLR-R052 | GNC Guidance Precision | Technical | The Apollo 11 Mission's guidance system shall calculate mid-course correction burns with a delta-V accuracy of +/- 0.1 meters per second, ensuring the trajectory remains within mission-defined corridors. | Precise calc of trajectory adjustments is vital for minimizing fuel consumption and ensuring the spacecraft stays on the optimal path, supporting mission efficiency and success. | instrumentUnit | FLR-R028 Course Correction Calculation Requirement |
| CLR-R053 | RCS Control Stability | Technical | The Apollo 11 Mission's control system shall maintain spacecraft attitude within +/- 0.5 degrees of commanded orientation during orbital and coast phases. | Stable spacecraft attitude is necessary for accurate navigation, efficient engine burns, proper thermal control, and reliable communication, impacting multiple critical mission functions. | serviceModule | FLR-R096 Spacecraft Orientation Control |
| CLR-R054 | LMDS Radar Precision | Technical | The Apollo 11 Mission's lunar lander's navigation system shall provide real-time altitude and velocity data with an accuracy of +/- 1 meter for altitude and +/- 0.1 meters per second for velocity during the final 50 meters of powered descent. | High-fidelity real-time navigation data is critical for the lunar lander's autonomous and manual control during the final, most hazardous, phase of descent, ensuring a safe touchdown. | lunarModuleDescentStage | FLR-R097 Descent Data Acquisition |
| CLR-R055 | SIC Thrust Magnitude | Technical | The Apollo 11 Mission's launch vehicle's first stage propulsion shall provide a minimum thrust of 34.5 Meganewtons at liftoff. | Sufficient thrust from the first stage is fundamental to overcome Earth's gravity and initiate the launch sequence, enabling the entire mission. | ||
| CLR-R056 | SPS Ignition Reliability | Technical | The Apollo 11 Mission's in-space propulsion system shall be capable of performing at least 3 full-duration major burns (e.g., Lunar Orbit Insertion, Trans-Earth Injection) with a 99.8% ignition success rate for each burn. | The reliability of in-space propulsion is paramount for achieving and departing lunar orbit, directly impacting mission success and crew safety; failure means being stranded. | serviceModule | FLR-R024 In Space Propulsion Requirement |
| CLR-R057 | DPS Throttling Range | Technical | The Apollo 11 Mission's lunar lander's descent propulsion system shall provide throttleable thrust from 10% to 100% of maximum thrust to enable precise lunar landing control. | Throttling capability provides the fine control necessary to manage descent rate and fuel consumption during the lunar landing, crucial for achieving a soft and controlled touchdown. | lunarModuleDescentStage | FLR-R099 Descent Rate Modulation |
| CLR-R058 | LMAS Burn Duration | Technical | The Apollo 11 Mission's lunar lander's ascent propulsion system shall achieve a burn duration of <= 400 seconds to insert the ascent stage into lunar orbit. | A specific burn duration is required to ensure the ascent stage achieves the correct lunar orbit for rendezvous, directly enabling the crew's return to the Command Module. | lunarModuleAscentStage | FLR-R066 Ascent Propulsion Requirement |
| CLR-R059 | Primary Structure Load Limit | Technical | All primary structural elements of the Apollo 11 Mission launch system shall withstand launch loads of up to 4 gees without permanent deformation or failure. | Structural integrity during the high-stress launch phase is absolutely essential to prevent catastrophic failure and ensure the vehicle and crew reach orbit safely. | ||
| CLR-R060 | CM Heat Shield Thermal Perf | Technical | The Apollo 11 Mission's crew vehicle heat shield shall ablate as designed and limit internal crew compartment temperature rise to less than 5°C during atmospheric re-entry. | The heat shield is critical for crew survival during re-entry by protecting against extreme temperatures, directly addressing human safety. | commandModule | FLR-R100 Thermal Protection Logic |
| CLR-R061 | Pyrotechnic Initiation Reliability | Technical | All pyrotechnic devices (e.g., stage separation, parachute deployment) used in the Apollo 11 Mission shall have a 99.99% initiation reliability. | Highly reliable pyrotechnic devices are crucial for sequential mission events like stage separations and parachute deployment, as failures in these systems could lead to catastrophic mission loss or crew fatalities. | ||
| CLR-R062 | Docking Mechanism Reliability | Technical | The Apollo 11 Mission's spacecraft docking system shall enable two spacecraft to mate and form a rigid connection in lunar orbit, capable of withstanding dynamic loads during rendezvous maneuvers, with a 99.5% success rate for capture and latching. | Reliable docking is essential for transferring crew and samples, making it a critical path to crew return and scientific goals. Failure would mean being stranded in lunar orbit. | ||
| CLR-R063 | LMDS Landing Gear Energy | Technical | The Apollo 11 Mission's lunar lander's landing gear shall absorb impact energy equivalent to a 3 meters per second vertical velocity and 1 meter per second horizontal velocity at touchdown without structural failure. | The landing gear must reliably absorb the forces of lunar touchdown to protect the lander structure, its internal systems, and the crew. | ||
| CLR-R064 | ECS Water Supply Rate | Technical | The Apollo 11 Mission's crew's potable water system shall provide a minimum of 2 kilograms of potable water per crew member per day. | Adequate potable water is a fundamental requirement for sustaining crew health and life throughout the mission. | ||
| CLR-R065 | ECS Filter Efficiency | Technical | The Apollo 11 Mission's cabin atmosphere purification system shall maintain carbon dioxide levels below 0.5% by volume and remove particulate matter >= 0.5 microns with 99% efficiency. | Maintaining breathable air free of harmful contaminants is a continuous and critical life support function, directly impacting crew health and safety. | ||
| CLR-R066 | Data Handling Integrity | Technical | The Apollo 11 Mission's data acquisition system shall record and store all critical telemetry data for the entire mission duration, with no less than 99.9% data integrity. | High data integrity ensures that ground control has accurate information for real-time decision-making, post-flight analysis, and mission lessons learned. | ||
| CLR-R067 | Comm Video Bandwidth | Technical | The Apollo 11 Mission spacecraft shall be capable of transmitting live video from the lunar surface to Earth with a resolution of at least 320x240 pixels and a frame rate of >= 10 frames per second. | Live video transmission from the lunar surface significantly enhances public engagement and inspiration, and provides valuable real-time visual context for mission operations. | lunarModuleAscentStage | FLR-R103 Telemetry Stream Integrity |
| CLR-R068 | EMU Pressure Containment | Technical | The Apollo 11 Mission's Extravehicular Mobility Unit shall maintain internal pressure at 25.5 kilopascals with no more than 5% pressure loss per hour during Extravehicular Activity. | Maintaining internal pressure in the Extravehicular Mobility Unit is critical for astronaut safety and performance during Extravehicular Activity in the vacuum of space. | psa | FLR-R104 EMU Pressure Maintenance |
| CLR-R069 | EASEP Operational Duration | Technical | The Apollo 11 Mission's deployed scientific instruments shall be operational for a minimum of 30 days post-deployment and transmit at least 100 Kilobytes of scientific data per day for this period. | Ensuring long-term operation and sufficient data transmission from deployed instruments maximizes the scientific return and provides continuous monitoring of the lunar environment. | lunarModuleDescentStage | FLR-R059 Instrument Deployment Requirement |
| CLR-R070 | Mission System Reliability | Technical | All mission-critical flight systems of the Apollo 11 Mission (e.g., primary propulsion, life support, main computer) shall demonstrate a statistical reliability of >= 0.999 (three nines) for their operational lifetimes. | Extremely high reliability for critical systems is foundational to ensuring mission success and astronaut safety, given the inherent risks and remote operating environment. | ||
| CLR-R071 | Flight Software Defect Rate | Technical | The Apollo 11 Mission's flight software for primary guidance and control shall have zero critical defects (Severity 1 or 2) identified during a minimum of 2,000 hours of integrated hardware-in-the-loop simulation prior to flight. | Zero critical software defects are essential for autonomous and commanded operations, as software failures could directly jeopardize mission success and crew safety. | instrumentUnit | FLR-R105 Software Mission Proficiency |
| CLR-R072 | Component Acceptance Rate | Technical | All flight components of the Apollo 11 Mission shall undergo acceptance testing to verify conformance to specifications before integration, with <= 0.1% non-conformance rate. | Rigorous acceptance testing ensures that only compliant and reliable components are integrated into the flight system, minimizing risks from faulty parts. | ||
| CLR-R073 | Material Vacuum Resistance | Technical | All spacecraft materials of the Apollo 11 Mission shall withstand long-term exposure to the space environment (vacuum, radiation, thermal cycling) for up to 14 days without critical degradation of structural integrity or functional performance. | Material robustness in the extreme space environment is fundamental to ensuring the long-term integrity and functionality of the spacecraft, directly impacting mission safety and success. | serviceModule | FLR-R106 Space Environment Resilience |
| CLR-R074 | Electronic EMI Immunity | Technical | The entire Apollo 11 Mission system shall be designed to withstand the electromagnetic interference (EMI) environment of launch and space operations without functional degradation. | Immunity to electromagnetic interference ensures that all electronic systems operate reliably without disruption from internal or external electromagnetic noise, vital for mission control and safety. | ||
| CLR-R075 | Image Resolution Standard | Technical | The visual data capture system shall provide a minimum resolution of 2k for still images and 16mm equivalent for motion film. | High-resolution imagery is necessary to meet scientific documentation and public prestige goals. | commandModule | FLR-R107 Visual Data Capture |
| CLR-R076 | Waste Storage Volume | Technical | The waste containment system shall provide a minimum of 0.5 cubic feet of sealed storage per crew member for an 8-day mission. | Prevents cabin contamination and maintains crew hygiene during flight. | commandModule | FLR-R108 Waste Containment Function |
| CLR-R077 | VHF Audio Bandwidth | Technical | The cross-vehicle audio link shall operate within the 250-300 MHz range with a signal-to-noise ratio of at least 20dB. | Ensures clear voice coordination between the LM and CSM during critical lunar operations. | FLR-R109 Cross Vehicle Audio Link | |
| CLR-R078 | System Redundancy Mapping | Technical | All Level-1 critical electronic components shall be duplicated in an 'A' and 'B' bus configuration with automatic failover. | Implements the fault tolerance required to prevent mission loss from a single component failure. | serviceModule | FLR-R110 Component Fault Tolerance |
| CLR-R079 | Medical Kit Specification | Technical | The onboard medical kit shall contain antibiotics, analgesics, and minor surgical tools certified for use in zero-gravity. | Enables the crew to manage health incidents without immediate Earth-based assistance. | commandModule | FLR-R111 Human Medical Self Sufficiency |
| CLR-R080 | Ground Archival Protocol | Technical | Mission telemetry shall be recorded on magnetic tape at three geographically distinct sites with 99.9% data parity. | Ensures long-term preservation of mission data for future scientific analysis. | instrumentUnit | FLR-R112 Data Redundancy Archiving |
| CLR-R081 | Crew Seat Load Factor | Technical | The crew seating system shall attenuate peak launch acceleration to ensure loads experienced by the crew do not exceed 6g. | Ensures crew safety during the high-stress launch phase. | commandModule | FLR-R003 Crew Ingress Requirement |
| CLR-R082 | Launch Abort Thresholds | Technical | The Instrument Unit shall trigger an automatic abort if the vehicle attitude deviation exceeds 5 degrees or if tank pressure drops below 90% of nominal. | Ensures a safe abort sequence if critical limits are violated. | instrumentUnit | FLR-R006 Countdown Abort Requirement |
| CLR-R083 | Separation Timer Precision | Technical | Pyrotechnic separation events shall be triggered within 50 milliseconds of the command issue to prevent re-contact. | Ensures clean separation of stages and modules. | instrumentUnit | FLR-R014 Ascent Staging Command Requirement |
| CLR-R084 | Cabin Pressure Hold | Technical | The crew cabin shall maintain a pressure leak rate of less than 0.1 psi per hour at a nominal pressure of 5.0 psi. | Defines the boundary for cabin integrity for crew survival in vacuum. | commandModule | FLR-R004 Cabin Pressurization Requirement |
| CLR-R085 | Timing Synch Error | Technical | The master mission clock system shall maintain synchronization across all segments with a drift of less than 1ms per 24 hours. | Precise timing is required to synchronize thousands of events across ground and flight segments. | instrumentUnit | FLR-R005 Countdown Sequencing Requirement |
| CLR-R086 | Engine Start Latency | Technical | The S-IC engine ignition sequence shall complete within 150ms of the authenticated launch command. | Timely ignition is critical to meet the planetary launch window and intended trajectory. | stage1 | FLR-R007 Stage1 Thrust Initiation Requirement |
| CLR-R087 | Staging Shock Limit | Technical | Separation pyrotechnics shall not exceed a peak shock load of 50g on adjacent structural interfaces. | Limits mechanical stress on the second stage to prevent damage during first-stage jettison. | stage2 | FLR-R009 Stage2 Thrust Initiation Requirement |
| CLR-R088 | Cutoff Delta V Error | Technical | Residual thrust from the S-IVB engine post-cutoff shall not exceed 0.05 m/s. | Precise termination of thrust is necessary to achieve stable Earth orbit insertion. | stage3 | FLR-R012 Orbit Insertion Thrust Termination Requirement |
| CLR-R089 | Cockpit Display Refresh | Technical | Mission-critical flight displays in the CM cockpit shall have a minimum data refresh rate of 2 Hz. | Provides the crew with real-time situational awareness for manual intervention or aborts. | commandModule | FLR-R015 Crew Ascent Monitoring Requirement |
| CLR-R090 | Telemetry Sampling Rate | Technical | High-rate telemetry channels for engine health shall be sampled at a minimum of 100 samples per second. | High-fidelity data is needed for ground-based automated verification of propulsion health. | instrumentUnit | FLR-R018 Ground Performance Verification Requirement |
| CLR-R091 | Post Tli Separation Velocity | Technical | The S-IVB auxiliary propulsion system shall provide a minimum delta-V of 1.0 m/s for post-TLI separation. | Ensures the spent third stage moves away from the spacecraft to prevent re-contact. | stage3 | FLR-R019 Tli Thrust Initiation Requirement |
| CLR-R092 | Sla Separation Velocity | Technical | The SLA separation springs shall provide a minimum separation velocity of 0.3 meters per second. | Mechanical force is required to move the spacecraft away from the adapter for transposition. | spacecraftLMAdapter | FLR-R021 Module Separation Requirement |
| CLR-R093 | Transposition Maneuver Rate | Technical | The RCS shall provide a minimum angular acceleration of 2.0 deg/sec² for transposition maneuvers. | Defines the control authority needed to rotate the CM 180 degrees for docking. | serviceModule | FLR-R022 Module Repositioning Requirement |
| CLR-R094 | Sextant Angular Accuracy | Technical | The onboard sextant shall provide an angular measurement accuracy of +/- 10 arcseconds. | Required for precise celestial navigation fixes to update the state vector. | instrumentUnit | FLR-R026 Navigational Data Acquisition Requirement |
| CLR-R095 | State Vector Integration Latency | Technical | The navigation computer shall integrate new tracking data into the state vector within 500ms of receipt. | Minimizes latency in trajectory models for accurate course correction calculations. | instrumentUnit | FLR-R027 Trajectory Calculation Requirement |
| CLR-R096 | Command Turnaround Latency | Technical | The MSFN ground stations shall maintain an uplink command turnaround latency of less than 2.0 seconds. | Fast turnaround is essential for ground controllers to react to time-sensitive anomalies. | instrumentUnit | FLR-R033 Spacecraft Data Reception Requirement |
| CLR-R097 | Ground Station Sensitivity | Technical | The Unified S-Band system shall have a minimum receiver sensitivity of -120 dBm. | Ensures weak signals from lunar distances are accurately tracked. | instrumentUnit | FLR-R034 Ground Tracking Requirement |
| CLR-R098 | Relay Network Bit Error Rate | Technical | The ground communication network shall maintain a Bit Error Rate (BER) of less than 10⁻⁶ across all relay sites. | High signal fidelity ensures voice and telemetry remain intelligible. | instrumentUnit | FLR-R035 Ground Communication Relay Requirement |
| CLR-R099 | Timeline Drift Alert | Technical | The mission timeline management software shall trigger an alert if execution drifts more than 5 minutes from plan. | Maintains operational discipline for synchronized orbital events. | commandModule | FLR-R036 Crew Activity Scheduling Requirement |
| CLR-R100 | Sleep Acoustic Limit | Technical | Ambient noise levels in the crew sleep area shall be limited to 55 dBA. | Technical requirement for ensuring restorative crew sleep. | commandModule | FLR-R037 Crew Rest Provision Requirement |
| CLR-R101 | Target Orbit Perigee | Technical | The LOI burn shall target a lunar orbit perigee of 60 +/- 5 nautical miles. | Achieving specific orbit parameters is critical for landing and rendezvous. | serviceModule | FLR-R039 Loi Guidance Requirement |
| CLR-R102 | Hatch Clearance Dimensions | Technical | The LM crew transfer hatch shall provide a minimum clear opening of 32 x 32 inches. | Ensures astronauts in bulky suits can safely move between modules. | lunarModuleAscentStage | FLR-R042 Lander Crew Transfer Requirement |
| CLR-R103 | Lm Computer Alignment Time | Technical | The LM primary guidance computer shall be initialized and aligned within 60 minutes of activation. | Verifies configuration readiness before undocking. | lunarModuleAscentStage | FLR-R043 Lander Configuration Requirement |
| CLR-R104 | Docking Latch Torque Threshold | Technical | The LM docking latches shall require a minimum of 300 inch-pounds of torque to achieve a rigid seal. | Defines the mechanical requirement for securing the interface between vehicles. | FLR-R044 Module Disengagement Requirement | |
| CLR-R105 | Undocking Separation Velocity | Technical | The undocking maneuver shall target a relative separation velocity of 0.1 +/- 0.05 meters per second. | Prevents re-contact between CSM and LM after separation. | FLR-R045 Module Separation Maneuver Requirement | |
| CLR-R106 | Dsky Display Brightness | Technical | The LM DSKY displays shall be readable under direct sunlight (minimum 500 nits brightness). | Necessary for reading landing data during the bright lunar day. | lunarModuleAscentStage | FLR-R047 Descent Data Display Requirement |
| CLR-R107 | Landing Radar Lock Time | Technical | The landing radar shall achieve frequency lock within 5 seconds of the Radar Enable command. | Rapid data acquisition is required to update altitude before final descent. | lunarModuleDescentStage | FLR-R048 Descent Data Processing Requirement |
| CLR-R108 | Post Landing Safe Time | Technical | The LM post-landing safe sequence shall complete within 60 seconds of touchdown. | Securing propulsion prevents hazardous pressure build-up on the surface. | lunarModuleDescentStage | FLR-R051 Post Landing Safing Requirement |
| CLR-R109 | Lm Cabin Integrity Leak Rate | Technical | The LM cabin integrity test shall confirm a leak rate of <= 0.05 psi/hour before EVA egress. | Ensures cabin can be re-pressurized before crew departs. | lunarModuleAscentStage | FLR-R052 Post Landing Verification Requirement |
| CLR-R110 | Symbolic Mount Rigidity | Technical | The flag assembly shall withstand a 10-Newton lateral deployment force without collapsing. | Quantitative requirement to ensure national symbol remains upright. | psa | FLR-R056 Symbolic Deployment Requirement |
| CLR-R111 | Sample Tool Mechanical Advantage | Technical | Lunar sample tongs shall provide a minimum 5:1 mechanical leverage for rock collection. | Compensates for reduced manual dexterity of EVA gloves. | psa | FLR-R057 Sample Collection Requirement |
| CLR-R112 | Easep Thermal Insulation | Technical | EASEP experiment packages shall utilize 20-layer aluminized Mylar for thermal insulation. | Protects instruments from extreme lunar thermal cycles. | lunarModuleDescentStage | FLR-R059 Instrument Deployment Requirement |
| CLR-R113 | Eva Communication Range | Technical | Astronaut radio systems shall maintain voice link at a maximum range of 500 meters from the LM. | Defines the technical boundary for safe astronaut travel on the surface. | cmLMDocking, psa | FLR-R061 Eva Ingress Requirement |
| CLR-R114 | Surface Timeline Sync | Technical | Surface operations shall synchronize to UTC time with an accuracy of +/- 0.5 seconds. | Synchronization is vital for managing the timeline relative to the CSM orbit. | instrumentUnit | FLR-R064 Surface Timeline Management Requirement |
| CLR-R115 | Lm Ascent Delta V Minimum | Technical | The LM ascent stage shall provide a minimum delta-V of 1,850 m/s to achieve lunar orbit. | Specifies required propulsive performance to escape Moon gravity. | lunarModuleAscentStage | FLR-R066 Ascent Propulsion Requirement |
| CLR-R116 | Rendezvous Orbit Target | Technical | The rendezvous radar shall target an orbital node within 5 km of the CSM. | Approach accuracy ensures vehicles are within terminal docking range. | lunarModuleAscentStage | FLR-R068 Rendezvous Execution Requirement |
| CLR-R117 | Reentry Flight Path Angle | Technical | The CM reentry flight path angle shall be targeted at -6.5 degrees +/- 0.2 degrees. | Precise angle manages heating and prevents atmospheric skipping. | commandModule | FLR-R079 Reentry Guidance Requirement |
Quantitative requirements register¶
Product Quantitative requirements register
The numeric thresholds stated by the requirements: the quantity, the limit and its unit, with the constraint the requirement places on it.
Use it to check design values and test limits against the requirement, and see which units the thresholds use.
The numeric thresholds stated by the requirements: the quantity, the limit and its unit, with the constraint the requirement places on it.
Use it to check design values and test limits against the requirement, and see which units the thresholds use.
76 thresholds in 50 requirements; 62 carry a unit, and the other 14 are dimensionless numbers (10 typed Integer, 4 typed Real), such as maxAcceptableInjuries, minRequiredSciencePackages, minRequiredVisualSystems, minStillPhotosCount.
| ID | Requirement | Level | Attribute | Quantity | Limit | Unit | Constraint |
|---|---|---|---|---|---|---|---|
| HLR-R001 | Crew Return Safety Requirement | Mission | maxAcceptableInjuries | Integer | 0 | crewInjuryCount <= maxAcceptableInjuries | |
| HLR-R002 | Lunar Lander Soft Landing Requirement | Mission | maxLandingZoneDeviation | length | 1000 | m | (actualVerticalVelocity <= maxVerticalVelocity) and (actualHorizontalVelocity <= maxHorizontalVelocity) and (actualLandingZoneDeviation <= maxLandingZoneDeviation) |
| HLR-R002 | Lunar Lander Soft Landing Requirement | Mission | maxHorizontalVelocity | speed | 0.5 | m/s | (actualVerticalVelocity <= maxVerticalVelocity) and (actualHorizontalVelocity <= maxHorizontalVelocity) and (actualLandingZoneDeviation <= maxLandingZoneDeviation) |
| HLR-R002 | Lunar Lander Soft Landing Requirement | Mission | maxVerticalVelocity | speed | 2 | m/s | (actualVerticalVelocity <= maxVerticalVelocity) and (actualHorizontalVelocity <= maxHorizontalVelocity) and (actualLandingZoneDeviation <= maxLandingZoneDeviation) |
| HLR-R003 | Trans Lunar Injection Accuracy Requirement | Mission | maxTimeToLunarOrbitInsertion | duration | 75 | h | (actualDeltaVAccuracy <= maxDeltaVAccuracy) and (actualTimeToLunarOrbitInsertion <= maxTimeToLunarOrbitInsertion) |
| HLR-R003 | Trans Lunar Injection Accuracy Requirement | Mission | maxDeltaVAccuracy | speed | 0.5 | m/s | (actualDeltaVAccuracy <= maxDeltaVAccuracy) and (actualTimeToLunarOrbitInsertion <= maxTimeToLunarOrbitInsertion) |
| HLR-R004 | Communication Uptime Requirement | Mission | minCommunicationUptimePercentage | RatioValue | 95 | % | (actualCommunicationUptimePercentage >= minCommunicationUptimePercentage) and (maxSingleBlackoutDuration <= allowedSingleBlackoutDuration) |
| HLR-R004 | Communication Uptime Requirement | Mission | allowedSingleBlackoutDuration | duration | 10 | min | (actualCommunicationUptimePercentage >= minCommunicationUptimePercentage) and (maxSingleBlackoutDuration <= allowedSingleBlackoutDuration) |
| HLR-R006 | Lunar Sample Collection Quantity Requirement | Mission | minRequiredSampleMass | mass | 20 | kg | (actualSampleMass >= minRequiredSampleMass) and (contaminationPercentage <= maxContaminationPercentage) |
| HLR-R006 | Lunar Sample Collection Quantity Requirement | Mission | maxContaminationPercentage | RatioValue | 0.1 | % | (actualSampleMass >= minRequiredSampleMass) and (contaminationPercentage <= maxContaminationPercentage) |
| HLR-R007 | Scientific Instrument Deployment Requirement | Mission | minRequiredSciencePackages | Integer | 2 | (actualDeployedVisualSystems >= minRequiredVisualSystems) and (actualDeployedSciencePackages >= minRequiredSciencePackages) and (actualDataTransmissionDuration >= minDataTransmissionDuration) | |
| HLR-R007 | Scientific Instrument Deployment Requirement | Mission | minRequiredVisualSystems | Integer | 1 | (actualDeployedVisualSystems >= minRequiredVisualSystems) and (actualDeployedSciencePackages >= minRequiredSciencePackages) and (actualDataTransmissionDuration >= minDataTransmissionDuration) | |
| HLR-R007 | Scientific Instrument Deployment Requirement | Mission | minDataTransmissionDuration | duration | 30 | d | (actualDeployedVisualSystems >= minRequiredVisualSystems) and (actualDeployedSciencePackages >= minRequiredSciencePackages) and (actualDataTransmissionDuration >= minDataTransmissionDuration) |
| HLR-R008 | Lunar Visual Documentation Requirement | Mission | minStillPhotosCount | Integer | 1000 | (actualStillPhotosCount >= minStillPhotosCount) and (actualMotionPictureDuration >= minMotionPictureDuration) | |
| HLR-R008 | Lunar Visual Documentation Requirement | Mission | minMotionPictureDuration | duration | 30 | min | (actualStillPhotosCount >= minStillPhotosCount) and (actualMotionPictureDuration >= minMotionPictureDuration) |
| HLR-R010 | Planetary Protection Quarantine Requirement | Mission | requiredQuarantineLevel | Integer | 5 | (actualQuarantineLevel == requiredQuarantineLevel) and not biologicalContaminationDetected and not contaminationThresholdExceeded | |
| HLR-R028 | Crew Sleep Environment Quality | Mission | minUndisturbedSleepDuration | duration | 6 | h | (actualUndisturbedSleepDuration >= minUndisturbedSleepDuration) and (actualNoiseLevelMax <= maxNoiseLevelReqd) |
| HLR-R028 | Crew Sleep Environment Quality | Mission | maxNoiseLevelReqd | soundPressureLevel | 60 | dB | (actualUndisturbedSleepDuration >= minUndisturbedSleepDuration) and (actualNoiseLevelMax <= maxNoiseLevelReqd) |
| HLR-R030 | Crew Alarm Response Time | Mission | maxAlarmResponseTime | duration | 1 | s | actualAlarmResponseTime <= maxAlarmResponseTime |
| HLR-R032 | Lunar Lander To Orbiter Voice Comm | Mission | minSignalClarity | RatioValue | 90 | % | actualSignalClarity >= minSignalClarity |
| HLR-R033 | Extravehicular Mobility Unit Life Support Duration | Mission | minEMULifeSupportDuration | duration | 4 | h | actualEMULifeSupportDuration >= minEMULifeSupportDuration |
| HLR-R035 | Extravehicular Mobility Unit Dexterity For Tasks | Mission | minTaskCompletionSuccessRate | RatioValue | 90 | % | actualTaskCompletionSuccessRate >= minTaskCompletionSuccessRate |
| HLR-R036 | Lunar Surface Mobility Range | Mission | maxFatigueImpact | RatioValue | 10 | % | (actualTraverseDistanceCapability >= minTraverseDistanceCapability) and (actualFatigueImpact <= maxFatigueImpact) |
| HLR-R036 | Lunar Surface Mobility Range | Mission | minTraverseDistanceCapability | length | 50 | m | (actualTraverseDistanceCapability >= minTraverseDistanceCapability) and (actualFatigueImpact <= maxFatigueImpact) |
| HLR-R037 | Extravehicular Activity Tool Security | Mission | maxToolsLost | Integer | 0 | toolsMeetContactRequirement and (toolsLostDuringEVA <= maxToolsLost) | |
| HLR-R038 | Sample Pristine Preservation | Mission | maxTerrestrialContamination | RatioValue | 0.1 | % | actualTerrestrialContamination <= maxTerrestrialContamination |
| HLR-R040 | Sample Geological Context | Mission | minSampleCorrelationPercentage | RatioValue | 90 | % | (actualSampleCorrelationPercentage >= minSampleCorrelationPercentage) and photosHaveScaleReferences |
| HLR-R046 | Abort Sequence Execution Time | Mission | maxAbortExecutionTime | duration | 5 | min | actualAbortExecutionTime <= maxAbortExecutionTime |
| HLR-R047 | Manual Override Response Time | Mission | maxOverrideResponseTime | duration | 1 | s | actualOverrideResponseTime <= maxOverrideResponseTime |
| HLR-R048 | Ground Segment Data Update Frequency | Mission | maxUpdateInterval | duration | 10 | min | actualUpdateInterval <= maxUpdateInterval |
| HLR-R049 | Lunar Lander Ascent Readiness Time | Mission | maxTimeToAscentLaunch | duration | 24 | h | actualTimeFromLandingToAscentLaunch <= maxTimeToAscentLaunch |
| HLR-R050 | Flight Software Update Time | Mission | maxSoftwareUpdateDuration | duration | 1 | h | actualSoftwareUpdateDuration <= maxSoftwareUpdateDuration |
| HLR-R052 | Crew Emergency Medical Proficiency | Mission | minMedicalProficiencyScore | Real | 90 | (medicalProficiencyScore >= minMedicalProficiencyScore) and (externalAssistanceRequiredBeforeTime >= minSelfSufficiencyDuration) | |
| HLR-R052 | Crew Emergency Medical Proficiency | Mission | minSelfSufficiencyDuration | duration | 72 | h | (medicalProficiencyScore >= minMedicalProficiencyScore) and (externalAssistanceRequiredBeforeTime >= minSelfSufficiencyDuration) |
| HLR-R053 | In Flight Procedure Error Rate | Mission | maxProcedureErrorRate | RatioValue | 0.5 | % | actualProcedureErrorRate <= maxProcedureErrorRate |
| HLR-R055 | Crew Psychological State | Mission | minPsychologicalStateScore | Real | 75 | actualPsychologicalStateScore >= minPsychologicalStateScore | |
| HLR-R057 | Micrometeoroid Penetration Risk | Mission | maxAcceptablePenetrationProbability | Real | 0.001 | actualPenetrationProbabilityPerMission <= maxAcceptablePenetrationProbability | |
| HLR-R060 | Post Flight Data Archiving | Mission | minArchivalDuration | duration | 50 | yr | (actualDataAvailabilityPercentage >= minDataAvailabilityPercentage) and (actualArchivalDuration >= minArchivalDuration) |
| HLR-R060 | Post Flight Data Archiving | Mission | minDataAvailabilityPercentage | RatioValue | 99.99 | % | (actualDataAvailabilityPercentage >= minDataAvailabilityPercentage) and (actualArchivalDuration >= minArchivalDuration) |
| CLR-R051 | Cabin Environmental Control Requirement | Technical | minCabinTemperatureReqd | thermodynamicTemperature | 20 | °C | (actualCabinTemperatureMin >= minCabinTemperatureReqd) and (actualCabinTemperatureMax <= maxCabinTemperatureReqd) and (actualOxygenPressureMin >= minOxygenPressureReqd) and (actualOxygenPressureMax <= maxOxygenPressureReqd) |
| CLR-R051 | Cabin Environmental Control Requirement | Technical | maxCabinTemperatureReqd | thermodynamicTemperature | 25 | °C | (actualCabinTemperatureMin >= minCabinTemperatureReqd) and (actualCabinTemperatureMax <= maxCabinTemperatureReqd) and (actualOxygenPressureMin >= minOxygenPressureReqd) and (actualOxygenPressureMax <= maxOxygenPressureReqd) |
| CLR-R051 | Cabin Environmental Control Requirement | Technical | minOxygenPressureReqd | pressure | 2.5 | pound-force per square inch (psi) | (actualCabinTemperatureMin >= minCabinTemperatureReqd) and (actualCabinTemperatureMax <= maxCabinTemperatureReqd) and (actualOxygenPressureMin >= minOxygenPressureReqd) and (actualOxygenPressureMax <= maxOxygenPressureReqd) |
| CLR-R051 | Cabin Environmental Control Requirement | Technical | maxOxygenPressureReqd | pressure | 4 | pound-force per square inch (psi) | (actualCabinTemperatureMin >= minCabinTemperatureReqd) and (actualCabinTemperatureMax <= maxCabinTemperatureReqd) and (actualOxygenPressureMin >= minOxygenPressureReqd) and (actualOxygenPressureMax <= maxOxygenPressureReqd) |
| CLR-R052 | GNC Guidance Precision | Technical | maxDeltaVcalcAccuracy | speed | 0.1 | m/s | (actualDeltaVcalcAccuracy <= maxDeltaVcalcAccuracy) and trajectoryWithinCorridor |
| CLR-R053 | RCS Control Stability | Technical | maxAttitudeDeviation | angularMeasure | 0.5 | ° | actualAttitudeDeviation <= maxAttitudeDeviation |
| CLR-R054 | LMDS Radar Precision | Technical | maxAltitudeAccuracy | length | 1 | m | (actualAltitudeAccuracy <= maxAltitudeAccuracy) and (actualVelocityAccuracy <= maxVelocityAccuracy) |
| CLR-R054 | LMDS Radar Precision | Technical | maxVelocityAccuracy | speed | 0.1 | m/s | (actualAltitudeAccuracy <= maxAltitudeAccuracy) and (actualVelocityAccuracy <= maxVelocityAccuracy) |
| CLR-R055 | SIC Thrust Magnitude | Technical | minLiftoffThrust | force | 34.5 | MN | actualLiftoffThrust >= minLiftoffThrust |
| CLR-R056 | SPS Ignition Reliability | Technical | minMajorBurnCount | Integer | 3 | (actualMajorBurnCount >= minMajorBurnCount) and (actualIgnitionSuccessRate >= minIgnitionSuccessRate) | |
| CLR-R056 | SPS Ignition Reliability | Technical | minIgnitionSuccessRate | RatioValue | 99.8 | % | (actualMajorBurnCount >= minMajorBurnCount) and (actualIgnitionSuccessRate >= minIgnitionSuccessRate) |
| CLR-R057 | DPS Throttling Range | Technical | minRequiredThrottlePercentage | RatioValue | 10 | % | (actualMinThrottlePercentage <= minRequiredThrottlePercentage) and (actualMaxThrottlePercentage >= maxRequiredThrottlePercentage) |
| CLR-R057 | DPS Throttling Range | Technical | maxRequiredThrottlePercentage | RatioValue | 100 | % | (actualMinThrottlePercentage <= minRequiredThrottlePercentage) and (actualMaxThrottlePercentage >= maxRequiredThrottlePercentage) |
| CLR-R058 | LMAS Burn Duration | Technical | maxAscentBurnDuration | duration | 400 | s | actualAscentBurnDuration <= maxAscentBurnDuration |
| CLR-R059 | Primary Structure Load Limit | Technical | requiredMaxLaunchLoadWithstood | acceleration | 4 | gn | (actualMaxLaunchLoadWithstood >= requiredMaxLaunchLoadWithstood) and not permanentDeformationObserved and not structuralFailureObserved |
| CLR-R060 | CM Heat Shield Thermal Perf | Technical | maxInternalTemperatureRise | thermodynamicTemperature | 5 | °C | (actualInternalTemperatureRise < maxInternalTemperatureRise) and heatShieldAblationAsDesigned |
| CLR-R061 | Pyrotechnic Initiation Reliability | Technical | minInitiationReliability | RatioValue | 99.99 | % | actualInitiationReliability >= minInitiationReliability |
| CLR-R062 | Docking Mechanism Reliability | Technical | minCaptureLatchingSuccessRate | RatioValue | 99.5 | % | (actualCaptureLatchingSuccessRate >= minCaptureLatchingSuccessRate) and connectionRigidityMaintained and withstandsDynamicLoads |
| CLR-R063 | LMDS Landing Gear Energy | Technical | minImpactVerticalVelocityRequired | speed | 3 | m/s | (maxImpactVerticalVelocityAbsorbed >= minImpactVerticalVelocityRequired) and (maxImpactHorizontalVelocityAbsorbed >= minImpactHorizontalVelocityRequired) and not structuralFailureOccurred |
| CLR-R063 | LMDS Landing Gear Energy | Technical | minImpactHorizontalVelocityRequired | speed | 1 | m/s | (maxImpactVerticalVelocityAbsorbed >= minImpactVerticalVelocityRequired) and (maxImpactHorizontalVelocityAbsorbed >= minImpactHorizontalVelocityRequired) and not structuralFailureOccurred |
| CLR-R064 | ECS Water Supply Rate | Technical | minWaterRequiredPerCrewPerDay | mass | 2 | kg | actualWaterProvidedPerCrewPerDay >= minWaterRequiredPerCrewPerDay |
| CLR-R065 | ECS Filter Efficiency | Technical | minParticulateRemovalEfficiency | RatioValue | 99 | % | (actualCO2LevelMax <= maxCO2LevelReqd) and (actualParticulateRemovalEfficiency >= minParticulateRemovalEfficiency) |
| CLR-R065 | ECS Filter Efficiency | Technical | maxCO2LevelReqd | RatioValue | 0.5 | % | (actualCO2LevelMax <= maxCO2LevelReqd) and (actualParticulateRemovalEfficiency >= minParticulateRemovalEfficiency) |
| CLR-R066 | Data Handling Integrity | Technical | minDataIntegrityPercentage | RatioValue | 99.9 | % | actualDataIntegrityPercentage >= minDataIntegrityPercentage |
| CLR-R067 | Comm Video Bandwidth | Technical | minVideoHeight | Integer | 240 | (actualVideoWidth >= minVideoWidth) and (actualVideoHeight >= minVideoHeight) and (actualFrameRate >= minFrameRate) | |
| CLR-R067 | Comm Video Bandwidth | Technical | minVideoWidth | Integer | 320 | (actualVideoWidth >= minVideoWidth) and (actualVideoHeight >= minVideoHeight) and (actualFrameRate >= minFrameRate) | |
| CLR-R067 | Comm Video Bandwidth | Technical | minFrameRate | frequency | 10 | fps | (actualVideoWidth >= minVideoWidth) and (actualVideoHeight >= minVideoHeight) and (actualFrameRate >= minFrameRate) |
| CLR-R068 | EMU Pressure Containment | Technical | maxPressureLossRate | RatioValue | 5 | % | (actualPressureLossRate <= maxPressureLossRate) |
| CLR-R068 | EMU Pressure Containment | Technical | nominalEMUInternalPressure | pressure | 25.5 | kPa | (actualPressureLossRate <= maxPressureLossRate) |
| CLR-R069 | EASEP Operational Duration | Technical | minDailyDataTransmission | storageCapacity | 100 | kB | (actualOperationalDuration >= minOperationalDuration) and (actualDailyDataTransmission >= minDailyDataTransmission) |
| CLR-R069 | EASEP Operational Duration | Technical | minOperationalDuration | duration | 30 | d | (actualOperationalDuration >= minOperationalDuration) and (actualDailyDataTransmission >= minDailyDataTransmission) |
| CLR-R070 | Mission System Reliability | Technical | minRequiredReliability | Real | 0.999 | actualSystemReliability >= minRequiredReliability | |
| CLR-R071 | Flight Software Defect Rate | Technical | minSimulationHoursRequired | duration | 2000 | h | (actualCriticalDefectsCount <= maxCriticalDefectsAllowed) and (actualSimulationHours >= minSimulationHoursRequired) |
| CLR-R071 | Flight Software Defect Rate | Technical | maxCriticalDefectsAllowed | Integer | 0 | (actualCriticalDefectsCount <= maxCriticalDefectsAllowed) and (actualSimulationHours >= minSimulationHoursRequired) | |
| CLR-R072 | Component Acceptance Rate | Technical | maxNonConformanceRate | RatioValue | 0.1 | % | actualNonConformanceRate <= maxNonConformanceRate |
| CLR-R073 | Material Vacuum Resistance | Technical | minExposureDurationReqd | duration | 14 | d | (actualDegradationLevel <= maxDegradationLevel) and (actualExposureDuration >= minExposureDurationReqd) |
| CLR-R073 | Material Vacuum Resistance | Technical | maxDegradationLevel | RatioValue | 0 | % | (actualDegradationLevel <= maxDegradationLevel) and (actualExposureDuration >= minExposureDurationReqd) |
Traceability matrices¶
Product Traceability matrices
One matrix per specification: requirements across, the satisfying elements down; a filled cell is a
Use it to see at a glance what each element is accountable for, and spot requirements no element covers.
One matrix per specification: requirements across, the satisfying elements down; a filled cell is a
satisfy statement (darker: stated twice).Use it to see at a glance what each element is accountable for, and spot requirements no element covers.
Mission requirements × operations
Functional requirements × functions
Technical requirements × hardware and interfaces
- The technical requirements are satisfied most often by
instrumentUnit(17),commandModule(15),lunarModuleAscentStage(11),lunarModuleDescentStage(10),serviceModule(10). - 48 of 48 mission-level satisfy statements name an operation as performed in a mission phase (10 phases); 2 operations are performed in more than one phase and appear once, as one row.
Coverage and gap report¶
Product Coverage and gap report
For every level, how many requirements have a complete trace (a parent above and a refining or satisfying element below), followed by the defects that break the trace.
Use it to prioritize requirements work: what is unsatisfied, disconnected, or stated twice.
For every level, how many requirements have a complete trace (a parent above and a refining or satisfying element below), followed by the defects that break the trace.
Use it to prioritize requirements work: what is unsatisfied, disconnected, or stated twice.
complete: has a parent (needs excepted) and a child; no parent: refines nothing; no child: nothing refines or satisfies it; isolated: neither.
14 requirements are not satisfied by any element.
- Specified but without a
satisfy:CLR-R077,CLR-R104,CLR-R105 - Not used in any specification:
CLR-R055,CLR-R059,CLR-R061,CLR-R062,CLR-R063,CLR-R064,CLR-R065,CLR-R066,CLR-R070,CLR-R072,CLR-R074
| ID | Title | Level | Coverage | Statement |
|---|---|---|---|---|
| CLR-R055 | SIC Thrust Magnitude | Technical | not specified | The Apollo 11 Mission's launch vehicle's first stage propulsion shall provide a minimum thrust of 34.5 Meganewtons at liftoff. |
| CLR-R059 | Primary Structure Load Limit | Technical | not specified | All primary structural elements of the Apollo 11 Mission launch system shall withstand launch loads of up to 4 gees without permanent deformation or failure. |
| CLR-R061 | Pyrotechnic Initiation Reliability | Technical | not specified | All pyrotechnic devices (e.g., stage separation, parachute deployment) used in the Apollo 11 Mission shall have a 99.99% initiation reliability. |
| CLR-R062 | Docking Mechanism Reliability | Technical | not specified | The Apollo 11 Mission's spacecraft docking system shall enable two spacecraft to mate and form a rigid connection in lunar orbit, capable of withstanding dynamic loads during rendezvous maneuvers, with a 99.5% success rate for capture and latching. |
| CLR-R063 | LMDS Landing Gear Energy | Technical | not specified | The Apollo 11 Mission's lunar lander's landing gear shall absorb impact energy equivalent to a 3 meters per second vertical velocity and 1 meter per second horizontal velocity at touchdown without structural failure. |
| CLR-R064 | ECS Water Supply Rate | Technical | not specified | The Apollo 11 Mission's crew's potable water system shall provide a minimum of 2 kilograms of potable water per crew member per day. |
| CLR-R065 | ECS Filter Efficiency | Technical | not specified | The Apollo 11 Mission's cabin atmosphere purification system shall maintain carbon dioxide levels below 0.5% by volume and remove particulate matter >= 0.5 microns with 99% efficiency. |
| CLR-R066 | Data Handling Integrity | Technical | not specified | The Apollo 11 Mission's data acquisition system shall record and store all critical telemetry data for the entire mission duration, with no less than 99.9% data integrity. |
| CLR-R070 | Mission System Reliability | Technical | not specified | All mission-critical flight systems of the Apollo 11 Mission (e.g., primary propulsion, life support, main computer) shall demonstrate a statistical reliability of >= 0.999 (three nines) for their operational lifetimes. |
| CLR-R072 | Component Acceptance Rate | Technical | not specified | All flight components of the Apollo 11 Mission shall undergo acceptance testing to verify conformance to specifications before integration, with <= 0.1% non-conformance rate. |
| CLR-R074 | Electronic EMI Immunity | Technical | not specified | The entire Apollo 11 Mission system shall be designed to withstand the electromagnetic interference (EMI) environment of launch and space operations without functional degradation. |
| CLR-R077 | VHF Audio Bandwidth | Technical | specified, not satisfied | The cross-vehicle audio link shall operate within the 250-300 MHz range with a signal-to-noise ratio of at least 20dB. |
| CLR-R104 | Docking Latch Torque Threshold | Technical | specified, not satisfied | The LM docking latches shall require a minimum of 300 inch-pounds of torque to achieve a rigid seal. |
| CLR-R105 | Undocking Separation Velocity | Technical | specified, not satisfied | The undocking maneuver shall target a relative separation velocity of 0.1 +/- 0.05 meters per second. |
Requirements outside the refinement chain
- Isolated (no parent, nothing below):
CLR-R055,CLR-R059,CLR-R061,CLR-R062,CLR-R063,CLR-R064,CLR-R065,CLR-R066,CLR-R070,CLR-R072,CLR-R074 - No parent:
FLR-R091TGNC Navigation Accuracy - No child:
CLR-R077VHF Audio Bandwidth - No child:
CLR-R104Docking Latch Torque Threshold - No child:
CLR-R105Undocking Separation Velocity
Refinement links that skip the mission level
FLR-R092Manual Piloting Logic refines the capabilityAdaptabilityAndProblemSolvingdirectlyFLR-R094Training Simulator Hours refines the capabilityCrewTrainingAndSimulationdirectlyFLR-R093System Interface Compatibility refines the capabilityComplexLogisticsAndIntegrationdirectlyFLR-R092Manual Piloting Logic refines the capabilityHumanPerformanceUnderExtremeStressdirectly
7 satisfy statements are stated twice, word for word
CLR-R008byinstrumentUnitCLR-R024byplssCLR-R025byplssCLR-R035byplssCLR-R050bylunarModuleDescentStageHLR-R065bymonitorSpacecraftSystemsHLR-R067bymonitorSpacecraftSystems
Verification status¶
Product Verification status
What the model itself can say about each
Use it to see which requirements the model can verify today, and what is missing for the rest.
What the model itself can say about each
satisfy statement: the requirement's require constraints evaluated with the requirement's subject bound to the satisfying element.Use it to see which requirements the model can verify today, and what is missing for the rest.
0 of 272 satisfy statements can be decided from the model
- 0 statements (0 requirements) satisfy a requirement whose constraint compares an attribute that nothing binds. The threshold is in the model; the design or measured value is not.
- 227 statements satisfy a requirement stated only in prose: it has no
require constraintto evaluate. - Evaluated on their own, the 56 requirement definitions that have a constraint are 56 undetermined.
- So the
satisfyrelationships are allocations (who is responsible), not evidence: no requirement is verified by the model yet. Binding eachactual…attribute to the satisfying element's value would turn them into checks.
| ID | Level | Satisfied by | Verification | Missing value |
|---|---|---|---|---|
| HLR-R001 | Mission requirement | retrieveCrewAndCM | cannot be evaluated | `hlr-R001.crewInjuryCount` has no value |
| HLR-R002 | Mission requirement | executePoweredDescentBurn | cannot be evaluated | `hlr-R002.actualVerticalVelocity` has no value |
| HLR-R003 | Mission requirement | executeTLIBurn | cannot be evaluated | `hlr-R003.actualDeltaVAccuracy` has no value |
| HLR-R004 | Mission requirement | communicateWithMissionControl | cannot be evaluated | `hlr-R004.actualCommunicationUptimePercentage` has no value |
| HLR-R005 | Mission requirement | monitorSpacecraftSystems | no require constraint | |
| HLR-R005 | Mission requirement | monitorSpacecraftSystems | no require constraint | |
| HLR-R006 | Mission requirement | collectLunarSamples | cannot be evaluated | `hlr-R006.actualSampleMass` has no value |
| HLR-R007 | Mission requirement | deployScientificInstruments | cannot be evaluated | `hlr-R007.actualDeployedVisualSystems` has no value |
| HLR-R008 | Mission requirement | performLunarEVA | cannot be evaluated | `hlr-R008.actualStillPhotosCount` has no value |
| HLR-R009 | Mission requirement | performLunarEVA | cannot be evaluated | `hlr-R009.symbolSuccessfullyPlanted` has no value |
| HLR-R010 | Mission requirement | initiateQuarantineProcedures | cannot be evaluated | `hlr-R010.actualQuarantineLevel` has no value |
| HLR-R011 | Mission requirement | conductMidCourseCorrections | no require constraint | |
| HLR-R026 | Mission requirement | monitorSpacecraftSystems | cannot be evaluated | `hlr-R026.wasteContaminationDetected` has no value |
| HLR-R028 | Mission requirement | manageCrewRestPeriods | cannot be evaluated | `hlr-R028.actualUndisturbedSleepDuration` has no value |
| HLR-R030 | Mission requirement | monitorSpacecraftSystems | cannot be evaluated | `hlr-R030.actualAlarmResponseTime` has no value |
| HLR-R032 | Mission requirement | performLunarEVA | cannot be evaluated | `hlr-R032.actualSignalClarity` has no value |
| HLR-R033 | Mission requirement | performLunarEVA | cannot be evaluated | `hlr-R033.actualEMULifeSupportDuration` has no value |
| HLR-R035 | Mission requirement | performLunarEVA | cannot be evaluated | `hlr-R035.actualTaskCompletionSuccessRate` has no value |
| HLR-R036 | Mission requirement | performLunarEVA | cannot be evaluated | `hlr-R036.actualTraverseDistanceCapability` has no value |
| HLR-R037 | Mission requirement | performLunarEVA | cannot be evaluated | `hlr-R037.toolsMeetContactRequirement` has no value |
| HLR-R038 | Mission requirement | collectLunarSamples | cannot be evaluated | `hlr-R038.actualTerrestrialContamination` has no value |
| HLR-R040 | Mission requirement | collectLunarSamples | cannot be evaluated | `hlr-R040.actualSampleCorrelationPercentage` has no value |
| HLR-R045 | Mission requirement | executeLOIBurn | cannot be evaluated | `hlr-R045.singleFailureCausesOperationalLoss` has no value |
| HLR-R046 | Mission requirement | executeLaunchSequence | cannot be evaluated | `hlr-R046.actualAbortExecutionTime` has no value |
| HLR-R047 | Mission requirement | performManualPiloting | cannot be evaluated | `hlr-R047.actualOverrideResponseTime` has no value |
| HLR-R048 | Mission requirement | communicateWithMissionControl | cannot be evaluated | `hlr-R048.actualUpdateInterval` has no value |
| HLR-R049 | Mission requirement | executeLunarAscentBurn | cannot be evaluated | `hlr-R049.actualTimeFromLandingToAscentLaunch` has no value |
| HLR-R050 | Mission requirement | communicateWithMissionControl | cannot be evaluated | `hlr-R050.actualSoftwareUpdateDuration` has no value |
| HLR-R052 | Mission requirement | transferCrewToVehicle | cannot be evaluated | `hlr-R052.medicalProficiencyScore` has no value |
| HLR-R053 | Mission requirement | conductLMCSMDocking | cannot be evaluated | `hlr-R053.actualProcedureErrorRate` has no value |
| HLR-R054 | Mission requirement | manageCrewRestPeriods | cannot be evaluated | `hlr-R054.significantGIIssuesExperienced` has no value |
| HLR-R055 | Mission requirement | manageCrewRestPeriods | cannot be evaluated | `hlr-R055.actualPsychologicalStateScore` has no value |
| HLR-R057 | Mission requirement | monitorSpacecraftSystems | cannot be evaluated | `hlr-R057.actualPenetrationProbabilityPerMission` has no value |
| HLR-R059 | Mission requirement | deployScientificInstruments | cannot be evaluated | `hlr-R059.structuralIntegrityMaintained` has no value |
| HLR-R060 | Mission requirement | recoveryQuarantineOperations | cannot be evaluated | `hlr-R060.actualDataAvailabilityPercentage` has no value |
| HLR-R061 | Mission requirement | executeLOIBurn | no require constraint | |
| HLR-R062 | Mission requirement | executeLaunchSequence | no require constraint | |
| HLR-R063 | Mission requirement | communicateWithMissionControl | no require constraint | |
| HLR-R063 | Mission requirement | communicateWithMissionControl | no require constraint | |
| HLR-R064 | Mission requirement | deployScientificInstruments | no require constraint | |
| HLR-R065 | Mission requirement | monitorSpacecraftSystems | no require constraint | |
| HLR-R065 | Mission requirement | monitorSpacecraftSystems | no require constraint | |
| HLR-R066 | Mission requirement | communicateWithMissionControl | no require constraint | |
| HLR-R066 | Mission requirement | communicateWithMissionControl | no require constraint | |
| HLR-R067 | Mission requirement | monitorSpacecraftSystems | no require constraint | |
| HLR-R067 | Mission requirement | monitorSpacecraftSystems | no require constraint | |
| HLR-R068 | Mission requirement | performPreLaunchCountdown | no require constraint | |
| HLR-R069 | Mission requirement | performManualPiloting | no require constraint | |
| FLR-R001 | Functional requirement | load | no require constraint | |
| FLR-R002 | Functional requirement | load | no require constraint | |
| FLR-R003 | Functional requirement | board | no require constraint | |
| FLR-R004 | Functional requirement | board | no require constraint | |
| FLR-R005 | Functional requirement | countdown | no require constraint | |
| FLR-R006 | Functional requirement | countdown | no require constraint | |
| FLR-R007 | Functional requirement | provideThrust1 | no require constraint | |
| FLR-R008 | Functional requirement | provideThrust1 | no require constraint | |
| FLR-R009 | Functional requirement | provideThrust2 | no require constraint | |
| FLR-R010 | Functional requirement | provideThrust2 | no require constraint | |
| FLR-R011 | Functional requirement | provideThrust3 | no require constraint | |
| FLR-R012 | Functional requirement | provideThrust3 | no require constraint | |
| FLR-R013 | Functional requirement | guide | no require constraint | |
| FLR-R014 | Functional requirement | guide | no require constraint | |
| FLR-R015 | Functional requirement | observe | no require constraint | |
| FLR-R016 | Functional requirement | observe | no require constraint | |
| FLR-R017 | Functional requirement | analyze | no require constraint | |
| FLR-R018 | Functional requirement | analyze | no require constraint | |
| FLR-R019 | Functional requirement | burn | no require constraint | |
| FLR-R020 | Functional requirement | control | no require constraint | |
| FLR-R021 | Functional requirement | executeTransposition | no require constraint | |
| FLR-R022 | Functional requirement | executeTransposition | no require constraint | |
| FLR-R023 | Functional requirement | reconfigure | no require constraint | |
| FLR-R024 | Functional requirement | burn | no require constraint | |
| FLR-R025 | Functional requirement | provideAttitudeControlAndThrust | no require constraint | |
| FLR-R026 | Functional requirement | trackAndRelay | no require constraint | |
| FLR-R027 | Functional requirement | calculate | no require constraint | |
| FLR-R028 | Functional requirement | calculate | no require constraint | |
| FLR-R029 | Functional requirement | correct | no require constraint | |
| FLR-R030 | Functional requirement | monitorOnboard | no require constraint | |
| FLR-R031 | Functional requirement | monitorGround | no require constraint | |
| FLR-R032 | Functional requirement | comms | no require constraint | |
| FLR-R033 | Functional requirement | comms | no require constraint | |
| FLR-R034 | Functional requirement | trackAndRelay | no require constraint | |
| FLR-R035 | Functional requirement | trackAndRelay | no require constraint | |
| FLR-R036 | Functional requirement | rest | no require constraint | |
| FLR-R037 | Functional requirement | rest | no require constraint | |
| FLR-R038 | Functional requirement | burn | no require constraint | |
| FLR-R039 | Functional requirement | control | no require constraint | |
| FLR-R040 | Functional requirement | checkout | no require constraint | |
| FLR-R041 | Functional requirement | checkout | no require constraint | |
| FLR-R042 | Functional requirement | prep | no require constraint | |
| FLR-R043 | Functional requirement | prep | no require constraint | |
| FLR-R044 | Functional requirement | undock | no require constraint | |
| FLR-R045 | Functional requirement | undock | no require constraint | |
| FLR-R046 | Functional requirement | burn | no require constraint | |
| FLR-R047 | Functional requirement | monitor | no require constraint | |
| FLR-R048 | Functional requirement | monitor | no require constraint | |
| FLR-R049 | Functional requirement | pilot | no require constraint | |
| FLR-R050 | Functional requirement | pilot | no require constraint | |
| FLR-R051 | Functional requirement | postLand | no require constraint | |
| FLR-R052 | Functional requirement | postLand | no require constraint | |
| FLR-R053 | Functional requirement | prepEva | no require constraint | |
| FLR-R054 | Functional requirement | prepEva | no require constraint | |
| FLR-R055 | Functional requirement | eva | no require constraint | |
| FLR-R056 | Functional requirement | eva | no require constraint | |
| FLR-R057 | Functional requirement | collect | no require constraint | |
| FLR-R058 | Functional requirement | collect | no require constraint | |
| FLR-R059 | Functional requirement | deploy | no require constraint | |
| FLR-R060 | Functional requirement | deploy | no require constraint | |
| FLR-R061 | Functional requirement | conclude | no require constraint | |
| FLR-R062 | Functional requirement | conclude | no require constraint | |
| FLR-R063 | Functional requirement | rest | no require constraint | |
| FLR-R064 | Functional requirement | rest | no require constraint | |
| FLR-R065 | Functional requirement | ascend | no require constraint | |
| FLR-R066 | Functional requirement | ascend | no require constraint | |
| FLR-R067 | Functional requirement | calculate | no require constraint | |
| FLR-R068 | Functional requirement | rendezvous | no require constraint | |
| FLR-R069 | Functional requirement | dock | no require constraint | |
| FLR-R070 | Functional requirement | dock | no require constraint | |
| FLR-R071 | Functional requirement | transfer | no require constraint | |
| FLR-R072 | Functional requirement | transfer | no require constraint | |
| FLR-R073 | Functional requirement | jettison | no require constraint | |
| FLR-R074 | Functional requirement | jettison | no require constraint | |
| FLR-R075 | Functional requirement | burn | no require constraint | |
| FLR-R076 | Functional requirement | prep | no require constraint | |
| FLR-R077 | Functional requirement | separate | no require constraint | |
| FLR-R078 | Functional requirement | separate | no require constraint | |
| FLR-R079 | Functional requirement | guide | no require constraint | |
| FLR-R080 | Functional requirement | guide | no require constraint | |
| FLR-R081 | Functional requirement | deploy | no require constraint | |
| FLR-R082 | Functional requirement | deploy | no require constraint | |
| FLR-R083 | Functional requirement | splashdown | no require constraint | |
| FLR-R084 | Functional requirement | splashdown | no require constraint | |
| FLR-R085 | Functional requirement | retrieve | no require constraint | |
| FLR-R086 | Functional requirement | retrieve | no require constraint | |
| FLR-R087 | Functional requirement | quarantine | no require constraint | |
| FLR-R088 | Functional requirement | quarantine | no require constraint | |
| FLR-R089 | Functional requirement | secure | no require constraint | |
| FLR-R090 | Functional requirement | secure | no require constraint | |
| FLR-R091 | Functional requirement | trackAndRelay | no require constraint | |
| FLR-R092 | Functional requirement | pilot | no require constraint | |
| FLR-R093 | Functional requirement | load | no require constraint | |
| FLR-R094 | Functional requirement | board | no require constraint | |
| FLR-R095 | Functional requirement | correct | no require constraint | |
| FLR-R096 | Functional requirement | provideAttitudeControlAndThrust | no require constraint | |
| FLR-R097 | Functional requirement | monitor | no require constraint | |
| FLR-R098 | Functional requirement | provideThrust1 | no require constraint | |
| FLR-R099 | Functional requirement | burn | no require constraint | |
| FLR-R100 | Functional requirement | guide | no require constraint | |
| FLR-R101 | Functional requirement | burn | no require constraint | |
| FLR-R102 | Functional requirement | monitorOnboard | no require constraint | |
| FLR-R103 | Functional requirement | comms | no require constraint | |
| FLR-R104 | Functional requirement | eva | no require constraint | |
| FLR-R105 | Functional requirement | guide | no require constraint | |
| FLR-R106 | Functional requirement | monitorOnboard | no require constraint | |
| FLR-R107 | Functional requirement | deploy | no require constraint | |
| FLR-R108 | Functional requirement | monitorOnboard | no require constraint | |
| FLR-R109 | Functional requirement | eva | no require constraint | |
| FLR-R110 | Functional requirement | burn | no require constraint | |
| FLR-R111 | Functional requirement | rest | no require constraint | |
| FLR-R112 | Functional requirement | retrieve | no require constraint | |
| CLR-R001 | Technical requirement | stage1 | no require constraint | |
| CLR-R002 | Technical requirement | stage1 | no require constraint | |
| CLR-R003 | Technical requirement | stage1 | no require constraint | |
| CLR-R004 | Technical requirement | stage2 | no require constraint | |
| CLR-R005 | Technical requirement | stage2 | no require constraint | |
| CLR-R006 | Technical requirement | stage3 | no require constraint | |
| CLR-R007 | Technical requirement | stage3 | no require constraint | |
| CLR-R008 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R008 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R009 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R010 | Technical requirement | launchEscapeSystem | no require constraint | |
| CLR-R011 | Technical requirement | launchEscapeSystem | no require constraint | |
| CLR-R012 | Technical requirement | commandModule | no require constraint | |
| CLR-R013 | Technical requirement | commandModule | no require constraint | |
| CLR-R014 | Technical requirement | commandModule | no require constraint | |
| CLR-R015 | Technical requirement | serviceModule | no require constraint | |
| CLR-R016 | Technical requirement | serviceModule | no require constraint | |
| CLR-R017 | Technical requirement | serviceModule | no require constraint | |
| CLR-R018 | Technical requirement | lunarModuleDescentStage | no require constraint | |
| CLR-R019 | Technical requirement | lunarModuleDescentStage | no require constraint | |
| CLR-R020 | Technical requirement | lunarModuleAscentStage | no require constraint | |
| CLR-R021 | Technical requirement | lunarModuleAscentStage | no require constraint | |
| CLR-R022 | Technical requirement | psa | no require constraint | |
| CLR-R023 | Technical requirement | psa | no require constraint | |
| CLR-R024 | Technical requirement | plss | no require constraint | |
| CLR-R024 | Technical requirement | plss | no require constraint | |
| CLR-R025 | Technical requirement | plss | no require constraint | |
| CLR-R025 | Technical requirement | plss | no require constraint | |
| CLR-R026 | Technical requirement | stage1 | no require constraint | |
| CLR-R027 | Technical requirement | stage2 | no require constraint | |
| CLR-R028 | Technical requirement | stage3 | no require constraint | |
| CLR-R029 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R030 | Technical requirement | commandModule | no require constraint | |
| CLR-R031 | Technical requirement | serviceModule | no require constraint | |
| CLR-R032 | Technical requirement | lunarModuleDescentStage | no require constraint | |
| CLR-R033 | Technical requirement | lunarModuleAscentStage | no require constraint | |
| CLR-R034 | Technical requirement | psa | no require constraint | |
| CLR-R035 | Technical requirement | plss | no require constraint | |
| CLR-R035 | Technical requirement | plss | no require constraint | |
| CLR-R036 | Technical requirement | stage1ToStage2 | no require constraint | |
| CLR-R036 | Technical requirement | stage2ToStage3 | no require constraint | |
| CLR-R037 | Technical requirement | stage2ToStage3 | no require constraint | |
| CLR-R037 | Technical requirement | stage1ToStage2 | no require constraint | |
| CLR-R038 | Technical requirement | iuToStage3 | no require constraint | |
| CLR-R039 | Technical requirement | iuToStage3 | no require constraint | |
| CLR-R040 | Technical requirement | cmSMUmbilical | no require constraint | |
| CLR-R041 | Technical requirement | cmSMUmbilical | no require constraint | |
| CLR-R042 | Technical requirement | cmLMDocking | no require constraint | |
| CLR-R043 | Technical requirement | cmLMDocking | no require constraint | |
| CLR-R044 | Technical requirement | lmInterstage | no require constraint | |
| CLR-R045 | Technical requirement | suitToPLSSUmbilical | no require constraint | |
| CLR-R046 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R046 | Technical requirement | spacecraftLMAdapter | no require constraint | |
| CLR-R047 | Technical requirement | spacecraftLMAdapter | no require constraint | |
| CLR-R048 | Technical requirement | lesConnection | no require constraint | |
| CLR-R049 | Technical requirement | lesConnection | no require constraint | |
| CLR-R050 | Technical requirement | lunarModuleDescentStage | no require constraint | |
| CLR-R050 | Technical requirement | lunarModuleDescentStage | no require constraint | |
| CLR-R051 | Technical requirement | commandModule | cannot be evaluated | `clr-R051.actualCabinTemperatureMin` has no value |
| CLR-R052 | Technical requirement | instrumentUnit | cannot be evaluated | `clr-R052.actualDeltaVcalcAccuracy` has no value |
| CLR-R053 | Technical requirement | serviceModule | cannot be evaluated | `clr-R053.actualAttitudeDeviation` has no value |
| CLR-R054 | Technical requirement | lunarModuleDescentStage | cannot be evaluated | `clr-R054.actualAltitudeAccuracy` has no value |
| CLR-R056 | Technical requirement | serviceModule | cannot be evaluated | `clr-R056.actualMajorBurnCount` has no value |
| CLR-R057 | Technical requirement | lunarModuleDescentStage | cannot be evaluated | `clr-R057.actualMinThrottlePercentage` has no value |
| CLR-R058 | Technical requirement | lunarModuleAscentStage | cannot be evaluated | `clr-R058.actualAscentBurnDuration` has no value |
| CLR-R060 | Technical requirement | commandModule | cannot be evaluated | `clr-R060.actualInternalTemperatureRise` has no value |
| CLR-R067 | Technical requirement | lunarModuleAscentStage | cannot be evaluated | `clr-R067.actualVideoWidth` has no value |
| CLR-R068 | Technical requirement | psa | cannot be evaluated | `clr-R068.actualPressureLossRate` has no value |
| CLR-R069 | Technical requirement | lunarModuleDescentStage | cannot be evaluated | `clr-R069.actualOperationalDuration` has no value |
| CLR-R071 | Technical requirement | instrumentUnit | cannot be evaluated | `clr-R071.actualCriticalDefectsCount` has no value |
| CLR-R073 | Technical requirement | serviceModule | cannot be evaluated | `clr-R073.actualDegradationLevel` has no value |
| CLR-R075 | Technical requirement | commandModule | no require constraint | |
| CLR-R076 | Technical requirement | commandModule | no require constraint | |
| CLR-R078 | Technical requirement | serviceModule | no require constraint | |
| CLR-R079 | Technical requirement | commandModule | no require constraint | |
| CLR-R080 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R081 | Technical requirement | commandModule | no require constraint | |
| CLR-R082 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R083 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R084 | Technical requirement | commandModule | no require constraint | |
| CLR-R085 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R086 | Technical requirement | stage1 | no require constraint | |
| CLR-R087 | Technical requirement | stage2 | no require constraint | |
| CLR-R088 | Technical requirement | stage3 | no require constraint | |
| CLR-R089 | Technical requirement | commandModule | no require constraint | |
| CLR-R090 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R091 | Technical requirement | stage3 | no require constraint | |
| CLR-R092 | Technical requirement | spacecraftLMAdapter | no require constraint | |
| CLR-R093 | Technical requirement | serviceModule | no require constraint | |
| CLR-R094 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R095 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R096 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R097 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R098 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R099 | Technical requirement | commandModule | no require constraint | |
| CLR-R100 | Technical requirement | commandModule | no require constraint | |
| CLR-R101 | Technical requirement | serviceModule | no require constraint | |
| CLR-R102 | Technical requirement | lunarModuleAscentStage | no require constraint | |
| CLR-R103 | Technical requirement | lunarModuleAscentStage | no require constraint | |
| CLR-R106 | Technical requirement | lunarModuleAscentStage | no require constraint | |
| CLR-R107 | Technical requirement | lunarModuleDescentStage | no require constraint | |
| CLR-R108 | Technical requirement | lunarModuleDescentStage | no require constraint | |
| CLR-R109 | Technical requirement | lunarModuleAscentStage | no require constraint | |
| CLR-R110 | Technical requirement | psa | no require constraint | |
| CLR-R111 | Technical requirement | psa | no require constraint | |
| CLR-R112 | Technical requirement | lunarModuleDescentStage | no require constraint | |
| CLR-R113 | Technical requirement | cmLMDocking | no require constraint | |
| CLR-R113 | Technical requirement | psa | no require constraint | |
| CLR-R114 | Technical requirement | instrumentUnit | no require constraint | |
| CLR-R115 | Technical requirement | lunarModuleAscentStage | no require constraint | |
| CLR-R116 | Technical requirement | lunarModuleAscentStage | no require constraint | |
| CLR-R117 | Technical requirement | commandModule | no require constraint |
End-to-end trace¶
Product End-to-end trace
One stakeholder need, SHN-N005 Scientific Return, followed down through the capability, mission, functional and technical requirements that refine it, to the hardware that satisfies them.
Use it to show reviewers how a top-level need is carried into the design, and which components it depends on.
One stakeholder need, SHN-N005 Scientific Return, followed down through the capability, mission, functional and technical requirements that refine it, to the hardware that satisfies them.
Use it to show reviewers how a top-level need is carried into the design, and which components it depends on.
flowchart TD nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EasepThermalInsulation["CLR-R112 Easep Thermal Insulation"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__SampleToolMechanicalAdvantage["CLR-R111 Sample Tool Mechanical Advantage"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__LunarVisualDocumentationRequirement["HLR-R008 Lunar Visual Documentation Requirement"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__VisualDataCapture["FLR-R107 Visual Data Capture"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__ScientificInstrumentDeploymentRequirement["HLR-R007 Scientific Instrument Deployment Requirement"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__LunarSampleCollectionQuantityRequirement["HLR-R006 Lunar Sample Collection Quantity Requirement"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EMUPressureContainment["CLR-R068 EMU Pressure Containment"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__ImageResolutionStandard["CLR-R075 Image Resolution Standard"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__InstrumentDeploymentRequirement["FLR-R059 Instrument Deployment Requirement"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__ExtendedScientificOperation["HLR-R064 Extended Scientific Operation"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Purpose_CapabilitiesPackage_sysml_CapabilitiesPackage__ScientificDataAcquisitionAndSampleReturn["Scientific Data Acquisition And Sample Return"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__EMUPressureMaintenance["FLR-R104 EMU Pressure Maintenance"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_StakeholderNeedsPackage_sysml_StakeholderNeedsPackage__ScientificReturn(["SHN-N005 Scientific Return"]) nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EASEPOperationalDuration["CLR-R069 EASEP Operational Duration"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__SampleCollectionRequirement["FLR-R057 Sample Collection Requirement"] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Purpose_CapabilitiesPackage_sysml_CapabilitiesPackage__ScientificDataAcquisitionAndSampleReturn --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__ExtendedScientificOperation nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Purpose_CapabilitiesPackage_sysml_CapabilitiesPackage__ScientificDataAcquisitionAndSampleReturn --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__LunarSampleCollectionQuantityRequirement nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Purpose_CapabilitiesPackage_sysml_CapabilitiesPackage__ScientificDataAcquisitionAndSampleReturn --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__LunarVisualDocumentationRequirement nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Purpose_CapabilitiesPackage_sysml_CapabilitiesPackage__ScientificDataAcquisitionAndSampleReturn --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__ScientificInstrumentDeploymentRequirement nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__LunarVisualDocumentationRequirement --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__VisualDataCapture nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_StakeholderNeedsPackage_sysml_StakeholderNeedsPackage__ScientificReturn --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Purpose_CapabilitiesPackage_sysml_CapabilitiesPackage__ScientificDataAcquisitionAndSampleReturn nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__EMUPressureMaintenance --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EMUPressureContainment nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__ExtendedScientificOperation --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__EMUPressureMaintenance nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__VisualDataCapture --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__ImageResolutionStandard nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__ScientificInstrumentDeploymentRequirement --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__InstrumentDeploymentRequirement nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__LunarSampleCollectionQuantityRequirement --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__SampleCollectionRequirement nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__InstrumentDeploymentRequirement --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EasepThermalInsulation nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__InstrumentDeploymentRequirement --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EASEPOperationalDuration nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__SampleCollectionRequirement --> nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__SampleToolMechanicalAdvantage nhw_lunarModuleDescentStage[/"lunarModuleDescentStage : Lunar Module Descent Stage"/] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EasepThermalInsulation -. satisfied by .-> nhw_lunarModuleDescentStage nhw_lunarModuleDescentStage[/"lunarModuleDescentStage : Lunar Module Descent Stage"/] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EASEPOperationalDuration -. satisfied by .-> nhw_lunarModuleDescentStage nhw_commandModule[/"commandModule : Apollo Command Module"/] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__ImageResolutionStandard -. satisfied by .-> nhw_commandModule nhw_psa[/"psa : Pressure Suite Assembly"/] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EMUPressureContainment -. satisfied by .-> nhw_psa nhw_psa[/"psa : Pressure Suite Assembly"/] nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__SampleToolMechanicalAdvantage -. satisfied by .-> nhw_psa classDef c0 fill:#2a78d6,color:#ffffff,stroke:none class nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_StakeholderNeedsPackage_sysml_StakeholderNeedsPackage__ScientificReturn c0 classDef c1 fill:#eb6834,color:#0b0b0b,stroke:none class nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Purpose_CapabilitiesPackage_sysml_CapabilitiesPackage__ScientificDataAcquisitionAndSampleReturn c1 classDef c2 fill:#1baf7a,color:#0b0b0b,stroke:none class nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__LunarVisualDocumentationRequirement,nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__ScientificInstrumentDeploymentRequirement,nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__LunarSampleCollectionQuantityRequirement,nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_MissionRequirementsPackage_sysml_MissionRequirementsPackage__ExtendedScientificOperation c2 classDef c3 fill:#eda100,color:#0b0b0b,stroke:none class nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__VisualDataCapture,nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__InstrumentDeploymentRequirement,nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__EMUPressureMaintenance,nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_FunctionalRequirementsPackage_sysml_FunctionalRequirementsPackage__SampleCollectionRequirement c3 classDef c4 fill:#e87ba4,color:#0b0b0b,stroke:none class nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EasepThermalInsulation,nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__SampleToolMechanicalAdvantage,nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EMUPressureContainment,nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__ImageResolutionStandard,nfile____home_runner_work_apollo_11_sysml_v2_apollo_11_sysml_v2_Requirements_TechnicalRequirementsPackage_sysml_TechnicalRequirementsPackage__EASEPOperationalDuration c4
The mission shall yield significant scientific data, primarily through the return of lunar samples.
The need is carried by 1 capability, 7 mission, 8 functional and 5 technical requirements; the diagram keeps the paths that end in hardware: commandModule, lunarModuleDescentStage, psa. The operations and functions that satisfy the upper levels are in the concept of operations and the functional architecture; the hardware in the physical architecture.