NASA-STD-3001 Technical Brief

Relevant Technical 

Requirements

Apollo Lunar Lander 

Module Design: Medical 

& Human Performance 

Perspective

OCHMO-TB-022

Rev B

NASA-STD-3001Volume 1, Rev C

[V1 3000] Medical Management

[V1 3003] In-Mission Preventive HealthCare 

[V1 3004] In-Mission MedicalCare

[V1 3006] Crew Medical Officers Quantity 

[V1 3007] Medical Evacuation

[V1 3008] In-Mission Evacuation toDefinitive 

Medical Care Facilities

[V1 3009] Palliative ComfortCare 

[V1 3010] Termination ofCare

[V1 3053] Crew Mortality Remains 

Return to Earth 

[V1 3054] In Situ Disposition of 

Deceased Crewmember Remains 

[V1 5009] Physiological Exposure 

Mission Training

[V1 6006] Extravehicular Activities 

(EVAs)

NASA-STD-3001Volume 2, Rev D

[V2 6002] Inert Diluent Gas

[V2 6003] O2 Partial Pressure Range forCrew 

Exposure

[V2 6004] Nominal Vehicle/HabitatCarbon 

Dioxide Levels

[V2 6006] Total Pressure Tolerance Rangefor 

Indefinite Crew Exposure

[V2 6007] Rate of PressureChange 

[V2 6150] BarotraumaPrevention

[V2 6008] Decompression Sickness (DCS)Risk 

Identification

[V2 6009] DecompressionSickness 

Treatment Capability

Executive Summary

As NASA plans to return to the 

moon during the Artemis missions, 

important lessons can be drawn 

from the Apollo missions of the

‘60s and ‘70s. The Apollo Lunar 

Module (LM) successfully 

supported lunar descent, landing, 

EVA operations, all necessary crew 

functions for the duration of the 

mission and ascent from the 

surface. Using it as a starting point 

for reference can save time and 

resources for new designs, as well 

as provide the opportunity to 

address past issues.
NASA-STD-3001 Technical Brief 

OCHMO-TB-022

Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Executive Summary (continued)

NASA Astronaut Buzz Aldrin and theApollo

11 Lunar Module

Relevant Technical

Requirements

NASA-STD-3001Volume 2, Rev D

[V2 6053] Lunar Dust Contamination

[V2 6064] Sustained Translational

Acceleration Limits

[V2 6065] RotationalVelocity

[V2 6066] Sustained Rotational Acceleration 

Due to Cross-CoupledRotation

[V2 6067] Transient RotationalAcceleration 

[V2 6069] Acceleration Injury Prevention 

[V2 6070] Injury Risk Criterion

[V2 6111] Dynamic MissionPhases 

Monitoring and Analysis

[V2 7016] Personal Hygiene Capability 

[V2 7020] Body WasteManagement

Capability

[V2 7026] Body Waste Odor 

[V2 7050] StowageProvisions

[V2 7053] Stowage Interference 

[V2 7064] Trash Accommodation 

[V2 8001] Volume Allocation

[V2 8005] FunctionalArrangement 

[V2 8006] Interference

[V2 8007] Spatial and Interface Orientation 

[V2 8013] Intravehicular Translation Paths 

[V2 8027] Hatchway Size and Shape

[V2 8033] Restraints for Crew Tasks 

[V2 8038] Restraint and MobilityAid

Standardization

[V2 8040] Mobility Aid for Assisted Ingress 

and Egress

[V2 8041] Unassisted Ingress, Egress,and 

Escape MobilityAids

[V2 8042] Mobility Aid Provision

[V2 10002] Design-Induced Error 

[V2 10003] Operability

[V2 11001] Suited Donning andDoffing

[V2 11005] EVA Translation PathHazard 

Avoidance

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

11/28/2023

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NASA-STD-3001 Technical Brief 

OCHMO-TB-022

Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Background

Lunar ModuleDetails

• Mass (fully loaded): 16,375 

kilograms (kg)

• Mass of crew and supplies:

o Crew: 2x75 kg

o Suits: 2x82 kg

o Food: 0.77 kg per 

man per day

o Water: 580 kg (Apollo

11)

• Pressurized volume: 6.65 

cubic meters (cu. m)

• Habitable volume: 4.53 cu. m

• Atmosphere: 100% O2 at 4.8 

pounds per square inch(psi)

• Carbon Dioxide: 7.6 

millimeters mercury (mmHg)

• Crew Size: 2 crewmembers

Over the course of the Apollo program, the original LM supported the Apollo 11, 12, and 14 

lunar missions, allowing crew to stay on the surface of the Moon for 21-33 hours in total, 

with 1-2 surface EVAs totaling 2-9 hours. The LM served as an improvised “lifeboat” during 

the abortive Apollo 13, sustaining 3 crew for 4 days with some modifications (three times 

the man-days intended for the LM).

After Apollo 14, the LM underwent slight design changes. The Extended Lunar Module 

(ELM) was modified with more powerful descent thrust and an additional waste storage 

tank. It allowed for longer lunar stays during the Apollo 15,16, and 17 missions (67-75 hours 

on the lunar surface, with 3-4 surface EVAs totaling 14-22 hours).

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

3 11/28/2023

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Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Background

Features and Accommodations

• Sleep: The crew slung hammocks 

perpendicularly to sleep (shown right) and 

stowed them during normal activities.

• Body Waste: The Apollo LM had no installed 

toilet or designated toilet area. The crew 

used urine and fecal collection bags (shown 

below). To reduce mass and risk of 

contamination, all body waste was left on the 

surface of the moon before ascent.

• Water: Most water was stored in a tank in 

the descent stage for use on the moon. Some 

water was stored in the ascent stage for use 

during the ascent phase. Both tanks were 

accessed via the same water gun nozzle. Hot 

water was not available during lunarstays.

• Food: Food was freeze-dried, vacuum sealed, 

and stored in the cabin. Astronauts pumped 

water into the food packs and palpated them 

to rehydrate the food before consumption.

Urine collectiondevice

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

4

Fecal collectionassembly

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Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Background

Features and Accommodations

• Navigation/Windows: While controlling the LM’s ascent and descent, the crew stood

at the console, which granted them excellent visibility out the windows. This allowed

the windowsto be smaller, which reduced overall mass and complexity of the LM

• Crew Restraint System: During lunar ascent/descent and docking/undocking with the 

command module (CM), the crew of the LM were strapped in the restraint assembly 

(shown below). It applied a constant 30 pounds of downward force to stabilize the 

crew and keep them at the controls. Adjustable Armrests and handgrips were also 

utilized to maintain posture during descent and ascent.

• Depressurization Operations: The LM didn’t feature an airlock, so the entire cabin was 

depressurized prior to lunar EVAs. As such, every piece of equipment had to withstand 

being in a vacuum. Food packs were vacuum-sealed, and were able to survive 

depressurization operations. Medication packaging also had to accommodate the 

lower pressure and decompression.

Design Considerations: If the crew is standing during ascent/descent, orthostatic intolerance (fainting 

due to transition from mg to descent acceleration profile) needs to be considered. Packaging, 

including food and medications, need to consider expected pressurechanges.

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

5 11/28/2023

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Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Background

Features and Accommodations

• Ladder: The LM ladder (shown right) had 

a 9-inch spacing between rungs. This may 

have been too narrow; footage from the 

Apollo missions shows astronauts 

occasionally missing a rung when climbing 

the ladder. The bottom of the ladder was 

30 inches from the footpad to account for 

the collapsible landing gear and unknown 

depth/softness of the lunar surface. The 

large gap added an additional challenge 

for astronauts climbing in and out of the 

LM.

• Radiation Countermeasures: The Apollo 

missions occurred during periods of high 

solar activity, which increased exposure to 

solar particle events (SPEs) but reduced 

exposure to galactic cosmic rays (GCRs). 

The LM and EVA suits provided negligible 

shielding against GCRs; astronauts were 

equipped with a variety of personal and 

handheld radiation meters for the 

duration of the missions (shown below).

Exterior of the LM, showing the ladder

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

6 11/28/2023

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NASA-STD-3001 Technical Brief 

OCHMO-TB-022

Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Background

Features and Accommodations

• Hatches: The LM featured two hatches. The forward hatch was located below the lower display 

panels (indicated below) and was used as the means of ingress/egress for lunar and inflight EVAs. It 

was approximately 32”x32” and swung inward. It had to be large enough to fit a crewmember 

wearing an EVA suit. The overhead hatch allowed crew and equipment to transfer between the LM 

and the CM while they were docked. It was located in the top of the LM, was roughly 33” in diameter, 

and also swung inward.

• Stowage: Approximately 30% of the total pressurized volume in the LM was dedicated to stowage. 

Locations of cabinets and shelves are shown in more detail on page 9. Additional storage for EVA 

equipment was located on the exterior of the descent stage, for use and access during EVAs.

• Crew Activities: Given the small habitable volume in the LM, there were no designated areas 

for any specific crew activity (besides sleep). Eating, suit donning/doffing, sample analysis, and 

all other tasks were performed in the same area.

Forward hatch

Windows for 

viewing during 

landing

Docking 

window

Windows 

shades

The interior of the LM, showing the command console

Design Considerations: Hatches must accommodate the passage of crewmembers and equipment. 

Stowage areas must be capable of storing all necessary equipment needed for the mission and any 

samples collected. Habitable volume must support all activities required of the crew.

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

7 11/28/2023

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Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

• The Apollo CM carried a small medical kit in the spacecraft's 

lower equipment bay. It contained oral drugs and pills (for 

pain, motion sickness, and diarrhea; as well as stimulants, 

antibiotics, decongestants, and aspirin), injectable drugs (for 

pain and motion sickness), bandages, topical agents (first aid 

cream, sun cream, and an antibiotic ointment), and eye drops.

• Pills and tablets in the medical kit were packaged so that the 

crew had easy access to the medication at all times. The pills 

were sealed individually in strips of 12 or 24 cells. Pressurerelated problems in medication packaging were resolved by 

puncturing each cell with a small pin; the hole made it 

possible for the air to vent when under reduced-pressure 

conditions (the medical supplies would have been packaged at 

standard sea level pressures, but while in space the Apollo CM 

was pressurized to 5 psi).

Lunar Module

• The LM contained a smaller medical kit.

• The kit was located in the left-hand midsection, readily 

accessible to both crewmembers.

• Size 19.1 × 14 × 3.8cm (7 1/2 × 5 1/2 × 1 1/2 in.).

Background

Apollo Medical Kits

Command Module

Design Considerations: Kits need to be easily accessible and packaging needs to withstand 

pressure changes and account for longer duration missions on the Lunarsurface.

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

8

CM medical kit was made of Betacloth and 

measured approximately 7" x 5" x 5.

Apollo medicalkit

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Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Background

Atmosphere – Carbon Dioxide (CO2)

Carbon Dioxide Apollo Requirement: Carbon dioxide (CO2) removal by lithium hydroxide (LiOH) absorption 

and limited to a partial pressure of 1013 N/m2 (7.6mmHg).

Lunar Module LiOH Circular Canister

• Two used for LM - The primary canister contains a LM cartridge with a capacity of 41 man-hours; the 

secondary canister, a Personal Life Support System(PLSS) cartridge with a capacity of 14 man-hours

• Approximately 13 poundseach

• Contaminant Control Assembly - This assembly contains an expendable LiOH and charcoal cartridge 

that filtersforeign particles and removes carbon dioxide and odorsfrom the oxygen ventilation loop

• CO2 partial pressure in atmosphere delivered to astronauts - 6.75 mmHgmax

CM LiOH Square Canister

• Two were used at a time, they were alternately changed every 12hours

• A total of 30 canisters were taken for the typical lunarflight

• Approximately 8 poundseach

• Dimensions: 18.4 x 13.3 x 18.4cm, (7 1/4 x 5 1/4 x 7 1/4 in.,13/16lb.)

• Flight measurements indicated that CO2partial pressure seldom rose above 

400N/m2 (3 mmHg)

• For three-man operations, the elementswere changed every 24 hours, but 

the replacement times were staggered every 12 hours to reducethe

2 variation in CO partial pressurelevels

Design Considerations: The updated NASA-STD-3001 Volume 2 Rev C requirement for one-hour 

partial pressure CO2 levels is limited to 3 mmHg. There are also standards to minimize having 

different size/shapes devices/filters to minimize ease of use (reduce time/training) and redundancy 

(refer to Apollo 13 mishap).

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

9

Locationof 

LM CO2

Removal 

Canisters

LM CO2

Removal 

Canister

CM CO 2Removal Canister

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NASA-STD-3001 Technical Brief 

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Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Background

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

10 11/28/2023

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NASA-STD-3001 Technical Brief 

OCHMO-TB-022

Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Back-Up

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

11 11/28/2023

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NASA-STD-3001 Technical Brief 

OCHMO-TB-022

Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Major Changes Between Revisions

Rev A  Rev B

• Updated information to reflect the revisions to language 

throughout both volumes of NASA-STD-3001.

• Updated/added website links due to new NASA website 

launch

Original  Rev A

• Updated information to be consistent with NASA-STD-3001

Volume 1 Rev B and Volume 2 Rev C.

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

12 11/28/2023

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NASA-STD-3001 Technical Brief 

OCHMO-TB-022

Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Referenced Technical Requirements

NASA-STD-3001 Volume 1 Revision C

[V1 3000] Medical Management All terrestrial and in-mission medical aspects included in this NASA 

Technical Standard shall be in accordance with current U.S. and appropriate partners medical care 

standards, with limitations as imposed by mission constraints, and managed by the Flight Medicine 

team, which includes, but is not limited to: the Flight Medicine Clinic, Flight Surgeon, Deputy Flight 

Surgeon, and their designees, including the in-mission medical care providers (Crew Medical Officers). 

[V1 3003] In-Mission Preventive Health Care All programs shall provide training, in-mission capabilities, 

and resources to monitor physiological and psychosocial well-being and enable delivery of in-mission 

preventive health care, based on epidemiological evidence-based probabilistic risk assessment (PRA), 

individual crewmember needs, clinical practice guidelines, flight surgeon expertise, historical review, 

mission parameters, and vehicle-derived limitations. These analyses consider the needs and limitations 

of each specific vehicle and design reference mission (DRM) with particular attention to parameters such 

as mission duration, expected return time to Earth, mission route and destination, expected radiation 

profile, concept of operations, and more. In-mission preventive care includes, but is not limited to: (see 

NASA-STD-3001, Volume 1 Rev C for fullstandard).

[V1 3004] In-Mission Medical Care All programs shall provide training, in-mission medical capabilities, 

and resources to diagnose and treat potential medical conditions based on epidemiological evidencebased PRA, individual crewmember needs, clinical practice guidelines, flight surgeon expertise, 

historical review, mission parameters, and vehicle-derived limitations. These analyses consider the 

needs and limitations of each specific vehicle and design reference mission (DRM) with particular 

attention to parameters such as mission duration, expected return time to Earth, mission route and 

destination, expected radiation profile, concept of operations, and more. In-mission capabilities 

(including hardware and software), resources (including consumables), and training to enable in-mission 

medical care, and behavioral care, are to include, but are not limited to: (see NASA-STD-3001, Volume 1 

Rev C for full standard).

[V1 3006] Crew Medical Officers Quantity The program(s) shall train a minimum of two crewmembers 

per vehicle/platform as Crew Medical Officers(CMOs).

[V1 3007] Medical Evacuation Medical evacuation to a location with a higher level of medical care shall 

be available for illness/injuries occurring during a spaceflight mission which are beyond the medical 

capabilities available at the crew’s location. 

[V1 3008] In-Mission Evacuation to Definitive Medical Care Facilities Plans and vehicle(s) shall be 

available to transport severely ill or injured crewmember(s) to appropriate Medical Care Facilities, 

including Definitive Medical Care Facilities (DMCF) in the event of a contingency scenario. 

[V1 3009] Palliative Comfort Care The program shall provide in-mission palliative comfort care 

capabilities for medical scenarios where onboard medical resources have been exhausted, or a timely 

return to Earth (or another location of higher medical capability) is not feasible, and survival of the 

crewmember has been determined to be impossible. 

[V1 3010] Termination of Care Each human spaceflight program shall have criteria for termination of care 

available prior to flight.

All referenced tables and figures are available in NASA-STD-3001 Volume 1 Revision C.

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

13

View the current versions of NASA-STD3001 Volume 1 & Volume 2 on the 

OCHMO Standards website

11/28/2023

Rev B
NASA-STD-3001 Technical Brief 

OCHMO-TB-022

Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Referenced Technical Requirements

NASA-STD-3001 Volume 1 Revision C

[V1 3053] Crew Mortality Remains Return to Earth The program shall be capable of returning the remains of 

a deceased crewmember back to Earth. 

[V1 3054] In Situ Disposition of Deceased Crewmember Remains The program shall meet planetary 

protection regulations in the case of in situ or jettison disposition of the remains of a deceased crewmember. 

[V1 5009] Physiological Exposure Mission Training Physiological training shall be provided to assist 

crewmembers with pre-mission familiarization to in-flight exposures including but not limited to: carbon 

dioxide [CO2] exposure training, hypoxia training/instruction, centrifuge, and high-performance aircraft 

microgravity adaptation training in preparation for each mission.

[V1 6006] Extravehicular Activities (EVAs) All crewmembers shall be medically cleared to perform an EVA by 

ground medical support personnel prior to each EVA.

All referenced tables and figures are available in NASA-STD-3001 Volume 1 Revision C.

NASA-STD-3001 Volume 2 Revision D

[V2 6002] Inert Diluent Gas Cabin atmospheric composition shall contain at least 30% diluent gas 

(assuming balance oxygen).

[V2 6003] O2 Partial Pressure Range for Crew Exposure The system shall maintain inspired oxygen partial 

pressure (PI

O2) in accordance with Table 6.2-1—Inspired Oxygen Partial Pressure Exposure Ranges. 

[V2 6004] Nominal Vehicle/Habitat Carbon Dioxide Levels The system shall limit the average one-hour CO2 

partial pressure (ppCO2) in the habitable volume to no more than 3 mmHg. 

[V2 6006] Total Pressure Tolerance Range for Indefinite Crew Exposure The system shall maintain the 

pressure to which the crew is exposed to between 34.5 kPa < pressure ≤ 103 kPa (5 psia < pressure ≤ 15.0 

psia) for indefinite human exposure without measurable impairments to health or performance. 

[V2 6007] Rate of Pressure Change For pressure changes >1.0 psi, the rate of change of total internal vehicle 

pressure shall not exceed 13.5 psi/min. 

[V2 6150] Barotrauma Prevention During a commanded pressure change, the system shall pause within 1 

psi of the pause command being issued by the unsuited or suited crewmember, with ability to increase or 

decrease pressure as needed after the pause.

[V2 6008] Decompression Sickness (DCS) Risk Identification Each program shall define mission unique 

DCS mitigation strategies to achieve the level of acceptable risk of DCS as defined below within 95% 

statistical confidence:

a. DCS ≤ 15% (includes Type I or isolated cutis marmorata).

b. Grade IV venous gas emboli (VGE) ≤ 20%.

c. Prevent Type II DCS.

All referenced tables and figures are available in NASA-STD-3001 Volume 2 Revision D.

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

14

View the current versions of NASA-STD3001 Volume 1 & Volume 2 on the 

OCHMO Standards website

11/28/2023

Rev B
NASA-STD-3001 Technical Brief 

OCHMO-TB-022

Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Referenced Technical Requirements

NASA-STD-3001 Volume 2 Revision D

[V2 6009] Decompression Sickness Treatment Capability The system shall provide DCS treatment

capability.

[V2 6053] Lunar Dust Contamination The system shall limit the levels of lunar dust particles less than 10

μm in size in the habitable atmosphere below a time-weighted average of 0.3 mg/m3 during intermittent

daily exposure periods that may persist up to 6 monthsin duration.

[V2 6064] Sustained Translational Acceleration Limits The system shall limit the magnitude, direction, 

and duration of crew exposure to sustained (> 0.5 seconds) translational acceleration by staying below 

the limits in Figures 6.5-(2-7) and Tables 6.5-(1-6) for seated and standing postures. 

[V2 6065] Rotational Velocity The system shall limit crew exposure to rotational velocities in yaw, pitch, 

and roll by staying below the limits specified in Figure 6.5-8—Rotational Velocity Limits and Table 6.5-7—

Rotational Velocity Limits. 

[V2 6066] Sustained Rotational Acceleration Due to Cross-Coupled Rotation The system shall prevent the 

crew exposure to sustained (> 0.5 second) rotational accelerations caused by cross-coupled rotations 

greater than 2 rad/s2. 

[V2 6067] Transient Rotational Acceleration The system shall limit transient (≤0.5 seconds) rotational 

accelerations in yaw, pitch, or roll as specified in Table 6.5-8—Head CG Rotational Acceleration Limits, to 

which the crew is exposed. The limits are appropriately scaled for each crewmember size from the 50th

percentile male limits of 2,200 rad/s2 for nominal and 3,800 rad/s2 for off-nominal cases. 

[V2 6069] Acceleration Injury Prevention The system shall mitigate the risk of injury to crewmembers 

caused by accelerations during dynamic mission phases per Table 6.5-9—Acceptable Injury Risk Due to 

Dynamic Loads. 

[V2 6070] Injury Risk Criterion The system shall limit crew exposure to transient translational 

acceleration (≤0.5 seconds) by limiting the injury risk criterion (β/beta) to no greater than 1.0 (Low) for 

seated or standing crew as defined by Dynamic Response (DR) limits in NASA/TM-20205008198 Table 2 

“Updated Dynamic Response Limits for Standing”, while crew are restrained as required in NASA/TM2013-217380REV1 for seated crew, or NASA/TM – 20205008198 for standing crew. 

[V2 6111] Dynamic Mission Phases Monitoring and Analysis The system shall collect vehicle and 

crewmember acceleration parameters, specific kinematic responses, and associated metadata, during all 

dynamic mission phases and suited operations (defined as ascent, abort, entry, descent, landing, 

postlanding, and EVA operations) to correlate with any injuries incurred by crewmembers. 

[V2 7016] Personal Hygiene Capability Personal hygiene items shall be provided for each crewmember, 

along with corresponding system capabilities for oral hygiene, personal grooming, and body cleansing.

[V2 7020] Body Waste Management Capability The system shall provide the capability for collection, 

containment, and disposal of body waste for both males and females.

[V2 7026] Body Waste Odor The system shall provide odor control for the body waste management 

system.

All referenced tables and figures are available in NASA-STD-3001 Volume 2 Revision D.

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

15

View the current versions of NASA-STD3001 Volume 1 & Volume 2 on the 

OCHMO Standards website

11/28/2023

Rev B
NASA-STD-3001 Technical Brief 

OCHMO-TB-022

Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Referenced Technical Requirements

NASA-STD-3001 Volume 2 Revision D

[V2 7050] Stowage Provisions The system shall provide for the stowage of hardware and supplies, 

to include location, restraint, and protection for these items. 

[V2 7053] Stowage Interference The system shall provide defined stowage locations that do not 

interfere with crew operations. 

[V2 7064] Trash Accommodation The system shall provide a trash management system to contain, 

mitigate odors, prevent release, and dispose of all expected trash. 

[V2 8001] Volume Allocation The system shall provide the defined habitable volume and layout to 

physically accommodate crew operations and living. 

[V2 8005] Functional Arrangement Habitability functions shall be located based on the use of 

common equipment, interferences, and the sequence and compatibility of operations. 

[V2 8006] Interference The system shall separate functional areas whose functions would 

detrimentally interfere with each other. 

[V2 8007] Spatial and Interface Orientation The system shall have consistent spatial and interface 

orientations relative to a defined vertical orientation. 

[V2 8013] Intravehicular Translation Paths The system shall provide intravehicular activity (IVA) 

translation paths that allow for safe and unencumbered movement of suited and unsuited crew 

and equipment. 

[V2 8027] Hatchway Size and Shape Hatchways and doorways shall be sized and shaped to 

accommodate all planned translations, including unrestricted passage of a suited crewmember and 

crewmembers carrying cargo or equipment. 

[V2 8033] Restraints for Crew Tasks The system shall provide restraints for expected crew 

operations. 

[V2 8038] Restraint and Mobility Aid Standardization Restraints and mobility aids shall be standardized, 

clearly distinguishable, and located to aid crewmembers in starting or stopping movement, changing 

direction or speed, or translating equipment. 

[V2 8040] Mobility Aid for Assisted Ingress and Egress Mobility aids shall be provided for the assisted 

ingress and egress of suited or unsuited crewmembers. 

[V2 8041] Unassisted Ingress, Egress, and Escape Mobility Aids Mobility aids shall be provided for 

ingress, egress, and escape of crewmembers without assistance from other crew or ground personnel. 

[V2 8042] Mobility Aid Provision Mobility aids shall be provided to support all expected suited and 

unsuited tasks. 

[V2 10002] Design-Induced Error The system shall provide crew interfaces that do not exceed the 

maximum observed error rates listed in Table 5.1-1—Maximum Observed Design-Induced Error Rates.

[V2 10003] Operability The system shall provide crew interfaces that enable tasks to be performed 

successfully within the appropriate time limit and degree of accuracy. 

[V2 11001] Suited Donning and Doffing The system shall accommodate efficient and effective donning 

and doffing of spacesuits for both nominal and contingencyoperations.

[V2 11005] EVA Translation Path Hazard Avoidance EVA translation paths shall be free from hazards. 

All referenced tables and figures are available in NASA-STD-3001 Volume 2 Revision D.

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

16

View the current versions of NASA-STD3001 Volume 1 & Volume 2 on the 

OCHMO Standards website

11/28/2023

Rev B
NASA-STD-3001 Technical Brief 

OCHMO-TB-022

Apollo Lunar Lander Module Design: Medical & 

Human Performance Perspective

Reference List

NASA Office of the Chief Health & Medical Officer(OCHMO)

This Technical Brief is derived from NASA-STD-3001 and is for referenceonly.

It does not supersede or waive existing Agency, Program, or Contractrequirements.

17

1. Johnston, R.S., Dietlein, L.F., & Berry, C.A. (1975). Biomedical Results of Apollo. NASA SP-368.

2. Apollo Operations Handbook, LM790-3-LM-2.1, LM790-2. 

https://www.ibiblio.org/apollo/Documents/LMA790-3-LM-2.1.pdf

3. OCHMO Cabin Architecture Technical Brief. 

https://www.nasa.gov/sites/default/files/atoms/files/cabin_architecture_technical_brief_ochmo_061 

62020.pdf

4. Lunar Module Quick Reference Data. Apollo News Reference. 

https://www.hq.nasa.gov/alsj/LM04_Lunar_Module_ppLV1-17.pdf

5. Apollo Operations Handbook – Lunar Module. Volume 1: Subsystems Data. April 1,1971.

https://www.hq.nasa.gov/alsj/LM10HandbookVol1.pdf

11/28/2023

Rev B