SLS-SPEC-159 Cross-Program DSNE REVISION I.pdf

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SLS-SPEC-159

REVISION I

National Aeronautics and Space Administration EFFECTIVE DATE: OCTOBER 27, 2021

CROSS-PROGRAM

DESIGN SPECIFICATION FOR

NATURAL ENVIRONMENTS (DSNE)

Space Launch System (SLS) Program

Revision: I Document No: SLS-SPEC-159

Effective Date: October 27, 2021 Page: 2 of 384

Title: Cross-Program Design Specification for Natural Environments (DSNE)

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HISTORY PAGE

Status Revision

No.

Change

No.

Description

Effective Date

Baseline Initial baseline per CECBD SV-02-0004, dated 8/8/12;

(CR SLS-00034) PCN SV00077

8/8/12

Category 1 Applicable Document Assessment per

PCBD SV2-01-0100R1, dated 8/22/13; CR SLS-

00162; PCN SV00305

8/22/13

A SLS-

00193

Update SLS-SPEC-159, Cross-Program Design

Specification for Natural Environments (DSNE) to

Revision A, per JICBD SV2-02-0063, dated

12/18/13; CR SLS-00193; PCN SV00450

12/18/13

B SLS-

00293

Update SLS-SPEC-159, Cross-Program Design

Specification for Natural Environments (DSNE) to

Revision B to close out a forward work item and change specifications due to model and database updates that are being applied by ESD per JICBD

SV2-02-0133, dated August 27, 2014; CR SLS-

00293; PCN SV00668

8/27/14

C SLS-

00370

Revise SLS-SPEC-159, Cross-Program Design

Specification for Natural Environments (DSNE) to

Revision C, per JICBD SV2-02-0194, dated March

25, 2015; CR SLS-00370; PCN SV00801

03/25/15

D SLS-

00407-

X

Revise SLS-SPEC-159, Cross-Program Design

Specification for Natural Environments (DSNE) to

Revision D, per JICBD SV2-02-0257, dated

November 4, 2015; CR SLS-00407-X; PCN

SV00895

11/4/15

E SLS-

00633-

X

Revise SLS-SPEC-159, Cross-Program Design

Specification for Natural Environments (DSNE), to

Revision E per JICBD SV2-02-0476, dated July 12, 2017; CR SLS-00633-X; PCN SV01341

07/12/17

Effective Date: October 27, 2021 Page: 3 of 384

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F

G

H

SLS-

00833-

X

SLS-

00903-

X

ESD-

0197-X

SLS-

00951-

X

Revise SLS-SPEC-159, Cross-Program Design

Specification for Natural Environments (DSNE) to

Revision F per JICBD SV2-02-0707, dated May 8, 2019; CR SLS-00833-X; PCN SV01922

Revise SLS-SPEC-159, Cross-Program Design

Specification for Natural Environments (DSNE) to

Revision G per JICBD SV2-02-0828, dated

December 11, 2019; CR SLS-00903-X; PCN

SV02184

Incorporate ESD 10012, ESD Concept of Operations, Revision F into the SLS Programmatic Baseline per

PCBD SV2-01-0737, dated April 23, 2020; CR

ESD-0197-X; PCN SV02191

Revise SLS-SPEC-159, Cross-Program Design

Specification for Natural Environments (DSNE) to

Revision H per JICBD SV2-02-0959, dated August

12, 2020; CR SLS-00951-X; PCN SV02416

05/08/19

12/11/19

4/23/20

8/12/20

I SLS-

01036-

X

Revise SLS-SPEC-159, Cross-Program Design

Specification for Natural Environments (DSNE) to

Revision I per JICBD SV2-02-1314, dated October

27, 2021; CR SLS-01036-X; PCN SV03055

10/27/21

NOTE: Updates to this document, as released by numbered changes (Change XXX), are identified by a black bar on the right margin.

Effective Date: October 27, 2021 Page: 4 of 384

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TABLE OF CONTENTS

PARAGRAPH PAGE

1.0 INTRODUCTION

1.1 Background

1.2 Purpose

1.3 Scope

1.4 Change Authority/Responsibility

2.0 DOCUMENTS

2.1 Applicable Documents, Models, and Data Sets

2.1.1 Applicable Documents

2.1.2 Applicable Models/Data Sets

3.0 NATURAL ENVIRONMENT SPECIFICATION

3.1 Prelaunch – Ground Processing Phases

3.1.1 Transportation Environments to the Launch Site KSC (Reserved)

3.1.2 Reserved

3.1.3 Ground Winds for Transport and Launch Pad Environments

3.1.4 Radiant (Thermal) Energy Environment for Ground Ops at KSC

3.1.5 Air Temperature Environment for Ground Operations at KSC

3.1.6 Air Pressure Environment for Ground Operations at KSC

3.1.7 Humidity Environment for Ground Operations at KSC

3.1.8 Aerosol Environment for Ground Operations at KSC

3.1.9 Precipitation Environment for Ground Operations at KSC

3.1.10 Flora and Fauna Environment for Ground Operations

3.1.11 Lightning Environment for Ground Operations at KSC

3.2 Launch Countdown and Earth Ascent Phases

3.2.1 Ground Winds Environments During Launch

3.2.2 Surface Air Temperature Environment During Launch

3.2.3 Surface Air Pressure Environment During Launch

3.2.4 Surface Humidity Environment During Launch

3.2.5 Aloft Wind Environment for Vehicle Ascent

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3.2.6 Aloft Air Temperature Environment for Vehicle Ascent

3.2.7 Aloft Air Pressure Environment for Vehicle Ascent

3.2.8 Aloft Air Density Environment for Vehicle Ascent

3.2.9 Cloud Environment for Launch

3.2.10 Rain and Precipitation Environment for Launch

3.2.11 Flora and Fauna Environments during Launch and Ascent

3.2.12 Natural and Triggered Lightning during Launch and Ascent

3.2.13 Ionizing Radiation Environment for Launch, Ascent and Re-entry

3.3 In-Space Phases

3.3.1 Total Dose

3.3.2 Single Event Effects

3.3.3 Plasma Charging

3.3.4 Ionizing Radiation Environment for Crew Exposure

3.3.5 Reserved

3.3.6 Meteoroid and Orbital Debris Environment

3.3.7 Earth Gravitational Field

3.3.8 Lunar Gravitational Field

3.3.9 Thermal Environment for In-Space Hardware

3.3.10 Solar Illumination Environment for In-Space Hardware

3.3.11 In-Space Neutral Atmosphere (Thermosphere) Density

3.3.12 Geomagnetic Fields (Reserved)

3.4 Lunar Surface Operational Phases

3.4.1 Lunar Surface Geological and Geomorphological Environment

3.4.2 Lunar Regolith Properties

3.4.3 Lunar Surface Plasma Environment

3.4.4 Lunar Regolith Electrical Properties

3.4.5 Optical Properties

3.4.6 Lunar Thermal Environment

3.4.7 Lunar Ionizing Radiation Environment

3.4.8 Lunar Meteoroid and Ejecta Environment

3.4.9 Lunar Illumination

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3.4.10 Lunar Neutral Atmosphere

3.4.11 Special Physical and Chemical Conditions of Regolith Inside Areas of

Permanent Shadow (RESERVED)

3.5 Entry and Landing Phases

3.5.1 Re-entry Neutral Atmosphere

3.5.2 Reserved

3.5.3 Lightning During Normal Landing

3.5.4 Aloft Winds for Normal Descent and Landing

3.5.5 Aloft Air Temperature for Normal Descent and Landing

3.5.6 Aloft Air Pressure for Normal Descent and Landing

3.5.7 Aloft Air Density for Normal Descent and Landing

3.5.8 Surface Winds for Normal Landing

3.5.9 Surface Air Temperature for Normal Landing

3.5.10 Surface Air Pressure for Normal Landing

3.5.11 Surface Air Humidity for Normal Landing

3.5.12 Aerosols for Normal Descent and Landing

3.5.13 Precipitation for Normal Descent and Landing

3.5.14 Flora and Fauna for Descent and Landing

3.5.15 Surface Characteristics and Topography for Normal Land Landing

3.5.16 Cloud Environment for Normal Descent and Landing

3.5.17 Radiant (Thermal) Energy Environment for Normal Landing

3.5.18 Sea State for Normal Water Landing

3.5.19 Reserved

3.5.20 Sea Surface Temperature for Water Landing

3.5.21 Aerosols for Water Landing

3.6 Contingency and Off-Nominal Landing Phases

3.6.1 Re-entry Neutral Atmosphere for Off-Nominal Descent and Landing

3.6.2 Reserved

3.6.3 Lightning During Off-Nominal Landing

3.6.4 Aloft Winds for Off-Nominal Descent and Landing

3.6.5 Aloft Air Temperature for Off-Nominal Descent and Landing

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3.6.6 Aloft Air Pressure for Off-Nominal Descent and Landing

3.6.7 Aloft Air Density for Off-Nominal Descent and Landing

3.6.8 Surface Winds for Off-Nominal Landing

3.6.9 Surface Air Temperature for Off-Nominal Landing

3.6.10 Surface Air Pressure for Off-Nominal Landing

3.6.11 Surface Air Humidity for Off-Nominal Landing

3.6.12 Aerosols for Off-Nominal Descent and Landing

3.6.13 Precipitation for Off-Nominal Descent and Landing

3.6.14 Flora and Fauna for Off-Nominal Descent and Landing

3.6.15 Surface Characteristics and Topography for Off-Nominal Descent and Landing

3.6.16 Cloud Environment for Off-Nominal Descent and Landing

3.6.17 Radiant (Thermal) Energy Environment for Off-Nominal Descent and Landing

3.6.18 Sea State for Off-Nominal Water Landing

3.6.19 Reserved

3.6.20 Sea Surface Temperature for Off-Nominal Water Landing

3.7 Recovery and Post-Flight Processing Phases

3.7.1 Environments for Post-Flight and Recovery at KSC

3.7.2 Sea State for KSC Post-Flight and Recovery

3.7.3 Lightning Specification for Post-Flight and Recovery

3.7.4 Surface Winds for Post-Flight and Recovery

3.7.5 Surface Air Temperature for Post-Flight and Recovery

3.7.6 Surface Air Pressure for Post-Flight and Recovery

3.7.7 Surface Air Humidity for Post-Flight and Recovery

3.7.8 Aerosol Environment for Post-Flight and Recovery

3.7.9 Precipitation Environment for Post-Flight and Recovery

3.7.10 Flora and Fauna Environment for Post-Flight and Recovery

3.7.11 Surface Characteristics and Topography for Post-Flt and Recovery

3.7.12 Cloud Environment for Post-Flight and Recovery

3.7.13 Radiant (Thermal) Energy Environment for Post-Flt and Recovery

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3.8 Interplanetary Space Specification

3.9 Mars Orbit Specification

3.10 Mars Atmosphere and Surface Phase Specification

3.11 Mars Moon Specification

3.12 Near Earth Asteroid Specification

4.0 COMPLIANCE ASSESMENT OF NATURAL ENVIRONMENTS

5.0 REFERENCES

APPENDIX

APPENDIX A ACRONYMS AND ABBREVIATIONS

APPENDIX B NATURAL ENVIRONMENT VALIDATION MATRIX

TABLE

TABLE 1.3-1. DRM CONOPS/DSNE MATRIX

TABLE 3.1.3-1. DESIGN PEAK WIND-SPEED PROFILE

TABLE 3.1.3-2. STEADY STATE WIND-SPEED PROFILE ASSOCIATED WITH THE

DESIGN PEAK WIND-SPEED PROFILE

TABLE 3.1.3-3. OCCURRENCE PROBABILITIES OF 30 S PEAK WIND SPEED IN 0.5 M/S

INTERVALS (CENTERED AT VALUE X) AT THE 18.3 M REFERENCE HEIGHT

TABLE 3.1.3-4. DESIGN HIGH AND LOW STEADY STATE WIND-SPEED PROFILES

FOR USE IN THERMAL ASSESSMENTS WITH TIME CONSTANTS LESS THAN

AN HOUR

TABLE 3.1.3-5. DESIGN HIGH AND LOW STEADY STATE WIND-SPEED PROFILES

FOR USE IN THERMAL ASSESSMENTS WITH TIME CONSTANTS ON THE

ORDER OF HOURS

TABLE 3.1.3-6. DESIGN HIGH AND LOW STEADY STATE WIND-SPEED PROFILES

FOR USE IN THERMAL ASSESSMENTS WITH TIME CONSTANTS ON THE

ORDER OF DAYS

TABLE 3.1.3-7. NON-DIMENSIONAL CONSTANTS FOR THE LONGITUDINAL,

LATERAL AND VERTICAL COMPONENTS OF TURBULENCE

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TABLE 3.1.3-8. NON-DIMENSIONAL CONSTANT FOR THE COHERENCE FUNCTION 37

TABLE 3.1.4-1. DESIGN HIGH RADIANT ENERGY AS A FUNCTION OF TIME OF DAY

TABLE 3.1.4-2. DESIGN LOW RADIANT ENERGY AS A FUNCTION OF TIME OF DAY

TABLE 3.1.4-3. SKY TEMPERATURE DESIGN LIMITS FOR KSC

TABLE 3.1.4-4. COLD DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, CLOUDY SKY

TABLE 3.1.4-5. HOT DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, CLOUDY SKY

TABLE 3.1.4-6. COLD DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, PARTLY CLOUDY SKY

TABLE 3.1.4-7. HOT DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, PARTLY CLOUDY SKY

TABLE 3.1.4-8. COLD DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, CLEAR SKY

TABLE 3.1.4-9. HOT DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, CLEAR SKY

TABLE 3.1.5-1. DESIGN HOT AND COLD DIURNAL TEMPERATURE PROFILE

TABLE 3.1.5-2. DESIGN HOT AND COLD MONTHLY AVERAGED DIURNAL

TEMPERATURE PROFILE

TABLE 3.1.7-1. PSYCHROMETRIC DATA, DEW POINT TEMPERATURE VERSUS

TEMPERATURE ENVELOPE FOR KSC

TABLE 3.1.9-1. DESIGN RAINFALL, KSC, BASED ON YEARLY LARGEST RATE FOR

STATED DURATIONS

TABLE 3.1.9-2. DESIGN HAIL CHARACTERISTICS FOR KSC

TABLE 3.2.1-1. PEAK WIND SPEED PROFILE FOR VEHICLE LAUNCH

TABLE 3.2.1-2. STEADY STATE WIND SPEED PROFILE FOR VEHICLE LAUNCH

TABLE 3.2.1-3. NON-DIMENSIONAL CONSTANTS FOR THE LONGITUDINAL,

LATERAL AND VERTICAL COMPONENTS OF TURBULENCE

TABLE 3.2.1-4. NON-DIMENSIONAL CONSTANT FOR THE COHERENCE FUNCTION 59

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TABLE 3.2.5-1. DISCRETE LONGITUDINAL GUST MAGNITUDE (M/S) AS A FUNCTION

OF ALTITUDE (KM) AND GUST HALF-WIDTH DM (M) BASED ON

MODERATE TURBULENCE

TABLE 3.2.5-2. DISCRETE LONGITUDINAL GUST MAGNITUDE (FT/S) AS A

FUNCTION OF ALTITUDE (KFT) AND GUST HALF-WIDTH DM (FT) BASED

ON MODERATE TURBULENCE

TABLE 3.2.5-3. EARTH-GRAM 2010 INPUT TO GENERATE 1,000 OR MORE

PERTURBED PROFILES (0 TO 90 KM) OF WIND, TEMPERATURE, PRESSURE,

AND DENSITY PER MONTHLY REFERENCE PERIOD

TABLE 3.2.5-4. EARTH-GRAM 2010 INPUT TO GENERATE MONTHLY MEAN

PROFILES TO BE APPENDED TO MVWPM PROFILES

TABLE 3.2.11-1. AVIAN NUMBER DENSITY UP TO 7.62 KM (25,000 FT)

TABLE 3.2.13-1. 200 KM INTEGRAL LET FLUX AS SHOWN IN FIGURE 3.2.13-1

TABLE 3.2.13-2. 200 KM DIFFERENTIAL PROTON FLUX AS SHOWN IN FIGURE 3.2.13-

2………………………………………………………………………………………..80

TABLE 3.2.13-3. 200 KM INTEGRAL PROTON FLUX AS SHOWN IN FIGURE 3.2.13-3 ...82

TABLE 3.2.13-4. FLUX OF > 10 MEV NEUTRONS AT ALTITUDES TO 20 KM

TABLE 3.3.1-1. TOTAL DOSE APPLICABILITY MATRIX FOR THE DESIGN

REFERENCE MISSION BY REGIONS OF SPACE

TABLE 3.3.1.1-1. DAILY TRAPPED PROTON FLUENCES

TABLE 3.3.1.1-2. DAILY TRAPPED ELECTRON FLUENCES

TABLE 3.3.1.1-3. PROTON FLUENCES OF AN ISS SPE

TABLE 3.3.1.1-4. DAILY TRAPPED BELTS TID INSIDE SHIELDING

TABLE 3.3.1.1-5. TOTAL SPE TID INSIDE SHIELDING

TABLE 3.3.1.2.1-1. DAILY TRAPPED PROTON FLUENCES

TABLE 3.3.1.2.1-2. DAILY TRAPPED ELECTRON FLUENCES

TABLE 3.3.1.2.1-3. DAILY TRAPPED BELTS TID INSIDE SHIELDING

TABLE 3.3.1.2.2-1. TRAPPED PROTON FLUENCES

TABLE 3.3.1.2.2-2. TRAPPED ELECTRON FLUENCES

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TABLE 3.3.1.2.2-3. TRAPPED BELTS TID INSIDE SHIELDING

TABLE 3.3.1.2.3-1. DAILY TRAPPED PROTON FLUENCES

TABLE 3.3.1.2.3-2. DAILY TRAPPED ELECTRON FLUENCES

TABLE 3.3.1.2.3-3. DAILY TRAPPED BELTS TID INSIDE SHIELDING

TABLE 3.3.1.2.4-1. DAILY TRAPPED PROTON FLUENCES

TABLE 3.3.1.2.4-2. DAILY TRAPPED ELECTRON FLUENCES

TABLE 3.3.1.2.4-3. DAILY TRAPPED BELTS TID INSIDE SHIELDING

TABLE 3.3.1.2.7-1. DAILY TRAPPED PROTON FLUENCES

TABLE 3.3.1.2.7-2. DAILY TRAPPED ELECTRON FLUENCES

TABLE 3.3.1.2.7-3. DAILY TRAPPED BELTS TID INSIDE SHIELDING

TABLE 3.3.1.3-1. DAILY TRAPPED ELECTRON FLUENCES

TABLE 3.3.1.3-2. DAILY TRAPPED BELTS TID INSIDE SHIELDING

TABLE 3.3.1.10.1-1. INTEGRAL AND DIFFERENTIAL PROTON FLUENCES OF A

SHIELDED SPE

TABLE 3.3.1.10.1-2. TOTAL SHIELDED SPE TID INSIDE AL SHIELDING

TABLE 3.3.1.10.2-1. INTEGRAL AND DIFFERENTIAL PROTON FLUENCE OF AN

UNSHIELDED SPE

TABLE 3.3.1.10.2-2. DAILY UNSHIELDED GCR INTEGRAL PROTON FLUENCE

TABLE 3.3.1.10.2-3. TOTAL UNSHIELDED SPE TID INSIDE AL SHIELDING

TABLE 3.3.1.10.2-4. TOTAL UNSHIELDED DAILY GCR TID INSIDE AL SHIELDING .142

TABLE 3.3.1.10.2-5. TOTAL UNSHIELDED SPE TID INSIDE AL SHIELDING – 15

YEARS……………………………………………………………………………….145

TABLE 3.3.1.10.2-6. INTEGRAL ELECTRON AND PROTON FLUENCE FOR 15 YEAR

EXPOSURE TO SOLAR WIND AND EARTH’S MAGNETOTAIL IN A NEAR

RECTILINEAR HALO ORBIT, 95TH PERCENTILE……………………………..147

TABLE 3.3.1.10.2-7 TOTAL UNSHIELDED SPE TID INSIDE ALUMINUM SHIELDING –

18 HOURS…………………………………………………………………………...149

TABLE 3.3.2-1. SINGLE EVENT EFFECTS APPLICABILITY MATRIX FOR THE DESIGN

REFERENCE MISSION BY REGIONS OF SPACE

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TABLE 3.3.2.1-1. ISS SPE INTEGRAL PEAK LET FLUX FOR SELECTED AL SHIELDING

THICKNESS AS A FUNCTION OF LET

TABLE 3.3.2.1-2. ISS SPE WORST DAY INTEGRAL FLUX FOR SELECTED AL

SHIELDING THICKNESS AS A FUNCTION OF LET

TABLE 3.3.2.1-3. INTEGRAL PROTON FLUX FOR AN ISS SPE, SOLAR MINIMUM GCR,

AVERAGE TRAPPED PROTONS AND PEAK TRAPPED PROTONS

TABLE 3.3.2.1-4. DIFFERENTIAL PROTON FLUX FOR AN ISS SPE, SOLAR MINIMUM

GCR, AVERAGE TRAPPED PROTONS AND PEAK TRAPPED PROTONS

TABLE 3.3.2.2.1-1. SPE INTEGRAL PEAK LET FLUX FOR SELECTED AL SHIELDING

THICKNESS AS A FUNCTION OF LET

TABLE 3.3.2.2.1-2. SPE WORST DAY INTEGRAL FLUX FOR SELECTED AL

SHIELDING THICKNESS AS A FUNCTION OF LET

TABLE 3.3.2.2.1-3. INTEGRAL PROTON FLUX FOR THE PEAK TRAPPED PROTONS.

TABLE 3.3.2.10.2-1. SPE INTEGRAL PEAK LET FLUX FOR SELECTED AL SHIELDING

THICKNESS AS A FUNCTION OF LET

TABLE 3.3.2.10.2-2. SPE WORST DAY INTEGRAL FLUX FOR SELECTED AL

SHIELDING THICKNESS AS A FUNCTION OF LET

TABLE 3.3.2.10.2-3. INTEGRAL PROTON FLUX OF A SPE AND GCR

TABLE 3.3.2.10.2-4. DIFFERENTIAL PROTON FLUX FOR A SPE AND SOLAR

MINIMUM GCR……………………………………………………………………..176

TABLE 3.3.2.10.2-5. GCR INTEGRAL LET AT SOLAR MINIMUM FOR SELECTED AL

SHIELDING THICKNESS AS A FUNCTION OF LET

TABLE 3.3.3-1. PLASMA CHARGING APPLICABILITY MATRIX FOR THE DESIGN

REFERENCE MISSIONS BY REGIONS OF SPACE

TABLE 3.3.3.1-1. AMBIENT PLASMA ENVIRONMENT FOR LESS THAN 1000 KM

ALTITUDE

TABLE 3.3.3.2.2-1. RADIATION BELT TRANSIT AVERAGE INTEGRAL ELECTRON

FLUX

TABLE 3.3.3.3-1. GEOSYNCHRONOUS ORBIT (GEO) PLASMA ENVIRONMENT

PARAMETERS

TABLE 3.3.3.4-1. INTERPLANETARY ENVIRONMENT PLASMA PARAMETERS

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TABLE 3.3.3.5-1. LUNAR ORBIT PLASMA PARAMETERS

TABLE 3.3.3.10-1. POLAR PLASMA PARAMETERS

TABLE 3.3.4-1. SPE DESIGN EVENT DIFFERENTIAL SPECTRA

TABLE 3.3.4-2. GCR DESIGN DIFFERENTIAL SPECTRA (SOLAR MINIMUM)

TABLE 3.3.9.1.4-1. PROJECTED WORST CASE MINIMUM SOLAR FLUX DURING

LUNAR ECLIPSE, DATED JUNE 26, 2029

TABLE 3.3.9.2-1. ALBEDO, OUTGOING LONGWAVE RADIATION (OLR) PAIRS FOR

CRITICAL SYSTEMS IN LOW-INCLINATION ORBITS

TABLE 3.3.9.2-2. ALBEDO, OLR PAIRS FOR CRITICAL SYSTEMS IN MEDIUM-

INCLINATION ORBITS

TABLE 3.3.9.2-3 SZA CORRECTION TERMS FOR ALBEDO FOR A RANGE OF ORBITAL

BETA ANGLES……………………………………………………………………...207

TABLE 3.3.10-1. SOLAR SPECTRAL IRRADIANCE-STANDARD CURVE, ABRIDGED

VERSION

TABLE 3.3.11-1. EARTH-GRAM 2010 INPUTS FOR THERMOSPHERE PARAMETER

CALCULATIONS

TABLE 3.4.1.1-1. NUMBER DENSITY (ALSO CALLED FREQUENCY) OF CRATERS

EQUAL TO OR LARGER THAN DIAMETER D PER KM2 FOR A 3.5 GA

SURFACE

TABLE 3.4.1.2-1. DEPTH/DIAMETER RATIOS FOR FRESH LUNAR CRATERS (AFTER

STOPAR ET AL., 2017)

TABLE 3.4.1.2-2. CRATER MORPHOLOGICAL CHARACTERISTICS (FOR D<1 KM;

MODIFIED AFTER BASILEVSKY, 1976)

TABLE 3.4.1.3-1. MEDIAN SLOPES IN DIFFERENT REGIONS, WITH +/- VALUES

REPRESENTING THE 25TH AND 75TH PERCENTILES

TABLE 3.4.1.4-1. LANDING SITE ANALYSIS OF ROCK ABUNDANCE. ALL OF THESE

SITES WITH THE EXCEPTION OF SURVEYOR 7 – AN EXTREME CASE ON

THE RIM OF TYCHO CRATER – HAVE FRACTIONAL ROCK AREA OF <~1%

IN DIVINER

TABLE 3.4.2.2.1-1 WEIGHT DISTRIBUTION IN SIZE-FRACTIONS OF

REPRESENTATIVE SCOOPED SURFACE SOILS (DATA FROM MORRIS ET

AL., 1983, DATA EMPHASIZE COARSER FRACTIONS). (TABLE ADAPTED

FROM HEIKEN ET AL., 1991: LUNAR SOURCEBOOK, TABLE 9.1, PG. 478.) .228

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TABLE 3.4.2.2.1-2 AVERAGE GEOTECHNICAL PARTICLE SIZE DISTRIBUTION FROM

MIDDLE CURVE OF FIGURE 3.4.2.2.1-1 (CARRIER 2003)……………………..228

TABLE 3.4.2.2.2-1 SUMMARY OF GRAIN-SPECIFIC PROPERTIES (<1MM SIZE-

FRACTION)

TABLE 3.4.2.2.3.1-1 CUMULATIVE PERCENTILE OF DUST PARTICLES (LESS THAN 10

MICRONS) SMALLER THAN THE PLOTTED SIZE FOR APOLLO 11 (SAMPLE

10084) AND APOLLO 17 (SAMPLE 70051) PARK ET AL., 2008

TABLE 3.4.2.3-1 SUMMARY OF BULK REGOLITH PROPERTIES TAKEN AS

REPRESENTATIVE OF TYPICAL LUNAR CHARACTERISTICS BASED ON

PRIOR LANDED MISSIONS AND SAMPLE PROPERTIES

TABLE 3.4.2.3.4-1 POROSITY FOR VARIOUS DEPTHS

TABLE 3.4.2.3.6-1 SIGNIFICANT LUNAR MINERALS: (%: A-ABUNDANT, M-MAJOR,

M-MINOR, T-TRACE)

TABLE 3.4.3-1. LUNAR SURFACE PLASMA PARAMETERS

TABLE 3.4.3-2. LUNAR SURFACE POTENTIALS………………………………………...258

TABLE 3.4.4-1 REGOLITH ELECTRICAL PROPERTIES

TABLE 3.4.4.2-1 NUMERICAL VALUES OF RELATIVE DIELECTRIC PERMITTIVITY

FROM FIGURE 3.4.4.2-1. FROM LUNAR SOURCEBOOK FIGURES 9.60 AND

9.61

TABLE 3.4.4.3-1 LOSS TANGENT OF LUNAR SOIL (BLUE CIRCLES, SAMPLE 14163

FINES) AND ROCK (ORANGE SQUARES, SAMPLE 14310) AS A FUNCTION OF

FREQUENCY FROM LUNAR SOURCEBOOK FIGURES 9.60 AND 9.61

TABLE 3.4.5.1-1 VALUES OF H-G PARAMETERS DETERMINED BY LRO FOR

VARIOUS TYPES OF REGOLITH (SATO ET AL. 2014, THEIR FIGURE 20)

TABLE 3.4.6.1.1-1 ALBEDO AND EMISSIVITY EXTREMES FOR GLOBAL AND SOUTH

POLAR REGIONS. SINCE THE SOUTH POLAR REGION IS ESSENTIALLY

HIGHLAND REGOLITH, WE USE HIGHLAND EQUATORIAL VALUES FOR A

AND . THE INFRARED EMISSIVITIES ARE TAKEN FROM VASAVADA ET

AL. 2012 AND HAYNE ET AL. 2017 AND THE GLOBAL ALBEDO IS FROM

WILLIAMS ET AL. 2017

TABLE 3.4.6.2-1 NOMINAL VALUES OF THERMAL PARAMETERS FOR LUNAR

REGOLITH

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TABLE 3.4.6.2.2-1 SPECIFIC HEAT VERSUS TEMPERATURE EXTRACTED FROM

FIGURE 3.4.6.2.2-1………………………………………………………………….272

TABLE 3.4.6.2.3-1 THERMAL DIFFUSIVITY AS A FUNCTION OF TEMPERATURE FOR

2 DIFFERENT DEPTHS. THESE VALUES ASSUME A DENSITY OF 1580

KG/M3

TABLE 3.4.6.3-1 LUNAR SURFACE TEMPERATURE EXTREMES FOR VARIOUS

LATITUDES AND SOLAR ILLUMINATION CONDITIONS FROM WILLIAMS

ET AL. 2017. MEAN TEMPERATURES ARE THE PLOTTED VALUE WITH THE

MAX OR MIN EXTREMES TAKEN FROM THE ERROR BARS. TEMPERATURE

FOR COLDEST PERMANENTLY SHADOWED CRATER IS FROM PAIGE AND

SIEGLER, 2016

TABLE 3.4.7.3-1 DIFFERENTIAL NEUTRON FLUX FOR SOLAR MAXIMUM AND

MINIMUM CONDITIONS (AFTER ADAMS ET AL. 2007)

TABLE 3.5.4-1. EARTH-GRAM 2010 INPUT TO GENERATE 1,000 OR MORE

PERTURBED PROFILES (0 TO 90 KM) OF TEMPERATURE, PRESSURE, AND

DENSITY PER MONTHLY REFERENCE PERIOD

TABLE 3.5.8-1. DRYDEN GUST SPECTRA PARAMETERS FOR THE LONGITUDINAL,

LATERAL, AND VERTICAL COMPONENTS FOR THE LANDING PHASE

TABLE 3.5.17-1. COLD DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, CLOUDY SKY

TABLE 3.5.17-2. HOT DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, CLOUDY SKY

TABLE 3.5.17-3. COLD DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, PARTLY CLOUDY SKY

TABLE 3.5.17-4. HOT DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, PARTLY CLOUDY SKY

TABLE 3.5.17-5. COLD DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, CLEAR SKY

TABLE 3.5.17-6. HOT DESIGN RADIANT ENERGY AND SKY TEMPERATURE AS A

FUNCTION OF TIME OF DAY, CLEAR SKY

TABLE 3.5.18-1. MINIMUM AVERAGE WAVE PERIOD CORRESPONDING TO GIVEN

SWH

TABLE 3.5.18-2. ENERGY SPECTRUM FOR 2 M SWH

TABLE 3.6.18-1. ENERGY SPECTRUM FOR 4 M SWH

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FIGURE

FIGURE 3.1.7-1. PSYCHROMETRIC DATA, DEW POINT TEMPERATURE VERSUS

TEMPERATURE ENVELOPE FOR KSC

FIGURE 3.2.13-1. 200 KM INTEGRAL FLUX FOR A DESIGN SPE AND SOLAR

MINIMUM GCR IN A STORMY MAGNETIC FIELD FOR 51.6° INCLINATION,

200 KM ALTITUDE, AT 40° NORTH LATITUDE, AS A FUNCTION OF LET

FIGURE 3.2.13-2. 200 KM DIFFERENTIAL DESIGN SPE AND GCR PROTON FLUX AS A

FUNCTION OF ENERGY

FIGURE 3.2.13-3. 200 KM INTEGRAL PROTON FLUX OF DESIGN SPE AND INTEGRAL

GCR FLUX AS A FUNCTION OF ENERGY

FIGURE 3.3.1.1-1. DAILY TRAPPED PROTON FLUENCES

FIGURE 3.3.1.1-2. DAILY TRAPPED ELECTRON FLUENCES

FIGURE 3.3.1.1-3. PROTON FLUENCES OF AN ISS SPE

FIGURE 3.3.1.1-4. DAILY TRAPPED BELTS TID INSIDE SHIELDING

FIGURE 3.3.1.1-5. TOTAL SPE TID INSIDE SHIELDING

FIGURE 3.3.1.2.1-1. DAILY TRAPPED PROTON FLUENCES

FIGURE 3.3.1.2.1-2. DAILY TRAPPED ELECTRON FLUENCES

FIGURE 3.3.1.2.1-3. DAILY TRAPPED BELTS TID INSIDE SHIELDING

FIGURE 3.3.1.2.2-1. TRAPPED PROTON FLUENCES

FIGURE 3.3.1.2.2-2. TRAPPED ELECTRON FLUENCES

FIGURE 3.3.1.2.2-3. TRAPPED BELTS TID INSIDE SHIELDING

FIGURE 3.3.1.2.3-1. DAILY TRAPPED PROTON FLUENCES

FIGURE 3.3.1.2.3-2. DAILY TRAPPED ELECTRON FLUENCES

FIGURE 3.3.1.2.3-3. DAILY TRAPPED BELTS TID INSIDE SHIELDING

FIGURE 3.3.1.2.4-1. DAILY TRAPPED PROTON FLUENCES

FIGURE 3.3.1.2.4-2. DAILY TRAPPED ELECTRON FLUENCES

FIGURE 3.3.1.2.4-3. DAILY TRAPPED BELTS TID INSIDE SHIELDING

FIGURE 3.3.1.2.7-1. DAILY TRAPPED PROTON FLUENCES

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FIGURE 3.3.1.2.7-2. DAILY TRAPPED ELECTRON FLUENCES

FIGURE 3.3.1.2.7-3. DAILY TRAPPED BELTS TID INSIDE SHIELDING

FIGURE 3.3.1.3-1. DAILY TRAPPED ELECTRON FLUENCES

FIGURE 3.3.1.3-2. DAILY TRAPPED BELTS TID INSIDE SHIELDING

FIGURE 3.3.1.10.1-1. INTEGRAL AND DIFFERENTIAL PROTON FLUENCES OF A

SHIELDED SPE

FIGURE 3.3.1.10.1-2. TOTAL SHIELDED SPE TID INSIDE AL SHIELDING

FIGURE 3.3.1.10.2-1. INTEGRAL AND DIFFERENTIAL PROTON FLUENCE OF AN

UNSHIELDED SPE

FIGURE 3.3.1.10.2-2. DAILY UNSHIELDED GCR INTEGRAL PROTON FLUENCE

FIGURE 3.3.1.10.2-3. TOTAL UNSHIELDED SPE TID INSIDE AL SHIELDING

FIGURE 3.3.1.10.2-4. TOTAL UNSHIELDED SPE TID INSIDE AL SHIELDING – 15

YEARS……………………………………………………………………………….145

FIGURE 3.3.1.10.2-5. INTEGRAL ELECTRON AND PROTON FLUENCE FOR 15 YEAR

EXPOSURE TO SOLAR WIND AND EARTH’S MAGNETOTAIL IN A NEAR

RECTILINEAR HALO ORBIT, 95TH PERCENTILE……………………………..146

FIGURE 3.3.1.10.2-6 TOTAL UNSHIELDED SPE TID INSIDE ALUMINUM SHIELDING –

18 HOURS…………………………………………………………………………...149

FIGURE 3.3.2.1-1. ISS SPE INTEGRAL PEAK LET FLUX FOR SELECTED AL

SHIELDING THICKNESS AS A FUNCTION OF LET

FIGURE 3.3.2.1-2. ISS SPE WORST DAY INTEGRAL FLUX FOR SELECTED AL

SHIELDING THICKNESS AS A FUNCTION OF LET

FIGURE 3.3.2.1-3. INTEGRAL PROTON FLUX OF AN ISS SPE AND GCR

FIGURE 3.3.2.1-4. DIFFERENTIAL PROTON FLUX FOR ISS SPE AND SOLAR

MINIMUM GCR

FIGURE 3.3.2.2.1-1. SPE INTEGRAL PEAK LET FLUX FOR SELECTED AL SHIELDING

THICKNESS AS A FUNCTION OF LET

FIGURE 3.3.2.2.1-2. SPE WORST DAY INTEGRAL FLUX FOR SELECTED AL

SHIELDING THICKNESS AS A FUNCTION OF LET

FIGURE 3.3.2.2.1-3. INTEGRAL PEAK TRAPPED PROTON FLUX

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FIGURE 3.3.2.10.2-1. SPE INTEGRAL PEAK LET FLUX FOR SELECTED AL SHIELDING

THICKNESS AS A FUNCTION OF LET

FIGURE 3.3.2.10.2-2. SPE WORST DAY INTEGRAL FLUX FOR SELECTED AL

SHIELDING THICKNESS AS A FUNCTION OF LET

FIGURE 3.3.2.10.2-3. INTEGRAL PROTON FLUX OF A SPE AND GCR

FIGURE 3.3.2.10.2-4. DIFFERENTIAL PROTON FLUX FOR SPE AND SOLAR MINIMUM

GCR

FIGURE 3.3.2.10.2-5. GCR INTEGRAL LET AT SOLAR MINIMUM FOR SELECTED AL

SHIELDING THICKNESS AS A FUNCTION OF LET

FIGURE 3.3.3.2.2-1. RADIATION BELT TRANSIT AVERAGE INTEGRAL ELECTRON

FLUX………………………………………………………………………………...182

FIGURE 3.3.9.2-1 PLOT OF NUMERICALLY INTEGRATED DATA (DOTS) AND

POLYNOMIAL FIT (LINE) OF THE SZA CORRECTION TERMS……………...207

FIGURE 3.4.1.1-1. CUMULATIVE CRATER DENSITY (NUMBER OF CRATERS OF

DIAMETER ≥X PER KM2) ON A LUNAR SURFACE OF 3.5 GA. (GA=BILLIONS

OF YEARS/SURFACE AGE)

FIGURE 3.4.1.3-1. FREQUENCY OF SLOPES ACROSS THE LUNAR SURFACE AT 25-M

BASELINE FROM LOLA, SHOWN WITH A LINEAR FREQUENCY AXIS AND

LOGARITHMIC FREQUENCY AXIS (KRESLAVSKY AND HEAD 2016)

FIGURE 3.4.1.3-2. MEDIAN SLOPES AT TWO LANDING SITES FROM A

COMBINATION OF LOLA (24 M BASELINES AND ABOVE) AND LROC

NARROW ANGLE CAMERA DIGITAL TERRAIN MODELS. MODIFIED FROM

KRESLAVSKY ET AL. (2015)

FIGURE 3.4.1.3-3. MEDIAN SLOPES FROM LOLA (17 M) (SEE ROSENBURG ET AL.

2011). (A) NORTH POLE, (B) SOUTH POLE, AND (C) EQUATORIAL REGIONS.

FIGURE 3.4.1.3-4 LOLA TOPOGRAPHY (A, C) AND SURFACE SLOPES (B, D) AT 100-M

BASELINE FOR THE LUNAR SOUTH (TOP) AND NORTH POLES (BOTTOM).

BOTH MAPS EXTEND FROM THEIR RESPECTIVE POLE TO 75° LATITUDE

(FROM SMITH ET AL., 2017)

FIGURE 3.4.1.4-1. FREQUENCY OF FRACTIONAL AREA COVERED BY ROCKS FROM

DIVINER, SHOWN WITH A LINEAR FREQUENCY AXIS (TOP) AND

LOGARITHMIC FREQUENCY AXIS (BOTTOM). FROM PDS DIVINER ROCK

ABUNDANCE GRID, WHICH IS CALCULATED AT 236 M/PX

RESOLUTION……………………………………………………………………….220

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FIGURE 3.4.1.4-2. CUMULATIVE SIZE-FREQUENCY DISTRIBUTIONS FOR ROCKS

NEAR THE SURVEYOR SPACECRAFT DERIVED FROM SURFACE IMAGES

(FROM SHOEMAKER AND MORRIS, 1970)

FIGURE 3.4.1.4-3. SPATIAL DISTRIBUTION OF ROCK ABUNDANCE (NOTE

LOGARITHMIC SCALE) ON THE MOON (HAYNE ET AL., 2017). THE MARIA

STAND OUT IN THIS MAP AS HAVING MODESTLY ENHANCED ROCK

ABUNDANCE OVER THE HIGHLANDS; MEAN VALUES IN THE MARIA ARE

0.005 (0.5%) COMPARED TO 0.003 (0.3%) FOR THE HIGHLANDS. THE

BRIGHTEST SPOTS IN THIS MAP ARE INDIVIDUAL LARGE CRATERS

FIGURE 3.4.2.1-1 A SCHEMATIC CROSS SECTION OF THE LUNAR SURFACE TO A

DEPTH OF 25 KM. THE UPPERMOST SURFACE IS THE LUNAR REGOLITH,

WITH A DEPTH OF APPROXIMATELY 0 – 15 M, DEPENDING ON LOCATION

AND MATURITY OF THE SURFACE. (MODIFIED FROM LUNAR

SOURCEBOOK, HEIKEN ET AL., 1991, AND LUNAREF WEBSITE, LUNAR

AND PLANETARY INSTITUTE)…………………………………………………..223

FIGURE 3.4.2.1-2. MODEL DISTRIBUTION OF REGOLITH THICKNESSES AT THE

APOLLO 15 SITE BASED ON OBSERVATIONS OF THE CRATER POPULATION

(HIRABAYASHI ET AL., 2018). THIS ILLUSTRATES THE EXPECTED

VARIABILITY AT A PARTICULAR SITE ON THE MOON

FIGURE 3.4.2.1.1-1 MODAL (VOLUME) ABUNDANCE OF DIFFERENT COMPONENTS

OF THE REGOLITH. DATA ARE FROM EACH OF THE APOLLO MISSIONS

AND REPRESENT THE 1 MM TO 90 MICRON SIZE FRACTION. MODIFIED

FROM FIGURE 7.1 LUNAR SOURCEBOOK (FROM LUNAREF WEBSITE,

LUNAR AND PLANETARY INSTITUTE)

FIGURE 3.4.2.2.1-1 GEOTECHNICAL PARTICLE SIZE DISTRIBUTION: MIDDLE CURVE

SHOWING THE AVERAGE DISTRIBUTION; LEFT-HAND AND RIGHT-HAND

CURVES SHOWING + 1 STANDARD DEVIATION (FROM CARRIER 2003)…227

FIGURE 3.4.2.2.1-2 PARTICLE SIZE DISTRIBUTION OF SUBMILLIMETER PARTICLES

FOR ALL APOLLO AND LUNA SITES EXCEPT APOLLO 16 (CARRIER

2005)………………………………………………………………………………….228

FIGURE 3.4.2.2.1-3 PARTICLE SIZE DISTRIBUTION OF SUBMILLIMETER PARTICLES

FOR ALL APOLLO 16 SITE (CARRIER 2005)

FIGURE 3.4.2.2.1-4 GRAIN-SIZE AS A FUNCTION OF DEPTH AT THE APOLLO 15 SITE.

SAMPLE 15010/11 COLLECTED CLOSE TO THE EDGE OF HADLEY RILLE

WHERE THE REGOLITH IS THIN AND IMMATURE. MODIFIED FROM

FIGURE 7.17 LUNAR SOURCEBOOK (FIGURE FROM LUNAREF WEBSITE,

LUNAR AND PLANETARY SCIENCE INSTITUTE)

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FIGURE 3.4.2.2.2-1 TYPICAL LUNAR SOIL AGGLUTINATES. (A) OPTICAL

MICROSCOPE PHOTOGRAPH DISPLAYING THE IRREGULAR SHAPE

VARIATION IN AGGLUTINATES (SEPARATED FROM APOLLO 11 SOIL

SAMPLE 10084, NASA PHOTO S69-54827). (B) SCANNING ELECTRON

PHOTOMICROGRAPH OF A DOUGHNUT-SHAPED AGGLUTINATE.

PARTICLE HAS A GLASSY SURFACE COATED WITH SMALL SOIL

FRAGMENTS (NASA PHOTO S87-38812). (FIGURE MODIFIED FROM FIGURE

7.2 IN CARRIER ET AL., 1991)

FIGURE 3.4.2.2.2-2 APOLLO 11 REGOLITH FRAGMENTS FROM THE 2-4 MM GRAIN-

SIZE FRACTION. NOTE THE DIVERSITY IN SHAPES AND ANGULARITY,

INCLUDING TWO IMPACT-GLASS SPHERULES. (PHOTO CREDIT: RANDY

KOROTEV,

HTTP://METEORITES.WUSTL.EDU/LUNAR/REGOLITH_BRECCIA.HTM)

FIGURE 3.4.2.2.3.1-1 CUMULATIVE PERCENTILE OF DUST PARTICLES (LESS THAN

10 MICRONS) SMALLER THAN THE PLOTTED SIZE FOR APOLLO 11

(SAMPLE 10084, ORANGE LINE) AND APOLLO 17 (SAMPLE 70051, BLUE

LINE) AFTER PARK ET AL., 2008

FIGURE 3.4.2.2.3.2-1 ANNUALLY AVERAGED LUNAR DUST DENSITY DISTRIBUTION

SHOWS HIGHEST CONCENTRATION AT THE SUNRISE TERMINATOR

(SZALAY 2016)……………………………………………………………………..237

FIGURE 3.4.2.2.3.3-1 EXPERIMENTAL RESULTS USING JSC-1 SIMULANT FOR A 1)

TRIBOCHARGING, 2) PHOTOEMISSION, AND 3) PHOTOELECTRON LAYER

(FROM COLWELL ET AL., 2007 AND SICKAFOOSE ET AL., 2001)

FIGURE 3.4.2.2.3.4-1. COMPARISON OF OBSERVED AND MODELED DUST DENSITY

AS A FUNCTION OF ALTITUDE AND SIZE (HORANYI 2015)………………...239

FIGURE 3.4.2.2.3.4-2. COMPARISON OF OBSERVED AND MODELED CUMULATIVE

DUST MASS (HORANYI 2015)……………………………………………………240

FIGURE 3.4.2.3.1-1 IN SITU BULK DENSITY OF THE REGOLITH BASED ON DRILL

CORE SAMPLES FROM THE APOLLO 15, 16, AND 17 MISSIONS. THE

ABRUPT INCREASES AND DECREASES RESULT FROM DIFFERENT LAYERS

AT DIFFERENT DEPTHS (LUNAR SOURCEBOOK 1991)

FIGURE 3.4.2.3.2-1 RELATIVE DENSITY AS A FUNCTION OF DEPTH (MODIFIED

FROM FIGURE 9.20 IN LUNAR SOURCEBOOK)

FIGURE 3.4.2.3.3-1 VOID RATIO AND POROSITY AS A FUNCTION OF RELATIVE

DENSITY FOR LUNAR SAMPLES. ALSO SHOWN IS A FUNCTION FOR IDEAL,

VARIABLY PACKED UNIFORM SPHERES. THERE IS CONSIDERABLE

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SCATTER AMONG THE LUNAR SAMPLES (MODIFIED FROM FIGURE 9.18 IN

REF. LUNAR SOURCEBOOK)

FIGURE 3.4.2.3.6-1: A COMPARISON OF THE LINEAR MOHS HARDNESS AND THE

LOGARITHMIC KNOOP HARDNESS SCALES. COMMON CONSTRUCTION

MATERIALS (LEFT SIDE) CAN BE COMPARED TO MOHS REFERENCE

MINERALS (RIGHT SIDE) (RICKMAN AND STREET, 2008)

FIGURE 3.4.2.4.2-1 COMPRESSIBILITY MEASUREMENTS ON APOLLO 12 SAMPLES.

INSET SHOWS A DIAGRAM OF A 1D OEDOMETER FOR MEASURING

COMPRESSIBILITY (LUNAR SOURCEBOOK 1991)

FIGURE 3.4.2.4.2.1-1 CHANGE IN VOID RATIO AS A FUNCTION OF APPLIED

VERTICAL STRESS. THE ARROWS INDICATE THE CHANGES IN VOID

RATIO AS THE SAMPLE IS LOADED AND THEN UNLOADED. (FIG 9.24 IN

CARRIER ET AL., 1991; LUNAR SOURCEBOOK, 1991)

FIGURE 3.4.2.4.6-1 NORMAL SHEAR STRESS VERSUS SHEAR STRENGTH. THE SLOPE

OF THE RELATION DEFINES THE FRICTION ANGLE (INSET) (MODIFIED

FROM FIGURE 9.26, LUNAR SOURCEBOOK 1991)

FIGURE 3.4.4.1-1. FIGURE 3 FROM OLHOEFT ET AL. (1974) SHOWING THE

ELECTRICAL CONDUCTIVITY VERSUS TEMPERATURE IN VACUUM FOR

LUNAR SAMPLE 12002,85 (BASALT)…………………………………………

FIGURE 3.4.4.1-2. TAKEN FROM FIGURE 4 IN OLHOEFT ET AL. (1974) IS FOR LUNAR

SAMPLE 65015,6 (HIGHLY RECRYSTALLIZED BRECCIA)…………………...260

FIGURE 3.4.4.2-1 FROM OLHOEFT AND STRANGWAY (1975) GIVES THE DIELECTRIC

CONSTANT VERSUS DENSITY WITH FITTED EQUATION FROM

REGRESSION ANALYSIS. OPEN SQUARES, TRIANGLES, AND CIRCLES ARE

DATA FROM APOLLO 11, 12, AND 14 SAMPLES, RESPECTIVELY, AND

CLOSE SQUARED, TRIANGLES AND CIRCLES ARE FROM APOLLO 15, 16,

AND 17 SAMPLES RESPECTIVELY. THIS IS FIGURE 2 IN THE OLHOEFT AND

STRANGWAY (1975) ARTICLE

FIGURE 3.4.4.2-2 RELATIVE DIELECTRIC PERMITTIVITY OF LUNAR SOIL (BLUE

CIRCLES, SAMPLE 14163 FINES) AND ROCK (ORANGE SQUARES, SAMPLE

14310) AS A FUNCTION OF FREQUENCY. THE SOIL DATA HAVE BEEN

NORMALIZED TO A DENSITY OF 1 G/CM3. FROM LUNAR SOURCEBOOK

FIGURES 9.60 AND 9.61……………………………………………………………261

FIGURE 3.4.4.3-1 LOSS TANGENT OF LUNAR SOIL (BLUE CIRCLES, SAMPLE 14163

FINES) AND ROCK (ORANGE SQUARES, SAMPLE 14310) AS A FUNCTION OF

FREQUENCY FROM LUNAR SOURCEBOOK

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FIGURE 3.4.5.1-1 HENYEY-GREENSTEIN PHASE FUNCTIONS USING THE

PARAMETERS LISTED IN TABLE 3.4.5.1-1. THE APOLLO CRYSTALLINE

VALUES ARE GIVEN TO SHOW POSSIBLE SMALL SCALE FORWARD

SCATTERING FROM ISOLATED PARTICLES. THE CRYSTALLINE

MATERIAL IS NOT SIGNIFICANT FOR ENGINEERING APPLICATIONS DUE

TO SMALL NUMBER DENSITIES

FIGURE 3.4.6.1.1-1 EQUATORIAL ALBEDO AND EMISSIVITY AS A FUNCTION OF

LONGITUDE FROM VASAVADA ET AL. 2012. THE SOLID LINE IN PANEL C

IS THE ALBEDO SMOOTHED WITH A MOVING AVERAGE OF 2O OF

LONGITUDE EVERY 0.05O. THE GRAY CURVE IS FROM THE CLEMENTINE

IMAGERY. PANEL D IS FROM DIVINER CHANNEL 7 WHICH IS NEAR THE

PEAK OF THE THERMAL EMISSIONS. THE SOLID LINE IS DATA SMOOTHED

OVER 3O OF LONGITUDE EVERY 0.05O

FIGURE 3.4.6.2.1-1 THERMAL CONDUCTIVITY VERSUS TEMPERATURE FOR

VARIOUS APOLLO SAMPLES (CREMERS AND BIRKEBACK 1971, CREMERS

ET AL. 1972, CREMERS 1972, CREMERS AND HSIA 1974)……………………271

FIGURE 3.4.6.2.2-1 REVISED ESTIMATE OF THE SPECIFIC HEAT VERSUS

TEMPERATURE OF LUNAR REGOLITH FROM WOODS-ROBINSON ET AL.

2019. THE ESTIMATE IS VALID BETWEEN 10 AND 400 K……………………272

FIGURE 3.4.6.3-1 ZONAL MEAN BOLOMETRIC TEMPERATURE AS A FUNCTION OF

LATITUDE AND 24-HOUR EQUIVALENT TIME OF DAY FROM LRO DIVINER

(FIGURE 9 (A) FROM WILLIAMS ET AL. 2017)

FIGURE 3.4.6.3-2 ZONAL MEAN BOLOMETRIC TEMPERATURE STANDARD

DEVIATION AS A FUNCTION OF LATITUDE AND 24-HOUR EQUIVALENT

TIME OF DAY FROM LRO DIVINER (FIGURE 9 (B) FROM WILLIAMS ET AL.

2017). THE LINE SYMBOLS ARE THE SAME AS FOR FIGURE 3.4.6.3-1…

FIGURE 3.4.6.4-1 TEMPERATURE AS A FUNCTION OF DEPTH AT THE APOLLO 15

AND 17 LANDING SITES (HATCHED AREAS SHOW DAY-TO-NIGHT

TEMPERATURE VARIATIONS). FROM LUNAR SOURCEBOOK: A USER’S

GUIDE TO THE MOON

FIGURE 3.4.7.3-1 DIFFERENTIAL NEUTRON FLUX FOR SOLAR MAXIMUM AND

MINIMUM CONDITIONS (ADAMS ET AL. 2007)……………………………….278

FIGURE 3.4.10-1 MULTI-TEMPORAL ILLUMINATION MAP OF THE LUNAR SOUTH

POLE, SHACKLETON CRATER (19 KM DIAMETER) IS IN THE CENTER, THE

SOUTH POLE IS LOCATED APPROXIMATELY AT 10 O'CLOCK ON ITS RIM.

MAPPED AREA EXTENDS FROM 88°S TO 90°S [NASA/GSFC/ARIZONA

STATE UNIVERSITY]

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FIGURE 3.4.10-2. MULTI-TEMPORAL ILLUMINATION MAP OF THE LUNAR NORTH

POLE. MAPPED AREA EXTENDS FROM 88°S TO 90°S [NASA/GSFC/ARIZONA

STATE UNIVERSITY]

FIGURE 3.5.18-1. CUMULATIVE DISTRIBUTIONS OF WATER SURFACE SLOPE FOR 2

M SWH

FIGURE 3.6.18-1. CUMULATIVE DISTRIBUTIONS OF WATER SURFACE SLOPE FOR 4

M SWH

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1.0 INTRODUCTION

1.1 Background

This document is derived from the former National Aeronautics and Space Administration

(NASA) Constellation Program (CxP) document CxP 70023, titled “The Design Specification for Natural Environments (DSNE), Revision C.” The original document has been modified to represent updated Design Reference Missions (DRMs) for the NASA Exploration Systems

Development (ESD) Programs.

1.2 Purpose

The DSNE completes environment-related specifications for architecture, system-level, and lower-tier documents by specifying the ranges of environmental conditions that must be accounted for by NASA ESD Programs. To assure clarity and consistency, and to prevent requirements documents from becoming cluttered with extensive amounts of technical material, natural environment specifications have been compiled into this document. The intent is to keep a unified specification for natural environments that each Program calls out for appropriate application.

1.3 Scope

This document defines the natural environments parameter limits (maximum and minimum values, energy spectra, or precise model inputs, assumptions, model options, etc.), for all ESD

Programs. These environments are developed by the NASA Marshall Space Flight Center

(MSFC) Natural Environments Branch (MSFC organization code: EV44). Many of the parameter limits are based on experience with previous programs, such as the Space Shuttle

Program. The parameter limits contain no margin and are meant to be evaluated individually to ensure they are reasonable (i.e., do not apply unrealistic extreme-on-extreme conditions).

The natural environments specifications in this document should be accounted for by robust design of the flight vehicle and support systems. However, it is understood that in some cases the

Programs will find it more effective to account for portions of the environment ranges by operational mitigation or acceptance of risk in accordance with an appropriate program risk management plan and/or hazard analysis process.

The DSNE is not intended as a definition of operational models or operational constraints, nor is it adequate, alone, for ground facilities which may have additional requirements (for example, building codes and local environmental constraints).

“Natural environments,” as the term is used here, refers to the environments that are not the result of intended human activity or intervention. It consists of a variety of external environmental factors (most of natural origin and a few of human origin) which impose restrictions or otherwise impact the development or operation of flight vehicles and destination surface systems. These natural environments include the following types of environments:

a. Terrestrial environments at launch, abort, and normal landing sites (winds, temperatures, pressures, surface roughness, sea conditions, etc.).

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b. Space environments (ionizing radiation, orbital debris, meteoroids, thermosphere density, plasma, solar, Earth, and lunar-emitted thermal radiation, etc.).

c. Destination environments (Lunar surface and orbital, Mars atmosphere and surface, near

Earth asteroids, etc.).

Many of the environmental specifications in this document are based on models, data, and environment descriptions contained in the NASA/TM 2016-218229, Natural Environment

Definition for Design (NEDD). The NEDD provides additional detailed environment data and model descriptions to support analytical studies for ESD Programs. For background information on specific environments and their effects on spacecraft design and operations, the environment models, and the data used to generate the specifications contained in the DSNE, the reader is referred to the NEDD.

Validation of the models, data, and design limits in this document are provided in Appendix B.

The intent is to provide validity of the specified natural environments for use in design assessment, which includes background of the inputs, physics, and methodology used in development of the various models and databases, as well as use in previous NASA programs.

Verification of the natural environments is accomplished by confirming the intended specifications are identified in this document. This confirmation is carried out through review by the Natural Environments Integrated Ad Hoc Team, and review, approval, and configuration control by the applicable ESD Programs.

Also, most of the environmental specifications in this document are tied specifically to the ESD

DRMs in ESD-10012, Revision E, Exploration Systems Development Concept of Operations

(ConOps). Coordination between these environment specifications and the DRMs must be maintained. This document should be compatible with the current ESD DRMs, but updates to the mission definitions and variations in interpretation may require adjustments to the environment specifications.

Table 1.3-1 provides the mapping of the DRMs in ESD-10012, Revision E to the corresponding sections in the DSNE.

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Table 1.3-1. DRM ConOps/DSNE Matrix

Exploration Systems ConOps DSNE

Section

No.

Title Section No. Title

5 Operations N/A N/A

5.1 Pre-Launch Ground Operations 3.1 Prelaunch-Ground Processing Phases

5.1.6 Pad and Launch Operations 3.1

3.2

Prelaunch-Ground Processing Phases

Launch Countdown and Earth Ascent Phases

5.1.7 Launch Scrub 3.2 Launch Countdown and Earth Ascent Phases

5.2 Ascent (Including SLS Booster

and CS Disposal)

3.2

3.5

Launch Countdown and Earth Ascent Phases

Entry and Landing Phases

5.3 Crew Operations 3.3

3.4

In-Space Phases

Lunar Surface Operational Phases

5.4 In-Space Operations 3.3 In-Space Phases

5.4.1 Earth Orbit Operations and SLS

Upper Stage Disposal

3.3 In-Space Phases

5.4.2 Lunar Transit for SLS/Orion

Missions

3.3 In-Space Phases

5.4.3 Proximity and Docking with Orion

and Orion-Dependent Co-

Manifested Payload (CPL)

3.3 In-Space Phases

5.4.4 Orion Lunar Flyby and Orbit

Insertion

3.3 In-Space Phases

5.4.5 Orion Rendezvous, Proximity

Operations, and Docking with

Target Vehicle

3.3 In-Space Phases

5.4.6 Orion Docked Operations with

Target Vehicle

3.3 In-Space Phases

5.4.7 Undocking from Target Vehicle 3.3 In-Space Phases

5.4.8 Earth Return Transit 3.3 In-Space Phases

5.5 Orion Entry, Descent, and Landing

and Recovery

3.5

3.6

3.7

Entry and Landing Phases

Contingency and Off-Nominal Landing Phases

Recovery and Post-Flight Processing Phases

5.6 Secondary Payloads Operations 3.3 In-Space Phases

5.7 Contingency Operations 3.1

3.2

3.3

3.6

Prelaunch-Ground Processing Phases

Launch Countdown and Earth Ascent Phases

In-Space Phases

Contingency and Off-Nominal Landing Phases

5.7.1 Pad Emergency Egress 3.1

3.2

Prelaunch-Ground Processing Phases

Launch Countdown and Earth Ascent Phases

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Exploration Systems ConOps DSNE

Section

No.

Title Section No. Title

5.7.2 Pad Abort for Orion Missions 3.2 Launch Countdown and Earth Ascent Phases

5.7.3 Ascent Abort for SLS Missions

with Orion

3.2 Launch Countdown and Earth Ascent Phases

5.7.4 Orbital and In-Space Aborts for

Orion Missions

3.3 In-Space Phases

5.7.5 Orion Cabin Leak and

Depressurization

3.3

5.7.6 Off-Nominal Re-Entry Orion

Crew Rescue

3.6 Contingency and Off-Nominal Landing Phases

5.7.7 Orion/Gateway Contingencies 3.3 In-Space Phases

6.1.3 Crew Lunar Transport DRM 3.3

3.4

Lunar Surface Operational Phases

1.4 Change Authority/Responsibility

The NASA Office of Primary Responsibility (OPR) for this document is EV44.

Proposed changes to this document will be submitted by a SLS Program Change Request (CR) to the appropriate SLS control board for disposition. The CR process is described in SLS-PLAN-

008, SLSP Configuration Management Plan (CMP).

Proposed changes to this document should be vetted through the Cross-Program Natural

Environments Integration Ad-Hoc Team (NEIAHT) prior to the submission of an SLS Program

CR. Requests for clarification, interpretation, or questions concerning this document should be addressed to the Cross-Program NEIAHT, or the MSFC Natural Environments Branch.

2.0 DOCUMENTS

2.1 Applicable Documents, Models, and Data Sets

2.1.1 Applicable Documents

The following data items include specifications, models, standards, guidelines, handbooks, and other special publications. The data items listed in this paragraph are applicable in the current approved baseline as specified in the SLS Master List of Baselined Data Items to the extent specified herein. Specific revisions of SLS controlled or jointly controlled documents will not be annotated unless required to specify the boundaries of an incorporated agreement or requirement.

Data items not controlled by SLS will be annotated by revision.

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Document

Number

Document

Revision

Document Title

ESD 10012 F Exploration Systems Development Concept of

Operations

MIL-STD-810 G, Change 1 Test Method Standard for Environmental

Engineering Considerations and Laboratory Tests

MPCV 70024 C Orion MPCV Program Human-Systems Integration

Requirements

SAE ARP5412 B Aircraft Lightning Environment and Related Test

Waveforms

SAE ARP5414 A Aircraft Lightning Zoning

GP 10017 Baseline Gateway Human Systems Requirements (HSR)

2.1.2 Applicable Models/Data Sets

The following models and data bases are used for specifications. Their application is described in the appropriate sections of this document.

Model/Data Set

Identification

Model/Data Set

Name/Description

Earth-GRAM Earth Global Reference Atmosphere Model (GRAM)

As of January 1, 2012 the latest version of this model is

Earth-GRAM 2010. Any previous analyses performed using a prior version do not require rework.

GGM02C Gravity Recovery and Climate Experiment (GRACE)

Gravity Model 02 C

GRAIL Gravity Recovery and Interior Laboratory (GRAIL)

Lunar Gravity Model

MEM 3 Meteoroid Engineering Model 3

ORDEM 3.1 Orbital Debris Engineering Model 3.1

KSC Jimsphere Wind Profile

Database

Kennedy Space Center Jimsphere Wind Profile

Database

MVWPM Monthly Vector Wind Profile Model

KSC Ground Wind Models Kennedy Space Center Ground Wind Models

KSC Doppler Radar Wind Profiler

Database

Kennedy Space Center Doppler Radar Wind Profiler

Database

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Model/Data Set

Identification

Model/Data Set

Name/Description

IRENE International Radiation Environment Near Earth

(AE9/AP9/SPM [Standard Plasma Model])

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3.0 NATURAL ENVIRONMENT SPECIFICATION

3.1 Prelaunch – Ground Processing Phases

3.1.1 Transportation Environments to the Launch Site KSC (Reserved)

Description

This section is reserved for special environmental requirements for shipping flight hardware to

Kennedy Space Center (KSC) not covered by other standard shipping requirements documents.

Examples might include monitoring for lightning discharge or electromagnetic irradiation and monitoring of temperature and pressure extremes. At this time, no special requirements have been identified.

Design Limits

Maximum: Reserved

Minimum: Reserved

Model Inputs

Reserved

Limitations

Reserved

Technical Notes

Reserved

3.1.2 Reserved

3.1.3 Ground Winds for Transport and Launch Pad Environments

Description

This section specifies ground wind environments (altitude range 0 to 150 meters (m) [0 to 492 feet (ft)]), up to and including the maximum design limits for flight hardware that will be exposed during ground operations at KSC, including transportation to and from the pad and on-pad operations. Design specifications include peak wind-speed profile, steady state wind-speed profile, frequency of occurrence of peak winds, and spectral gust environments. “Storage” applies to on-pad or outside storage only.

Design Limits

Table 3.1.3-1 provides the design peak wind profiles, in meters per second (m/s) and feet per second (ft/s), for the various operational phases at selected altitudes. The design steady state wind profiles associated with the design peak wind profiles are provided in Table 3.1.3-2. The steady state wind profile is that profile that could produce the instantaneous peak winds (gusts)

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in Table 3.1.3-1, over a 10-minute period. Peak wind profile values between those altitudes given in Tables 3.1.3-1 are determined by:

𝑢(𝑧) = 𝑢18.3 ( 𝑧

18.3 1.6(𝑢18.3)

−3 4⁄ where u(z) is the peak wind (m/s) at height z (m) and u18.3 is the peak wind speed (m/s) at 18.3 m.

Steady state profile values between those altitudes given in Table 3.1.3-2 are determined by:

𝑈̅(𝑧) = 𝑢(𝑧)

1 + (

18.3 𝑧 (0.283−0.435𝑒−0.2𝑢18.3)

1.98 − 1.887𝑒−0.2𝑢18.3

−1 where u(z) is the peak wind (m/s) at height z (m) and u18.3 is the peak wind (m/s) at 18.3 m. Note that metric units (m/s and m) must be used in the above two equations. Once u(z) and 𝑈̅(z) are determined, they can be converted to English units (ft/s).

Table 3.1.3-1. Design Peak Wind-Speed Profile

Height Peak Wind-Speed Profile

Transport To/From Pad On-Pad (Unfueled)

On-Pad

(Intermediate and Fully

Fueled) m ft m/s ft/s m/s ft/s m/s ft/s

10 32 28.6 93.8 36.0 118.1 22.1 72.5

18.3 60 30.8 101.1 38.3 125.7 24.2 79.4

30 98 32.7 107.3 40.3 132.2 26.0 85.3

60 197 35.6 116.8 43.3 142.1 28.8 94.5

90 295 37.4 122.7 45.2 148.3 30.6 100.4

120 394 38.8 127.3 46.6 152.9 31.8 104.3

150 492 39.8 130.6 47.7 156.5 32.9 107.9

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Table 3.1.3-2. Steady State Wind-Speed Profile Associated with the Design Peak Wind- Speed Profile

Height Steady State Wind-Speed Profile

Transport To/From Pad On-Pad (Unfueled)

On-Pad

(Intermediate and Fully

Fueled) m ft m/s ft/s m/s ft/s m/s ft/s

10 32 17.9 58.7 22.5 73.8 13.8 45.3

18.3 60 20.5…