SSP41017p1rG.pdf

SSP 41017

Rack to Mini Pressurized Logistics Module Interface Control Document

(ICD)

Part 1

Revision G

National Aeronautics and Space Administration International Space Station Program Johnson Space Center Houston, Texas Contract No. NAS15−10000

International Space Station Program esa european space agency

February 4th, 2005

Japan Aerospace Exploration Agency

SSP 41017, Part 1 February 4, 2004 Revision G

REVISION AND HISTORY PAGE

REV. DESCRIPTION PUB.

DATE

− Initial Release (Reference per SSCBD 000293, EFF. 05/10/96) 06/12/96

The Following PIRNs were agreed to and incorporated into this Initial Release;

41017−AS−0001A

41017−AS−0005B

41017−NA−0001E

41017−NA−0002D

41017−NA−0007

A Revision A (REFERENCE PIRN ES−0006A, NA−0008B, NA−0014, NA−0016A, NA−0018, ND−0003B, NA−0010A, AS−0011B) (Reference per SSCD 000403, EFF. 10/04/96) 04/16/98

B Revision B (REFERENCE PIRN, AS−0013B, AS−0014D, AS−0015C, NA−0021E, NA−0023D) (Reference per SSCD 000607, EFF. 01/08/98) 08/19/98

C Revision C (REFERENCE SSCD 000988, EFF. 07/26/00 ) (Reference per PIRNs

AS−0016, AS−0017C, NA−0026A, NA−0027, NA−0028B, NA−0030B) 04/06/01

IRN 41017−0343 (Reference SSCN 000343, EFF. 07/09/98) 04/06/01

D Revision D (REFERENCE SSCD 001809, EFF. 08/01/00) 04/10/01

Incorporates the following PIRNs associated with the appropriate SSCNs.

PIRN 41017-ES−0007F IRN N/A SSCN 001809

PIRN 41017-NA−0024H IRN N/A SSCN 001809

PIRN 41017-NA−0032B IRN N/A SSCN 001809

PIRN 41017-NA−0037B IRN N/A SSCN 001809

PIRN 41017-NA−0038A IRN N/A SSCN 001809

PIRN 41017-NA−0039A IRN N/A SSCN 001809

PIRN 41017-NA−0041 IRN N/A SSCN 001809

PIRN 41017-ND−0005C IRN N/A SSCN 001809

Revision D accounts for impacts identified in the following SSCNs: 000845, 000591, 000583, 000773, 001004, 000832, 000440, 000671, 000877, 000915, 000844, 001029, 001051, 001052, 001026, 000470, 000823, 000673, 000585, 000588, 000600, 000567 001127, and 000554.

Revision D also closes IRN 0346 for SSCN 000346 as the PIRN 41017−NA−0017 was withdrawn and IRN 0074 for SSCN 000074 as the PIRN 41017−NA−0009A was withdrawn.

REVISION AND HISTORY PAGE − Continued

REV. DESCRIPTION PUB.

DATE

E Revision E (Reference SSCD 003760, EFF. 06/30/00) 01/31/02

Incorporates the following PIRNs associated with the appropriate SSCNs

PIRN 41017−NA−0036A IRN N/A SSCN 003760

PIRN 41017-NA−0043B IRN N/A SSCN 003760

PIRN 41017−NA−0051C IRN N/A SSCN 003760

PIRN 41017−NA−0052 IRN N/A SSCN 003760

PIRN 41017−NA−0053C IRN N/A SSCN 003760

PIRN 41017−NA−0055A IRN N/A SSCN 003760

PIRN 41017-NA−0044G IRN 0006 SSCN 001959

F Revision F (Reference SSCD 005508, EFF 5/18/01) 01/31/02

Incorporates the following PIRNs associated with the appropriate SSCNs

PIRN 41017−AS−0018F IRN N/A SSCN 005508

PIRN 41017−NA−0050H IRN N/A SSCN 005508

PIRN 41017−ND−0008B IRN N/A SSCN 005508

PIRN 41017−NA−0054 IRN 0011 SSCN 003011

G Revision G (Reference SSCN 008198 EFF 11/08/05) 11/28/05

Incorporates the following PIRNs associated with the appropriate SSCNs:

PIRN 41017−NA−0060C IRN N/A SSCN 008198

PIRN 41017−NA−0061B IRN N/A SSCN 008198

PIRN 41017−NA−0064A IRN N/A SSCN 008198

Revision G closes the following SSCN actions for SSP 41017 Part 1 as those SSCNs have been evaluated and it has been determined that they are of no impact to this ICD:

PIRN N/A IRN 0001 SSCN 001662

PIRN N/A IRN 0002 SSCN 001920

PIRN N/A IRN 0003 SSCN 002107

PIRN N/A IRN 0004 SSCN 002345

PIRN N/A IRN 0005 SSCN 003213

PIRN N/A IRN 0007 SSCN 003690

PIRN N/A IRN 0008 SSCN 003746

PIRN N/A IRN 0009 SSCN 004676

Revision C also closes the actions for SSCN 002877 (IRN 0010), SSCN 000889 (IRN N/A), SSCN 001594 (IRN N/A), and SSCN 001386 (IRN N/A) as they have been overcome by events.

ERU: /s/Beth Mason 11−28−05 i

PREFACE

The contents of this document are intended to be consistent with the tasks and products to be prepared by Program participants. The SSP 41017 Rack to Mini Pressurized Logistics Module Interface Control Document Part 1, shall be implemented on all new ISS contractual and internal activities and shall be included in any existing contracts through contract changes. This document is under the control of the Space Station Control Board, and any changes or revisions will be approved by the Program Manager (or statement to indicate the delegated authority).

ii

INTERNATIONAL SPACE STATION PROGRAM

RACK TO MINI PRESSURIZED LOGISTICS MODULE

INTERFACE CONTROL DOCUMENT PART 1, REVISION G

LIST OF CHANGES

FEBRUARY 4, 2005

All changes to paragraphs, tables, and figures in this document are shown below:

SSCBD ENTRY DATE CHANGE PARAGRAPH(S)

000403 AS−0011B 3.2.1.4.4

ES−0006A PARAGRAPH(S)

2.0

3.2.1.2

3.2.2.2

3.2.2.3.5

APPENDIX

A1

NA−0008B FIGURES

3.2.1.1.1−1

3.2.1.1.1−2

NA−0010A PARAGRAPHS

3.2.1.4.2

NA−0014 PARAGRAPHS

4.0

NA−0016A PARAGRAPHS

2.0

NA−0018 PARAGRAPHS

Delete Issue Sheets

ND−0003B PARAGRAPHS

3.2.1.1.2

FIGURES

3.2.1.1.2−1

3.2.1.1.2−2

3.2.1.1.2−3 iii

INTERNATIONAL SPACE STATION PROGRAM

RACK TO MINI PRESSURIZED LOGISTICS MODULE

INTERFACE CONTROL DOCUMENT PART 1, REVISION G

LIST OF CHANGES

FEBRUARY 4, 2005

SSCBD ENTRY DATE CHANGE PARAGRAPH(S)

000607 AS−0013B 3.2.1.3.4

3.2.2.3.5

AS−0014D PARAGRAPH(S)

3.2.1.4.2

3.2.1.4.3

3.2.2.4.3

TABLE(S)

3.2.1.4.2−1

3.2.1.4.2−2

3.2.1.4.3−1

AS−0015C PARAGRAPH(S)

4.0

TABLE(S)

4.0−1 (add)

NA−0021E FIGURE(S)

3.2.1.1.2−1

3.2.1.1.2−2

NA−0023D FIGURE(S)

3.2.1.1.2−4

3.2.1.1.2−5

3.2.1.1.2−6

000988 AS−0016 PARAGRAPH(S)

3.2.1.4.4 iv

INTERNATIONAL SPACE STATION PROGRAM

RACK TO MINI PRESSURIZED LOGISTICS MODULE

INTERFACE CONTROL DOCUMENT PART 1, REVISION G

LIST OF CHANGES

FEBRUARY 4, 2005

SSCBD ENTRY DATE CHANGE PARAGRAPH(S)

AS−0017C TABLE(S)

3.2.1.4.1.1−1

3.2.2.4.1.1−1

PARAGRAPH(S)

3.2.1.4.1.1

3.2.2.4.1.1

NA−0026A PARAGRAPH(S)

2.0

2.1

NA−0027 PARAGRAPH(S)

Add to Concurrence Sheet

NA−0028B FIGURE(S)

3.2.1.1.2−1

3.2.1.1.2−2

NA−0030B PARAGRAPH(S)

3.2.1.3.3

000343 NA−0015A PARAGRAPH(S)

3.2.1.1.1

3.2.1.1.2

3.2.2.1.1

3.2.2.1.2

FIGURE(S)

3.2.1.1.1−4 3.2.1.1.1−5 3.2.1.1.1−6 3.2.1.1.2−3 3.2.1.1.2−4 3.2.1.1.2−5 v

INTERNATIONAL SPACE STATION PROGRAM

RACK TO MINI PRESSURIZED LOGISTICS MODULE

INTERFACE CONTROL DOCUMENT PART 1, REVISION G

LIST OF CHANGES

FEBRUARY 4, 2005

SSCBD ENTRY DATE CHANGE PARAGRAPH(S)

001809 ES−0007F 3.2.1.1.1

FIGURE(S)

3.2.1.1.1−6

3.2.1.1.1−7

3.2.1.1.1−8

NA−0024H PARAGRAPH(S)

3.2.1.1.2

FIGURE(S)

3.2.1.1.2−7

3.2.1.1.2−8

3.2.1.1.2−9

NA−0032 FIGURE(S)

3.2.1.1.2−2

NA−0037B PARAGRAPH(S)

3.2.2.3.6

NA−0038A FIGURE(S)

3.2.1.1.1−1

NA−0039A FIGURE(S)

3.2.1.1.2−7

3.2.1.1.2−10

NA−0041 3.2.2.3.1.1

3.2.2.3.1.2

FIGURE(S)

3.2.1.1.1−3

TABLE(S)

3.2.1.4.3−1 vi

INTERNATIONAL SPACE STATION PROGRAM

RACK TO MINI PRESSURIZED LOGISTICS MODULE

INTERFACE CONTROL DOCUMENT PART 1, REVISION G

LIST OF CHANGES

FEBRUARY 4, 2005

SSCBD ENTRY DATE CHANGE PARAGRAPH(S)

ND−0005C 3.2.1.4.2

3.2.1.4.3

TABLE(S)

3.2.1.4.2−1

3.2.1.4.2−2

3.2.1.4.2−3

3.2.1.4.3−1

3.2.1.4.3−2

3.2.1.4.3−3

003760 NA−0036A TABLE (S)

3.2.1.4.1.2−1

NA−0043B FIGURE(S)

3.2.1.1.2−1

3.2.1.1.2−2

NA−0051C FIGURE(S)

3.2.1.1.2−7

NA−0052 PARAGRAPH(S)

3.2.1.4.4

NA−0053C PARAGRAPH(S)

3.2.1.2

3.2.1.2.1 (ADD)

3.2.1.2.2 (ADD)

3.2.2.2

NA−0055A TABLE(S)

3.2.1.4.2−1

001959 NA−0044G TABLE(S)

3.2.1.4.3−1 vii

INTERNATIONAL SPACE STATION PROGRAM

RACK TO MINI PRESSURIZED LOGISTICS MODULE

INTERFACE CONTROL DOCUMENT PART 1, REVISION G

LIST OF CHANGES

FEBRUARY 4, 2005

SSCBD ENTRY DATE CHANGE TABLE(S)

005508 AS−0018F 3.2.1.4.2−1

3.2.1.4.3−1

NA−0050H FIGURE(S)

3.2.1.1.2−1 3.2.1.1.2−2

ND−0008B PARAGRAPH(S)

3.2.1.1.2

FIGURE(S)

3.2.1.1.2−11 (Page 1 of 5) (ADD) 3.2.1.1.2−11 (Page 2 of 5) (ADD) 3.2.1.1.2−11 (Page 3 of 5) (ADD) 3.2.1.1.2−11 (Page 4 of 5) (ADD) 3.2.1.1.2−11 (Page 5 of 5) (ADD) 3.2.1.1.2−12 (Page 1 of 4) (ADD) 3.2.1.1.2−12 (Page 2 of 4) (ADD) 3.2.1.1.2−12 (Page 3 of 4) (ADD) 3.2.1.1.2−12 (Page 4 of 4) (ADD)

003011 NA−0054 TABLE(S)

3.2.1.4.3−1

008198 7/03 NA−0060C PARAGRAPH(S)

3.2.1.1.1, 3.2.1.1.2, 3.2.2.1.1, 3.2.2.1.2,

3.2.2.3.7 (ADD)

FIGURE(S)

3.2.1.1.2−13, 3.2.1.1.2−14, 3.2.1.1.2−15, 3.2.1.1.2−16, 3.2.1.1.2−17, 3.2.1.1.2−18

(ADDS)

008198 10/03 NA−0061B FIGURE(S)

3.2.1.1.2−1, 3.2.1.1.2−2 viii

INTERNATIONAL SPACE STATION PROGRAM

RACK TO MINI PRESSURIZED LOGISTICS MODULE

INTERFACE CONTROL DOCUMENT PART 1, REVISION G

LIST OF CHANGES

FEBRUARY 4, 2005

SSCBD ENTRY DATE CHANGE

008198 02/05 NA−0064A COVER

008198 02/05 NA−0064A PREFACE

008198 02/05 NA−0064A CONCURRENCE(S)

008198 02/05 NA−0064A PARAGRAPHS(S)

2.0, 2.1, 3.2.1.4.2, 3.2.1.4.3, 3.2.2.4.3

008198 02/05 NA−0064A TABLES(S)

3.2.1.4.2−2, 3.2.1.4.2−3, 3.2.1.4.3−3, 4.0

008198 02/05 NA−0064A FIGURE(S)

3.2.1.1.1−3, 3.2.1.1.1−1, 3.2.1.1.1−2, 3.2.1.1.2−2, 3.2.1.1.2−3, 3.2.1.1.2−9, 3.2.1.1.2−16

008198 02/05 NA−0064A APPENDIX A

ix

NASA/JAXA/ESA/ASI APPROVAL

INTERNATIONAL SPACE STATION PROGRAM

RACK TO MINI PRESSURIZED LOGISTICS MODULE

INTERFACE CONTROL DOCUMENT

FEBRUARY 4, 2005

Date

Print Name

NASA Program Manager JAXA Program Manager

Print Name

Date

Date

Print Name

ESA Program Manager ASI Program Manager

Print Name

Date

See Directive

See Directive

See Directive

See Directive x

INTERNATIONAL SPACE STATION PROGRAM

RACK TO MINI PRESSURIZED LOGISTICS MODULE

INTERFACE CONTROL DOCUMENT, PART 1

FEBRUARY 4, 2005

CONCURRENCE

Warren England Boeing

PREPARED BY: PRINT NAME ORGN

/s/ Warren England 4/13/05

SIGNATURE DATE

CHECKED BY (BOEING): Quentin Henry Boeing

SIGNATURE DATE

/s/ Quentin L. Henry 4/13/05

SIGNATURE DATE

DQA BY: Merry McClain Boeing

PRINT NAME ORGN

/s/ Merry McClain 4/13/05

SIGNATURE DATE

APPROVED BY

NASA ICWG CHAIR: Chau Hong NASA/OM

PRINT NAME ORGN

/s/ Chau Hong 6/5/2005

SIGNATURE DATE

TABLE OF CONTENTS

PARAGRAPH PAGE

xi

1.0 INTRODUCTION 1 - 1

1.1 PURPOSE AND SCOPE 1 - 1

1.2 PRECEDENCE 1 - 1

1.3 RESPONSIBILITY AND CHANGE AUTHORITY 1 - 1

2.0 APPLICABLE DOCUMENTS 2 - 1

2.1 REFERENCE DOCUMENTS 2 - 1

3.0 INTERFACES 3 - 1

3.1 GENERAL 3 - 1

3.1.1 INTERFACE DESCRIPTION 3 - 1

3.1.1.1 ISPR DESCRIPTION 3 - 1

3.1.1.2 MODULE DESCRIPTION 3 - 1

3.1.1.3 ISPR INTERFACE FUNCTIONS 3 - 1

3.1.1.4 MODULE INTERFACE FUNCTIONS 3 - 1

3.1.2 INTERFACE RESPONSIBILITIES 3 - 1

3.1.2.1 RESPONSIBILITY FOR ISPR 3 - 1

3.1.2.2 RESPONSIBILITY FOR MODULE 3 - 1

3.1.3 ENGINEERING UNITS, TOLERANCES, AND CONVERSIONS 3 - 2

3.1.3.1 ENGINEERING UNITS 3 - 2

3.1.3.2 TOLERANCES AND CONVERSIONS 3 - 2

3.2 INTERFACE REQUIREMENTS 3 - 2

3.2.1 ISPR INTERFACE REQUIREMENTS 3 - 2

3.2.1.1 ENVELOPE REQUIREMENTS 3 - 2

3.2.1.1.1 DYNAMIC ENVELOPE 3 - 2

3.2.1.1.2 RACK STATIC ENVELOPE 3 −11

3.2.1.2 MASS PROPERTIES 3 - 11

3.2.1.2.1 LAUNCH/LANDING/GROUND HANDLING MASS 3 - 11

3.2.1.2.2 ON ORBIT MASS 3 - 11

3.2.1.3 STRUCTURAL/MECHANICAL 3 - 11

3.2.1.3.1 LAUNCH/LANDING/ON−ORBIT ATTACHMENT 3 - 11

3.2.1.3.2 GROUND HANDLING ATTACHMENT 3 - 11

3.2.1.3.3 ISPR MINIMUM RESONANT FREQUENCY 3 - 11

3.2.1.3.4 BONDING 3 - 12

3.2.1.4 INDUCED ENVIRONMENTS 3 - 12

3.2.1.4.1 VIBRATION 3 - 12

3.2.1.4.1.1 LAUNCH ACOUSTICS 3 - 12

3.2.1.4.1.2 RANDOM VIBRATION 3 - 41

3.2.1.4.2 ACCELERATION 3 - 41

3.2.1.4.3 INTERFACE LOADS 3 - 43

3.2.1.4.4 RACK DIFFERENTIAL PRESSURE 3 − 46

3.2.2 MPLM INTERFACE REQUIREMENTS 3 − 46

3.2.2.1 ENVELOPE REQUIREMENTS 3 − 46

3.2.2.1.1 DYNAMIC ENVELOPE 3 − 47

3.2.2.1.2 MPLM ACCOMMODATION OF RACK 3 − 47

3.2.2.2 MASS PROPERTIES 3 − 47

TABLE OF CONTENTS − Continued

PARAGRAPH PAGE

xii

3.2.2.3 STRUCTURAL/MECHANICAL 3 − 48

3.2.2.3.1 LAUNCH/LANDING/ON−ORBIT ATTACHMENT 3 − 48

3.2.2.3.1.1 ON−ORBIT MODULAR ATTACHMENT 3 − 48

3.2.2.3.1.2 RACK TO MODULE INTERFACE 3 − 48

3.2.2.3.2 GROUND HANDLING ATTACHMENT 3 − 48

3.2.2.3.3 MINIMUM RESONANT FREQUENCY 3 − 48

3.2.2.3.4 DELETED 3 − 48

3.2.2.3.5 BONDING (MPLM ONLY) 3 − 48

3.2.2.3.6 ARIS RACK COMPATIBILITY 3 − 48

3.2.2.3.7 PaRIS RACK COMPATIBILITY 3 − 48

3.2.2.4 INDUCED ENVIRONMENTS 3 − 48

3.2.2.4.1 VIBRATION 3 − 49

3.2.2.4.1.1 LAUNCH ACOUSTICS 3 − 49

3.2.2.4.1.2 RANDOM VIBRATION 3 − 49

3.2.2.4.2 ACCELERATION 3 − 49

3.2.2.4.3 INTERFACE LOADS 3 − 49

4.0 INTERFACE VERIFICATION 4 −1

APPENDIX

A ABBREVIATIONS AND ACRONYMS A−1

B INDEX OF TBDS AND TBCS 4 −1

TABLE OF CONTENTS − Continued

TABLE PAGE

TABLES

xiii

3.2.1.4.1.1−1 MPLM ACOUSTIC NOISE SPECTRA 3 - 12

3.2.1.4.1.2−1 MPLM RANDOM VIBRATION ENVIRONMENT 3 - 41

3.2.1.4.2−1 NASA RACK ACCELERATION (MAXIMUM PREDICTED LEVEL) 3 - 42

3.2.1.4.2−2 IHI PAYLOAD RACK ACCELERATIONS (MAXIMUM PREDICTED

LEVEL) 3 - 42

3.2.1.4.2−3 MHI SYSTEM RACK ACCELERATIONS (MAXIMUM PREDICTED

LEVEL) 3 - 42

3.2.1.4.3−1 MINI PRESSURIZED LOGISTICS MODULE AND MECHANICAL GROUND

SUPPORT EQUIPMENT LOCAL RACK ATTACH POINT DESIGN LIMIT LOADS

(LAUNCH, LANDING, ON−ORBIT AND GROUND

HANDLING) (PAGE 1 OF 2) 3 − 44

3.2.1.4.3−1 MINI PRESSURIZED LOGISTICS MODULE AND MECHANICAL GROUND

SUPPORT EQUIPMENT LOCAL RACK ATTACH POINT DESIGN LIMIT LOADS

(LAUNCH, LANDING, ON−ORBIT AND GROUND

HANDLING) (PAGE 2 OF 2) 3 − 45

3.2.1.4.3−2 MPLM RACK INTERFACE LOADS ON NASA RACKS DUE TO DIFFERENTIAL

PRESSURE (APPLICABLE FOR LANDING ONLY) 3 − 46

3.2.1.4.3−3 MPLM RACK INTERFACE LOADS ON MHI/IHI RACKS DUE TO

DIFFERENTIAL PRESSURE (APPLICABLE FOR LANDING ONLY) 3 − 46

4.0−1 INTERFACE VERIFICATION 4 −2

TABLE OF CONTENTS − Continued

FIGURE PAGE

FIGURES

xiv

FIGURES

3.2.1.1.1−1 RACK DYNAMIC ENVELOPE (SIDE VIEW) 3 - 3

3.2.1.1.1−2 RACK DYNAMIC ENVELOPE (FRONT VIEW) 3 - 4

3.2.1.1.1−3 RACK ATTACH POINT DESCRIPTIONS 3 - 5

3.2.1.1.1−4 RACK DYNAMIC ENVELOPE (DETAIL AT ATTACH POINTS A AND B)

APPLICABLE ONLY TO RACKS LAUNCHED IN THE US LAB 3 - 6

3.2.1.1.1−5 RACK DYNAMIC ENVELOPE (BACK VIEW DETAIL) APPLICABLE ONLY

TO RACKS LAUNCHED IN U.S. LAB 3 - 7

3.2.1.1.1−6 ARIS RACK LAUNCH/LANDING DYNAMIC ENVELOPE

(SIDE VIEW) 3 - 8

3.2.1.1.1−7 ARIS RACK LAUNCH/LANDING DYNAMIC ENVELOPE (BACK

VIEW) 3 - 9

3.2.1.1.1−8 ARIS RACK LAUNCH/LANDING DYNAMIC ENVELOPE (BOTTOM

VIEW) 3 - 10

3.2.1.1.2−1 RACK STATIC ENVELOPE (SIDE VIEW) 3 - 13

3.2.1.1.2−2 RACK STATIC ENVELOPE (FRONT VIEW) (PAGE 1 OF 2) 3 - 14

3.2.1.1.2−2 RACK STATIC ENVELOPE (FRONT VIEW) (PAGE 2 OF 2) APPLICABLE

ONLY TO RACKS FLOWN IN US LAB 3 - 15

3.2.1.1.2−3 RACK STATIC ENVELOPE (TOP VIEW) 3 - 16

3.2.1.1.2−4 RACK STATIC ENVELOPE (DETAIL AT ATTACH POINTS A AND B)

APPLICABLE ONLY TO RACKS FLOWN IN US LAB 3 - 17

3.2.1.1.2−5 RACK STATIC ENVELOPE (SIDE VIEW DETAIL) APPLICABLE TO RACKS

FLOWN IN US LAB ONLY 3 - 18

3.2.1.1.2−6 RACK STATIC ENVELOPE (SIDE VIEW DETAIL) APPLICABLE TO RACKS

FLOWN IN ALL MODULES EXCEPT US LAB 3 - 19

3.2.1.1.2−7 ARIS RACK LAUNCH/LANDING STATIC ENVELOPE (SIDE VIEW)

(PAGE 1 OF 2) 3 - 20

3.2.1.1.2−7 ARIS RACK LAUNCH/LANDING STATIC ENVELOPE (SIDE VIEW)

(PAGE 2 OF 2) 3 - 21

3.2.1.1.2−8 ARIS RACK LAUNCH/LANDING STATIC ENVELOPE (BACK VIEW) 3 - 22

3.2.1.1.2−9 ARIS LAUNCH/LANDING RACK STATIC ENVELOPE DETAIL (BOTTOM

VIEW) PAGE 1 OF 2 3 - 23

3.2.1.1.2−9 ARIS RACK LAUNCH/LANDING STATIC ENVELOPE DETAIL

PAGE 2 OF 2 3 - 24

3.2.1.1.2−10 ARIS RACK STATIC ENVELOPE KNEE BRACE INTRUSION DETAILS

(TOP VIEW) (NASA−ASI ONLY) 3 - 25

3.2.1.1.2−11 RACK STATIC ENVELOPE (APPLICABLE ONLY TO RACKS IN JEM −PM)

(SIDE VIEW) (PAGE 1 OF 5) 3 - 26

3.2.1.1.2−11 RACK STATIC ENVELOPE (APPLICABLE ONLY TO RACKS IN JEM −PM)

(BACK VIEW) (PAGE 2 OF 5) 3 - 27

3.2.1.1.2−11 RACK STATIC ENVELOPE (APPLICABLE ONLY TO RACKS IN JEM −PM)

(DETAIL D FOR SECTION X−X) (PAGE 3 OF 5) 3 - 28

3.2.1.1.2−11 RACK STATIC ENVELOPE (APPLICABLE ONLY TO RACKS IN JEM −PM)

(DETAIL D FOR SECTION Y−Y) (PAGE 4 OF 5) 3 - 29

TABLE OF CONTENTS − Continued

FIGURE PAGE

FIGURES

xv

3.2.1.1.2−11 RACK STATIC ENVELOPE (APPLICABLE ONLY TO RACKS IN JEM −PM)

(DETAIL E) (PAGE 5 OF 5) 3 - 30

3.2.1.1.2−12 RACK STATIC ENVELOPE APPLICABLE ONLY TO RACKS IN ELM−PS

(SIDE VIEW) (PAGE 1 OF 4) 3 - 31

3.2.1.1.2−12 RACK STATIC ENVELOPE APPLICABLE ONLY TO RACKS IN ELM−PS

(BACK VIEW) (PAGE 2 OF 4) 3 - 32

3.2.1.1.2−12 RACK STATIC ENVELOPE APPLICABLE ONLY TO RACKS IN ELM−PS

(DETAIL F FOR SECTION X−X) (PAGE 3 OF 4) 3 - 33

3.2.1.1.2−12 RACK STATIC ENVELOPE APPLICABLE ONLY TO RACKS IN ELM−PS

(DETAIL F FOR SECTION Y−Y) (PAGE 4 OF 4) 3 - 34

3.2.1.1.2−13 PaRIS RACK LAUNCH/LANDING STATIC ENVELOPE (SIDE VIEW) 3 - 35 3.2.1.1.2−14 PaRIS RACK LAUNCH/LANDING STATIC ENVELOPE

(FRONT VIEW) 3 - 36

3.2.1.1.2−15 PaRIS RACK LAUNCH/LANDING STATIC ENVELOPE (TOP VIEW) 3 - 37 3.2.1.1.2−16 PaRIS LAUNCH/LANDING STATIC ENVELOPE (LOWER ISOMETRIC VIEW) 3 - 38 3.2.1.1.2−17 PaRIS RACK LAUNCH/LANDING STATIC ENVELOPE (BOTTOM

VIEW DETAIL) 3 - 39

3.2.1.1.2−18 PaRIS RACK LAUNCH/LANDING STATIC ENVELOPE (BOTTOM

VIEW SECTION DETAIL) 3 - 40

1 - 1

1.0 INTRODUCTION

1.1 PURPOSE AND SCOPE

The purpose of this document is to provide definition of the physical, functional, and environmental requirements between the Mini Pressurized Logistics Module (MPLM) and racks which conform to the interfaces of the International Standard Payload Rack (ISPR), and between the Ground Support Equipment (GSE) and racks which conform to the interfaces of the ISPR.

The scope of this document is limited to the structural/mechanical interfaces between the MPLM and the ISPR that support the launch/landing/on−orbit event, and between the GSE and the ISPR that support the ground handling event.

1.2 PRECEDENCE

In the event of conflict between SSP 41000, Space Station System Specification, and the contents of this ICD, only the requirements of SSP 41000 applicable to each International Partner and to the National Aeronautics and Space Administration (NASA) shall take precedence.

1.3 RESPONSIBILITY AND CHANGE AUTHORITY

This document is prepared and maintained in accordance with SSP 30459, International Space Station Interface Control Plan. The Prime Contractor shall delegate the responsibility for preparation and maintenance of this ICD.

2 - 1

2.0 APPLICABLE DOCUMENTS

The following documents of the exact issue form a part of this document to the extent specified herein.

SSP 30245 Space Station Electrical Bonding Requirements Rev. B, 3 Jun, 1994 Reference Paragraph 3.2.1.3.4; 3.2.2.3.5

ASTM E380 Standard Practice for Use of the International System of Rev. A, 1993 Units (SI) (the Modernized Metric System) Reference Paragraph 3.1.3.2

COL−RQ−ESA−014 Columbus Electromagnetic Compatibility Requirements (Applicable to APM only)

Issue 2, Rev., B 15. Dec 95 Reference Paragraph 3.2.2.3.5

2.1 REFERENCE DOCUMENTS

The following documents are referenced in this ICD for context and user convenience:

SSP 30459 International Space Station Interface Control Plan Reference Paragraph 1.3

SSP 41000 Space Station System Specification Reference Paragraph 1.2

3 - 1

3.0 INTERFACES

3.1 GENERAL

3.1.1 INTERFACE DESCRIPTION

3.1.1.1 ISPR DESCRIPTION

The International Standard Payload Rack (ISPR) interfaces to the Mini Pressurized Logistics Module (MPLM) and to the Ground Support Equipment (GSE) will be physically identical and functionally compatible without the use of hardware adapters. The ISPR interfaces to the MPLM consist of structural/mechanical attachment for the launch/landing/on−orbit event. The ISPR interfaces to the GSE consist of structural/mechanical attachment for the ground handling event.

3.1.1.2 MODULE DESCRIPTION

Regardless of ISPR provider and without the use of hardware adapters the MPLM will support ISPR structural/mechanical attachment for the launch/landing/on−orbit event.

3.1.1.3 ISPR INTERFACE FUNCTIONS

The ISPR will support the following function at the interface with the MPLM and the GSE:

A. Structural/Mechanical Attachment

3.1.1.4 MODULE INTERFACE FUNCTIONS

The MPLM will support the following function at the interface to ISPRs:

A. Launch/landing/on−orbit Structural/Mechanical Attachment

3.1.2 INTERFACE RESPONSIBILITIES

3.1.2.1 RESPONSIBILITY FOR ISPR

The ISPR designer will ensure that the ISPR conforms to the interface requirements contained within this document.

3.1.2.2 RESPONSIBILITY FOR MODULE

Agenzia Spaziale Italiana (Italian Space Agency) (ASI) will ensure that dedicated ISPR locations within the MPLM conform to the interface requirements contained within this document.

3 - 2

3.1.3 ENGINEERING UNITS, TOLERANCES, AND CONVERSIONS

3.1.3.1 ENGINEERING UNITS

All dimensions will be defined in the English system of units followed by the parenthetical SI metric equivalent.

3.1.3.2 TOLERANCES AND CONVERSIONS

All tolerances and conversions will be in accordance with ASTM E380, Standard Practice For Use Of The International System Of Units (SI).

3.2 INTERFACE REQUIREMENTS

3.2.1 ISPR INTERFACE REQUIREMENTS

3.2.1.1 ENVELOPE REQUIREMENTS

3.2.1.1.1 DYNAMIC ENVELOPE

The rack shall not exceed the dynamic envelope shown in Figures 3.2.1.1.1−1 and 3.2.1.1.1−2, Rack Dynamic Envelope, when the attachment points A, B, C and D defined in Figure 3.2.1.1.1−3, Rack Attach Point Descriptions, are constrained to an infinitely stiff and massive boundary, and using the accelerations of paragraph 3.2.1.4.2.

Racks which utilize the Active Rack Isolation System (ARIS) shall not exceed the launch / landing dynamic envelope shown in Figures 3.2.1.1.1−4, 3.2.1.1.1−5, and 3.2.1.1.1−6, ARIS Rack launch / landing Dynamic Envelope, when the attachment points A, B, C and D defined in Figure 3.2.1.1.1−3, Rack Attach Point Descriptions, are constrained to an infinitely stiff and massive boundary, and using the accelerations of paragraph 3.2.1.4.2.

Racks which utilize the Passive Rack Isolation System (PaRIS) shall not exceed the launch / landing dynamic envelope defined by the PaRIS static rack envelope from paragraph 3.2.1.1.2 with an additional ± 0.29, ± 0.11, ± 0.05 inches in X, Y, and Z respectively, when the attachment points A, B, C and D defined in Figure 3.2.1.1.1–3, Rack Attach Point Descriptions, are constrained to an infinitely stiff and massive boundary, and using the accelerations of paragraph 3.2.1.4.2.

3 - 3

.125 (3.18)

.11 (2.8)

.125 (3.18)

.11 (2.8)

Static Envelope

Dynamic Envelope

NOTE 3

Pivot Point

NOTE 1

NOTE 2

.05 (1.3)

Note 1: MPLM intrusion of this area can be calculated from the static envelope defined in Figure 3.2.1.1.2−1.

Note 2: Detail dimensions of shaded area per section views as indicated on Figure 3.2.1.1.1−2 for racks in US Lab.

Note 3: Racks may protrude into the dynamic envelope of US Lab on orbit.

FIGURE 3.2.1.1.1−1 RACK DYNAMIC ENVELOPE (SIDE VIEW)

3 - 4

Rack Static Envelope

.29 (7.4)

.29 (7.4)

Rack Dynamic Envelope

A

A

B

B

C

C

FIGURE 3.2.1.1.1−2 RACK DYNAMIC ENVELOPE (FRONT VIEW)

3 - 5

A

B

C

E•

F

H G

I

L

N M

K

J

D

POINT NAME PHASE

A Rack Lower Rear Attachment Launch/Landing

B Rack Lower Rear Attachment Launch/Landing

C Rack Upper Attachment Launch/Landing/On−orbit

D Rack Upper Attachment Launch/Landing/On−orbit

E Rack Lower GSE Attachment Ground Handling

F Rack Lower GSE Attachment Ground Handling

G Rack Upper GSE Attachment Ground Handling

H Rack Upper GSE Attachment Ground Handling

I Rack Pivot Attachment On−orbit

J Rack Pivot Attachment On−orbit

K Rack Bonding Interface

(SSP 41002, Fig. 3.3.1.2.3−3)

Launch/Landing/On−orbit

L Rack Bonding Interface

(SSP 41002, Fig. 3.3.1.2.3−3)

Launch/Landing/On−orbit

M Rack Upper KBAR Attachment On−orbit (N/A to MPLM)

N Rack Upper KBAR Attachment On−orbit (N/A to MPLM)

FIGURE 3.2.1.1.1−3 RACK ATTACH POINT DESCRIPTIONS

3 - 6

R

2.

(2

5.

6)

2.

25 2.

(5 7.

(7 2.

1.

(4 9.

1.

(2 7.

.4

(1 1.

.5

(1 2.

7)

S E

C T

IO

N

A

A S

H O

W N

S E

C T

IO

N

C

C O

P P

O S

IT E

C U

T O

U T

F O

R L

O N

G E

R O

N C

LE

A

R A

N C

E

C U

T O

U T

A T

E A

C H

LO

W

E R

A T

TA

C

H M

E N

T F

IT

T

IN

G

AT

B

A C

K O

F R

A C

K

3.

(8 3.

3 1

FIGURE 3.2.1.1.1−4 RACK DYNAMIC ENVELOPE (DETAIL AT ATTACH POINTS A

AND B) APPLICABLE ONLY TO RACKS LAUNCHED IN THE US LAB

N ot e:

R ac ks m ay p ro tr ud e in to t he d yn am ic e nv el op e of

U S

L ab o n or bi t

3 - 7

R

2.

(2

5.

6)

2.

(7 1.

1.

(2 7.

.4

(1 1.

S E

C T

IO

N

B

B

C U

T O

U T

F O

R L

O N

G E

R O

N A

N D

M

ID

R

IN

G C

R O

S S

O V

E R

B R

A C

K E

T C

LE

A

R A

N C

E (E

X T

E N

D S

E N

T

IR

E W

ID

T

H O

F R

A C

K E

N V

E

LO

P E

P A

R A

LL

E

L T

O B

A C

K A

R C

3.

(8 2.

0 4

E X

C E

P T

A S

N O

T E

D A

T E

A C

H L

O W

E

AT

TA

C

H M

E N

T F

IT

T

IN

G

FIGURE 3.2.1.1.1−5 RACK DYNAMIC ENVELOPE (BACK VIEW DETAIL)

APPLICABLE ONLY TO RACKS LAUNCHED IN U.S. LAB

N ot e:

ac ks m ay p ro tr ud e in to t he d yn am ic e nv el op e of

U S

L ab o n or bi t

3 - 8

.05 (1.3)

.05 (1.3)

.05 (1.3)

NOTE 1

.11 (2.8)

.11 (2.8)

ARIS Rack Static Envelope

ARIS Rack Dynamic Envelope

Pivot Point

NOTE 1

Note 1: MPLM intrusion of this area can be calculated from the static envelope defined in Figure 3.2.1.1.2−1.

FIGURE 3.2.1.1.1−6 ARIS RACK LAUNCH/LANDING DYNAMIC ENVELOPE (SIDE VIEW)

3 - 9

.29 .29

.29 (7.37)

.29 (7.37)

ARIS Rack Static Envelope

ARIS Rack Dynamic Envelope

(0, 0, 0)

FIGURE 3.2.1.1.1−7 ARIS RACK LAUNCH/LANDING DYNAMIC ENVELOPE (BACK VIEW)

3 - 10

.29 (7.37)

.29 (7.37)

Rack Datum Point

.29 (7.37)

.29 (7.37)

.29 (7.37)

.29 (7.37)

.11 (2.79)

.11 (2.79)

.11 (2.79)

.11

.11 (2.79)

.11

ARIS

Static Envelope

ARIS

Dynamic Envelope

ARIS Isolation Plate Static Envelope

ARIS Isolation Plate Dynamic Envelope

FIGURE 3.2.1.1.1−8 ARIS RACK LAUNCH/LANDING DYNAMIC ENVELOPE

(BOTTOM VIEW)

3 - 11

3.2.1.1.2 RACK STATIC ENVELOPE

The rack shall not exceed the static envelope as shown in Figures 3.2.1.1.2−1 Rack Static Envelope (Side View), 3.2.1.1.2−2, Rack Static Envelope (Front View), and 3.2.1.1.2−3 Rack Static Envelope (Top View).

Racks which utilize the ARIS shall not exceed the launch configuration static envelope as shown in Figures 3.2.1.1.2−7, 3.2.1.1.2−8, ARIS Rack Static Envelope, and 3.2.1.1.2−9, ARIS Rack Launch/Landing Static Envelope Detail.

Racks in the JEM−PM location A5, F5, F6 shall not exceed the static envelope as shown in Figure 3.2.1.1.2−11 Rack Static Envelope (Applicable only to racks in JEM−PM). Racks in all locations of ELM−PS shall not exceed the static envelope as shown in Figure 3.2.1.1.2−12 Rack Static Envelope (Applicable only to racks in ELM−PS).

Racks which utilize the PaRIS shall not exceed the launch configuration static envelope as shown in Figures 3.2.1.1.2–13 to 3.2.1.1.2−18, PaRIS Rack Launch/Landing Static Envelope.

3.2.1.2 MASS PROPERTIES

3.2.1.2.1 LAUNCH/LANDING/GROUND HANDLING MASS

The mass of an integrated ISPR for launch/landing/ground handling shall be less than or equal to 1773 lbs (804.2 Kg).

3.2.1.2.2 ON ORBIT MASS

The mass of an integrated ISPR on orbit shall be less than or equal to 2200 lbs (997.9 Kg).

Note: All Modules will support the maximum integrated ISPR on orbit mass up to 1773 lbs (804.2 Kg) without operational restrictions, see paragraph 3.2.2.2.

3.2.1.3 STRUCTURAL/MECHANICAL

3.2.1.3.1 LAUNCH/LANDING/ON−ORBIT ATTACHMENT

ISPRs shall incorporate structural/mechanical provisions for attachment to the MPLM during the launch/landing/on−orbit event.

3.2.1.3.2 GROUND HANDLING ATTACHMENT

ISPRs shall incorporate structural/mechanical provisions for attachment to GSE during the ground handling event.

3.2.1.3.3 ISPR MINIMUM RESONANT FREQUENCY

ISPRs shall have a minimum natural frequency greater than 28 Hz when constrained without knee braces to infinitely heavy and stiff boundaries or greater than 25 Hz when constrained including the knee braces to infinitely heavy and stiff boundaries.

3 - 12

3.2.1.3.4 BONDING

Active ISPR’s shall incorporate structural/mechanical provisions for class R bonding to the MPLM in accordance with SSP 30245, Space Station Electrical Bonding Requirements.

3.2.1.4 INDUCED ENVIRONMENTS

ISPR interfaces to the MPLM shall be capable of operation during and after exposure to any feasible combination of the following environments.

3.2.1.4.1 VIBRATION

3.2.1.4.1.1 LAUNCH ACOUSTICS

Racks launched in the MPLM shall be capable of operation after exposure to the launch minimum acoustic environment defined in Table 3.2.1.4.1.1−1, MPLM Internal Acoustic Noise Spectra.

TABLE 3.2.1.4.1.1−1 MPLM ACOUSTIC NOISE SPECTRA

1/3 Octave Band Center Frequency (Hz)

Sound Pressure Level (dB) ref. 2 x 10 −5 N/m21/3 Octave Band Center Frequency (Hz) Liftoff (1) Aeronoise (2)

31.5 40.0 50.0 63.0 80.0 100.0 125.0 160.0 200.0 250.0 315.0 400.0 500.0 630.0 800.0 1000.0 1250.0 1600.0 2000.0 2500.0

Overall

111.5 93.5 98.0 102.5 114.0 124.0 122.0 121.0 124.5 123.0 121.5 121.5 117.0 115.5 114.5 113.0 109.0 108.5 106.0 102.0

131.5

96.0 99.5 102.0 105.0 108.0 110.0 112.0 113.5 115.0 116.0 116.5 114.5 111.0 107.5 104.5 101.5 97.5 94.0 90.0 86.5

123.5

Notes:

1) 5 seconds per mission (time per flight does not include a scatter factor)

2) 10 seconds per mission (time per flight does not include a scatter factor)

3 - 13

Pivot Point

NOTE 1, 9

33.13 (841.5)4.75

(120.7) 1.91

(48.5)

4.60 (116.8)

7.15 (181.6)

80.00 (2032.0)

CUT AWAY FOR KNEE

BRACE CLEARANCE

(EXTENDS ENTIRE

WIDTH OF RACK

ENVELOPE)

(1016.0)

42 (1066.8)

R 82.00 (2082.8)

REF

NOTE 2

1.4 (35.6)

1.678 (42.6)

Rack Datum Pt.

(0,0,0) Note 3

70.498 (1790.65)

Note 1: The GSE attach boss may penetrate the 3.0” x 3.0” (76 x 76) chamfer at bottom of rack provided that the boss rotates within the pivot envelope.

Note 2: The longeron fitting intrusion of the on−orbit envelope can be derived from the module intrusion of the dynamic envelope defined in Figure 3.2.1.1.1−1.

Note 3: Origin (0,0,0) = Rack Datum Point. See Figure 3.1.3−1 SSP 41017 Part 2 for Reference System definition Note 4: Kneebraces may intrude into this area for Racks with attach points C&D below the maximum value in Figure 3.3.2−3 SSP 41017 Part 2.

Note 5: MHI/IHI Rack only, Volume occupied by seat tracks.

Note 6: GSE boss can extend beyond the static envelope by .032” in the −Y direction Note 7: Payload SIR Drawer Handles may extend beyond the static envelope into the shaded area. Other permanent payload protrusions into the shaded area must be reviewed by the Operations Community and approved as exceedences to SSP 57000 by the Payload Control Board and documented in the Payload Unique Hardware ICDs. (Not applicable for racks in the JEM Logistics Module). Rack installation with this protrusion is only allowed with NASA GSE through the MPLM aft end cone.

Note 8: Equipment within the shaded area shall be designated removable or relocatable during rack installation/removal. Capture latch knob and tool for lock bolt and FAV (in JEM) may protrude into this area. GSE will maintain clearance with stayout zone boundary.

Note 9: Equipment within the shaded area shall be designated removable or relocatable during on−orbit operations. Pivot may protrude into this area. This stay out zone only applies to Boeing rack structures.

Note 10: Stay out zone for KBAR for on orbit only excluding KBAR pin.

CUTOUT FOR LONGER

ON CLEARANCE

(EXTENDS ENTIRE

WIDTH OF RACK

ENVELOPE PARALLEL

TO BACK ARC)

4.18 MAX

(106.2) NOTE 4

.783 MAX

(19.89)

NOTE 4

ÉÉÉ

7.87 (199.89)

NOTE 5

2.47 (62.74)

NOTE 5

.50 (12.7)

2.25 (57.2)

Note 7

13.8 (350)

10.0 (254)

0.12 (3.0)

NOTE 5

É É É É É É É É É É É É É É É É É É É

61.35

(1558.3)

1.30 (33.6)

5.88 (149.4)

Note 6

13.93 (353.8)

1.25 (31.8)

3.50 (88.9)

3.

4.75 (120.7)

(9 6.

5)

NOTE 8

R

NOTE 9

2.52 (64.0)

5.34 (135.7)

2 plcs 3.00 (76.2)

2 plcs 3.00 (76.2)

7.57 (192.3)

6.5 (165.1)

Note 10

1.30 (33.6)

FIGURE 3.2.1.1.2−1 RACK STATIC ENVELOPE (SIDE VIEW)

3 - 14

ÉÉÉÉÉÉÉÉÉÉ

ÉÉÉÉÉÉÉÉÉÉ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÍÍÍÍÍÍÍÍÍÍ

ÉÉ

ÉÉ

ÉÉ

Origin (0,0,0) = Rack Datum Point, see Figure 3.3.3−1 for Reference System definition Note 1: MHI/IHI Rack only volume occupied by seat tracks.

Note 2: Payload SIR Drawer Handles may extend beyond the static envelope into the shaded area. Other permanent payload protrusions into the shaded area must be reviewed by the Operations Community and approved as exceedances to SSP 57000 by the Payload Control Board and documented in the Payload Unique Hardware ICDs. (Not applicable for racks in the JEM Logistics Module) Rack installation with this protrusion is only allowed with NASA GSE through the MPLM aft end cone.

Note 3: Equipment within the shaded area shall be designated removable or relocatable during rack installation/removal.

Capture latch knob and tool for lock bolt and FAV (in JEM) may protrude into this area. GSE will maintain clearance with stayout zone boundary.

Note 4: Equipment within the shaded area shall be designated removable or relocatable during on−orbit operations. Pivot may protrude into this area.

Note 5: This stay out zone only applies to Boeing rack structures .

Note 6: Stay out zone for KBAR for on orbit only excluding KBAR pin.

41.5 (1054.1)

(0, 0, 0)

36.7 (932.2)

1.3 (33.0)

0.16 (4.1)

75.32 (1913.2)

1.10 (27.94)

0.45 (11.43)

1.55 (39.4)

ÉÉÉ

ÉÉÉ

ÉÉÉ

30.0 (762.0)

2.37 (60.2)

3.38 (85.9)

1.00 (25.4) ”2 places”

2.015 (51.2)

1.00 (25.4)

1.25 (31.8)

6.5 (165.1)

“2 places”

ÇÇÇ

ÇÇÇ

ÇÇÇ

ÇÇÇ

1.4(35.56) “2 places”

1.7(43.18) “2 places”

2.1(53.34) “2 places”ÇÇ

ÇÇ

ÇÇ

ÇÇ

ÉÉ ÉÉÉ

see Note 6

38.85 (986.8)

38.3 (972.82)

Note 2

Note 1

”2 places”Notes 4 & 5

Note 3

FIGURE 3.2.1.1.2−2 RACK STATIC ENVELOPE (FRONT VIEW) (PAGE 1 OF 2)

3 - 15

41.50 (1054.1)

ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ

ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ

ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ

36.7 (932.18

DETAIL BOX A

3.55 (90.17)

3.55 (90.17)

B

B

C

C

A

A

2.4 (60.96)

Note 1: MHI/IHI racks only volume occupied by seat tracks

FIGURE 3.2.1.1.2−2 RACK STATIC ENVELOPE (FRONT VIEW) (PAGE 2 OF 2)

APPLICABLE ONLY TO RACKS FLOWN IN US LAB

3 - 16

(0,0,0)

NOTE 1

x

2p ls

NOTE 1 : Origin (0,0,0) = Rack Datum Point. See FIGURE 3.1.3−1, SSP41017 Part 2 for reference system definition.

NOTE 2 : MHI/IHI Rack only, Volume occupied by seat tracks.

FIGURE 3.2.1.1.2−3 RACK STATIC ENVELOPE (TOP VIEW)

(1

N O

T

3 - 17

R

2.

(2

2.

8)

2.

20 2.

(5 5.

(7 1.

1.

(4 8.

1.

(2 7.

.4

(1 1.

.5

(1 2.

7)

S E

C T

IO

N

A

A S

H O

W N

S E

C T

IO

N

C

C O

P P

O S

IT

E

C U

T O

U T

F O

R L

O N

G E

R O

N C

LE

A

R A

N C

E

C U

T O

U T

A T

E A

C H

LO

W

E R

A T

TA

C

H M

E N

T F

IT

T

IN

G

AT

B

A C

K O

F R

A C

K

3.

(8 2.

FIGURE 3.2.1.1.2−4 RACK STATIC ENVELOPE (DETAIL AT ATTACH POINTS A AND B)

APPLICABLE ONLY TO RACKS FLOWN IN US LAB

N ot e:

R ac ks m ay p ro tr ud e in to th e dy na m ic e nv el op e of U

S L ab o n or bi t (

S ee

F ig ur es

.2

.1 .1

.1 an d 3.

2.

1.

3 - 18

R

2.

(2

2.

8)

2.

(7 1.

1.

(2 7.

.4

(1 1.

S E

C T

IO

N

B

B

C U

T O

U T

F O

R L

O N

G E

R O

N A

N D

M

ID

R

IN

G C

R O

S S

O V

E R

B R

A C

K E

T C

LE

A

R A

N C

E (E

X T

E N

D S

E N

T

IR

E W

ID

T

H O

F R

A C

K E

N V

E

LO

P E

P A

R A

LL

E

L T

O B

A C

K A

R C

3.

(8 2.

E X

C E

P T

A S

N O

T E

D A

T E

A C

H L

O W

AT

TA

C

H M

E N

T F

IT

T

IN

G

FIGURE 3.2.1.1.2−5 RACK STATIC ENVELOPE (SIDE VIEW DETAIL)

APPLICABLE TO RACKS FLOWN IN US LAB ONLY

N ot e:

R ac ks m ay p ro tr ud e in to th e dy na m ic e nv el op e of U

S L ab o n or bi t (

S ee

F ig ur es

.2

.1 .1

.1 an d 3.

2.

1.

1.

1−

5)

3 - 19

FIGURE 3.2.1.1.2−6 RACK STATIC ENVELOPE (SIDE VIEW DETAIL)

APPLICABLE TO RACKS FLOWN IN ALL MODULES EXCEPT US LAB

3 - 20

ÉÉÉ

ÉÉÉ

ÉÉÉ

Pivot Point

NOTE 1

33.13 (841.5)4.75

(120.7) 1.91

(48.5)

4.60 (116.8)

7.15 (181.6)

(1016.0)

42 (1066.8)

2 PLS 3.00

(76.2)

R 82.00 (2082.8)

2 PLS 3.00

(76.2)

REF

1.4 (35.6)

1.678 (42.62)

Rack Datum Pt.

(0,0,0) Note 3

Note 1: The GSE attach boss may penetrate the 3.0” x 3.0” (76 x 76) chamfer at bottom of rack provided that the boss rotates within the pivot envelope.

Note 2: The longeron fitting intrusion of the on−orbit envelope can be derived from the module intrusion of the dynamic envelope defined in Figure 3.2.1.1.1−1.

Note 3: Origin (0,0,0) = Rack Datum Point. See Figure 3.1.3−1 SSP 41017 Part 2 for Referance System definition

Note 4: Kneebraces may intrude into this area for Racks with attach points C&D below the maximum value in Figure 3.3.2−3 SSP 41017 Part 2.

Note 5: GSE boss can extend beyond the static envelope by .032” in the −Y direction.

Note 6: Detail of Isolation Plate Static Envelope (See Figure 3.2.1.1.2−7, Page 2 of 2).

Note 7: For details of these areas see Figure 3.2.1.1.2−1.

Note 8: For details of the top of the ARIS rack and kneebrace, see Figure 3.2.1.1.2−10.

CUTOUT FOR LONGER-

ON CLEARANCE (EX-

TENDS ENTIRE WIDTH

OF RACK ENVELOPE

PARALLEL TO BACK

ARC)

4.18 MAX

(106.2) NOTE 4

.783 MAX

(19.89)

NOTE 4

2.25 (57.2)

Note 5

X

View X

70.498 (1790.65)

ÉÉÉ

ÉÉÉ

ÈÈÈ

16.10 (408.94)

8.67 (220.22)

.625 (15.88)

NOTE 6

NOTE 7

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

ÉÉ

NOTE 2

80.00 (2032.0)

NOTE 8 NOTE 8

1.3 (33.6)

FIGURE 3.2.1.1.2−7 ARIS RACK LAUNCH/LANDING STATIC ENVELOPE (SIDE VIEW)

(PAGE 1 OF 2)

3 - 21

21.40 (543.6)

3.59 (91.2)

2.12 (53.9)

25.00 (6.35)

RACK DATUM POINT

3.49 (88.6)

3.29 (83.4)

RACK PIVOT POINT

REF

R

4.61 (117.1)

10.90 (276.9)

7.50 (190.6)

7.90 (200.7)

8.06 (204.7)

9.53 (242.1)

11.77 (299.0)

12.88 (327.1)

16.95 (430.4)

18.69 (474.7)

18.98 (482.1)

20.59 (522.9)

5.16 (131.1)

NOTE 1 − ISPR BOTTOM STATIC ENVELOPE

3.62 (91.9)

A

2.85 (72.4)

A

3.78 (96.0)2X

FIGURE 3.2.1.1.2−7 ARIS RACK LAUNCH/LANDING STATIC ENVELOPE (SIDE VIEW)

(PAGE 2 OF 2)

3 - 22

39.600 (1005.84)

(0, 0, 0)

ÉÉÉÉÉÉÉÉÉÉÉÉÉ

ÉÉÉÉÉÉÉÉÉÉÉÉÉ

ÉÉÉÉÉÉÉÉÉ

ÉÉÉÉÉÉÉÉÉ

ARIS RACK

STATIC ENVELOPE

1.00 (25.4)

(0,0,0) = RACK DATUM POINT, SEE FIGURE

3.1.3−1 OF SSP 41017 Part 2,FOR REFERENCE

SYSTEM DEFININITION

37.30 (947.42)

ARIS UPPER ACTUATOR

MOUNTING PLATE STATIC

ENVELOPE

41.50 (1054.1)

0.95 (24.13)

NOTE: For SIR Drawer exceptions and GSE Stayout Areas see Figure 3.2.1.1.2−2.

FIGURE 3.2.1.1.2−8 ARIS RACK LAUNCH/LANDING STATIC ENVELOPE (BACK VIEW)

0.15 (3.81)

3 - 23

2X

2X

2X

2X

2X

15.76 (400.3)

10.65 (270.5)

8.06 (204.7)

REF

REF7.90

(200.7)

6.31 (160.3)

3.92 (99.5)

RACK DATUM POINT

.15 (3.8)

1.78 (45.2)

4.2 (106.7)

18.45

20.85

35.10 (891.5)

37.53 (953.3)

(529.7)

(468.6)

39.45 (1002.0)

1.50 (38.1)

1.25 (31.7)

RACK PIVOT

CENTERLINE

38.05 (966.5)

37.80 (960.1)

FIGURE 3.2.1.1.2−9 ARIS LAUNCH/LANDING RACK STATIC ENVELOPE DETAIL

(BOTTOM VIEW) PAGE 1 OF 2

3 - 24

FIGURE 3.2.1.1.2−9 ARIS RACK LAUNCH/LANDING STATIC ENVELOPE DETAIL

3 - 25

ARIS RACK TOP VIEW

FIGURE 3.2.1.1.2−10 ARIS RACK STATIC ENVELOPE KNEE BRACE INTRUSION DETAILS

(TOP VIEW) (NASA−ASI ONLY)

3 - 26

PLS

Note 1: This figure is applicable only to the racks in the JEM−PM location A5, F5, F6.

Note 2: Figure 3.2.1.1.2−1 and Figure 3.2.1.1.2−2 are applicable to other envelope except as shown in this figure.

Note 3: Detail E(4PLS) is applicable only to the rack in the JEM−PM location F6.

FIGURE 3.2.1.1.2−11 RACK STATIC ENVELOPE (APPLICABLE ONLY TO RACKS IN

JEM −PM) (SIDE VIEW) (PAGE 1 OF 5)

3 - 27

JEM −PM) (BACK VIEW) (PAGE 2 OF 5)

3 - 28

JEM −PM) (DETAIL D FOR SECTION X−X) (PAGE 3 OF 5)

3 - 29

JEM −PM) (DETAIL D FOR SECTION Y−Y) (PAGE 4 OF 5)

3 - 30

JEM −PM) (DETAIL E) (PAGE 5 OF 5)

3 - 31

FIGURE 3.2.1.1.2−12 RACK STATIC ENVELOPE APPLICABLE ONLY TO RACKS IN

ELM−PS (SIDE VIEW) (PAGE 1 OF 4)

3 - 32

ELM−PS (BACK VIEW) (PAGE 2 OF 4)

3 - 33

ELM−PS (DETAIL F FOR SECTION X−X) (PAGE 3 OF 4)

3 - 34

ELM−PS (DETAIL F FOR SECTION Y−Y) (PAGE 4 OF 4)

3 - 35

1.30

24.35

FIGURE 3.2.1.1.2−13 PARIS RACK LAUNCH/LANDING STATIC ENVELOPE

(SIDE VIEW)

3 - 36

FIGURE 3.2.1.1.2−14 PARIS RACK LAUNCH/LANDING STATIC ENVELOPE (FRONT VIEW)

3 - 37

4.

FIGURE 3.2.1.1.2−15 PARIS RACK LAUNCH/LANDING STATIC ENVELOPE (TOP VIEW)

3 - 38

FIGURE 3.2.1.1.2−16 PARIS LAUNCH/LANDING STATIC ENVELOPE

(LOWER ISOMETRIC VIEW)

IS

O

M E

T R

IC

V

IE

W

R E

F E

R E

N C

E O

N

LY

3 - 39

3.

6.

9.

.0

.3

.0

.0

.2

FIGURE 3.2.1.1.2−17 PARIS RACK LAUNCH/LANDING STATIC ENVELOPE

(BOTTOM VIEW DETAIL)

3 - 40

0.

(3 .9

2)

(6 .5

2)

(9 .3

2)

(1 0.

.3

3.

37 3.

3.

6.

7.

8.

.3

.3

.4

(2 0.

7.

R

.2

FIGURE 3.2.1.1.2−18 PARIS RACK LAUNCH/LANDING STATIC ENVELOPE

(BOTTOM VIEW SECTION DETAIL)

3 - 41

3.2.1.4.1.2 RANDOM VIBRATION

ISPR interfaces to the MPLM shall be capable of operation during and after exposure to the random vibration environment defined in Table 3.2.1.4.1.2−1, MPLM Random Vibration Environment.

TABLE 3.2.1.4.1.2−1 MPLM RANDOM VIBRATION ENVIRONMENT

LOCATION FREQUENCY LEVEL

Input to rack at rack interfaces 20 Hz 0.0001 g2/Hz

20−80 HZ +11.5 dB/Oct

Any direction independent of mass 80 − 150 Hz .02 g2/Hz

150−2000 Hz −4.9 dB/Oct

2000 Hz 0.0003 g2/Hz

Composite 2.4 grms

3.2.1.4.2 ACCELERATION

Rack accelerations are defined in Table 3.2.1.4.2−1, NASA Rack Accelerations (Maximum Predicted Level), Table 3.2.1.4.2−2, IHI Payload Rack Accelerations (Maximum Predicted Level), Table 3.2.1.4.2−3, MHI System Rack Accelerations (Maximum Predicted Level) respectively.

Racks to be flown in MPLM will be designed to withstand the applicable acceleration environment for each kind of racks reported in these tables, when constrained to an infinitely massive and stiff boundary.

These acceleration environment values may be superseded by results from flight specific coupled loads analyses (CLA) of the MPLM with racks.

For on-orbit conditions, the acceleration environment will be 0.2g in any direction when the attach points A, B, C and D or C, D, I and J are employed.

For a tilted rack position, the rack will be subjected to the interface loads in Table 3.2.1.4.3−1, Mini Pressurized Logistics Module and Mechanical Ground Support Equipment Local Rack Attach Point Design Limit Loads (Launch, Landing, On−Orbit and Ground Handling), at attach points I and J.

3 - 42

TABLE 3.2.1.4.2−1 NASA RACK ACCELERATION

(MAXIMUM PREDICTED LEVEL)

Nx(g) Ny(g) Nz(g) Rx * (rad/sec2)

Ry* (rad/sec2)

Rz* (rad/sec2)

Launch +/−7.0 +/−8.0 +/−7.8 +/−70.8 +/−21.7 +/−34.8

Landing +/−5.3 +/−7.2 +/−9.0 +/−37.1 +/−23.0 +/−28.3

Ground Handling +/−0.5 +/−1.0 +/−2.0 +/−0.0 0.0 0.0

KSC Ground Handling (Alt Attach/Bosses)

+/−0.3 +/−1.08 +/−1.08 +/−0.0 +/−0.0 +/−0.0

Nodes 2 & 3 Ground Handling(Alt.

Attach/ Bosses)

±0.3 ±1.5 ±1.5 ±0.0 ±0.0 ±0.0

* Rotation taken about Rack center of mass.

TABLE 3.2.1.4.2−2 IHI PAYLOAD RACK ACCELERATIONS

(MAXIMUM PREDICTED LEVEL)

Nx(g) Ny(g) Nz(g) Rx * (rad/sec2)

Ry * (rad/sec2)

Rz * (rad/sec2)

Launch** +6.54

−6.15

+5.16

−5.40

+7.66

−7.91

+43.4

−42.3

+16.0

−15.5

+36.8

−34.1

Landing** +4.04

−4.92

+8.12

−7.75

+8.50

−4.46

+19.2

−18.9

+16.2

−18.0

+32.2

−33.0

* Rotation taken about Rack center of mass.

**The values in the table include uncertainty factor: 1.25

TABLE 3.2.1.4.2−3 MHI SYSTEM RACK ACCELERATIONS

(MAXIMUM PREDICTED LEVEL)

Nx(g) Ny(g) Nz(g) Rx * (rad/sec2)

Ry * (rad/sec2)

Rz * (rad/sec2)

Launch** +4.06

−4.47

+4.55

−4.67

+5.49

−5.71

+27.4

−27.1

+12.9

−11.5

+15.9

−17.4

Landing** +3.34

−3.76

+6.61

−6.46

+6.81

−3.74

+12.3

−11.9

+12.8

−13.5

+16.4

−15.6

* Rotation taken about Rack center of mass.

**The values in the table include uncertainty factor: 1.25

3 - 43

3.2.1.4.3 INTERFACE LOADS

Interface loads for launch and landing are the static, dynamic, and pressure loads exchanged between the rack and the module through the attach points A, B, C and D. Interface loads for ground handling are the static and dynamic loads exchanged between the rack and GSE through the attach points E, F, G, and H. On−orbit interface loads are static, dynamic and pressure loads exchanged between the rack and the module through the attach points A, B, C and D or C, D, I and J or I and J (for a tilted rack). For all flight and ground events, the racks shall not exceed the interface loads defined in Table 3.2.1.4.3−1, MPLM and Mechanical Ground Support Equipment Local Rack Attach Point Design Limit Loads (Launch, Landing, On−Orbit and Ground Handling) based on coupled dynamic, static, and pressure analyses or additional structural analysis shall be required. Table 3.2.1.4.3−2 defines the loads on NASA racks due to differential pressure. Table 3.2.1.4.3−3 defines the loads on MHI/IHI racks due to differential pressure.

Design load table is for individual rack/cargo assessment. Verification coupled loads analysis may require MPLM manifest modification.

S

P 41017, P art 1 R evision G F ebruary 4, 2005

3 −

TABLE 3.2.1.4.3−1 MINI PRESSURIZED LOGISTICS MODULE AND MECHANICAL GROUND SUPPORT EQUIPMENT LOCAL RACK ATTACH POINT DESIGN LIMIT LOADS (LAUNCH, LANDING, ON−ORBIT AND GROUND HANDLING) (PAGE 1 OF 2)

EVENT Limit

Load lbf

ATTACH POINT LOCATIONS

Load lbf

(N) A B C D E F G H I *3 J *3 M *3 N *3

Launch Fx

Fy

Fz

*1+7132/−6856 (31730) *2+6856/−6856 (30500)

±6250 (27800)

±8340 (37100)

±6630 (29500) *1+9231/−8565 (41069) *2+8565/−8565 (38100)

±5927 (26367)

±5867 (26100)

±90 (400)

±23 (100)

±5305 (23600)

±83 (370)

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

Landing Fx

Fy

Fz

±7613 (33863)

±5524 (24571) *1+13530/−12839 (60205) *2+12839/−12839 (57108)

±5951 (26470)

±12861 (57206)

±5852 (26030)

±4987 (22182)

±87 (387)

±26 (116)

±5012 (22293)

±77 (343)

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

On− Orbit

Fx

Fy

Fz

Do not exceed launch and landing interface limit loads (see above)

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

+250 (1112)

±125 (556)

±250 (1112)

−250 (1112)

±125 (556)

±250 (1112)

±125 (556)

±125 (556)

±125 (556)

±125 (556)

P 41017, P art 1 R evision G F ebruary 4, 2005

3 −

TABLE 3.2.1.4.3−1 MINI PRESSURIZED LOGISTICS MODULE AND MECHANICAL GROUND SUPPORT EQUIPMENT LOCAL RACK ATTACH POINT DESIGN LIMIT LOADS (LAUNCH, LANDING, ON−ORBIT AND GROUND HANDLING) (PAGE 2 OF 2)

EVENT Limit

Load lbf

ATTACH POINT LOCATIONS

Load lbf

(N) A B C D E F G H I *3 J *3 M *3 N *3

Ground Handling (Launch Attached)

Fx

Fy

Fz

±4330 (19261)

±4620 (20551)

±4940 (21974)

±4620 (20551)

±4940 (21974)

±2370 (10542)

±5140 (22864)

±2370 (10542)

±5140 (22864)

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

Ground Handling (Alt Attach)

Fx

Fy

Fz

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

±170 (756)

±560 (2491)

±480 (2135)

±170 (756)

±560 (2491)

±480 (2135)

±170 (756)

±560 (2491)

±480 (2135)

±170 (756)

±560 (2491)

±480 (2135)

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

Ground Handling (Alt Attach/ Bosses) Nodes 2 & 3

Fx

Fy

Fz

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

±300 (1335)

�3000 (13,345)

�2000 (�8900)

±1000 (4450)

±300 (1335)

�3000 (13,345)

�2000 (�8900)

±1000 (4450)

±300 (1335)

�3000 (13,345)

�2000 (�8900)

±1000 (4450)

±300 (1335)

�3000 (13,345)

�2000 (�8900)

±1000 (4450)

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

Ground Handling (Alt Attach/ Bosses) For U.S.

ISPR’S in

MPLM

only (*4)

Fx

Fy

Fz

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

±300 (1335)

±1000 (4450)

±1000 (4450)

±300 (1335)

±1000 (4450)

±1000 (4450)

±300 (1335)

±1000 (4450)

±1000 (4450)

±300 (1335)

±1000 (4450)

±1000 (4450)

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

N/A

Notes: N/A = Not applicable − Rack is not attached at this location On−orbit loads apply for the range of rack positions for nomal to fully tilted Landing loads include the pressure induced loads contained in Table 3.2.1.4.3−2 for NASA racks and Table 3.2.1.4.3−3 for MHI/IHI racks.

Launch and landing loads are applicable for any rack mounted position (one rack at a time) as noted below:

*1. Use the higher load value for the following MPLM locations: all starboard locations, portside locations for the 2 most forward bay locations, and the NADIR location for the 3rd bay from forward.

*2. Use the lower load value for all other locations not defined in note *1.

*3. Launch and landing loads apply only to ZSR racks in Node 2.

On−orbit for ARIS Pivot Fx loads are opposite sign.

*4. This row defines MPLM (KSC) GSE ground handling design limit loads.

3 − 46

TABLE 3.2.1.4.3−2 MPLM RACK INTERFACE LOADS ON NASA RACKS DUE TO

DIFFERENTIAL PRESSURE (APPLICABLE FOR LANDING ONLY)

Load Lbf (N)

ATTACH POINT LOCATION

Load Lbf (N)

A B C D

FX

FY

FZ

� 959 (4266)

� 286 (1271)

� 1892 (8416)

� 0 (0)

� 286 (1271)

� 1892 (8416)

� 962 (4281)

� 491 (2185)

� 0 (0)

� 0 (0)

� 601 (2674)

� 0 (0)

TABLE 3.2.1.4.3−3 MPLM RACK INTERFACE LOADS ON MHI/IHI RACKS DUE TO

DIFFERENTIAL PRESSURE (APPLICABLE FOR LANDING ONLY)

Load Lbf (N)

ATTACH POINT LOCATION

Load Lbf (N)

A B C D

FX

FY

FZ

� 1060 (4715)

� 315 (1401)

� 2090 (9296)

� 0 (0)

� 315 (1401)

� 2090 (9296)

� 1060 (4715)

� 330 (1468)

� 6 (27)

� 0 (0)

� 330 (1468)

� 6 (27)

3.2.1.4.4 RACK DIFFERENTIAL PRESSURE

The rack structure shall not permanently deform when exposed to a maximum repressurization rate of 6.96 psi/min (800 Pa/s).

The rack structure shall not permanently deform when exposed to a maximum depressurization rate of 7.74 psi/min (890 Pa/s).

3.2.2 MPLM INTERFACE REQUIREMENTS

3.2.2.1 ENVELOPE REQUIREMENTS

3 − 47

3.2.2.1.1 DYNAMIC ENVELOPE

Each rack location within the MPLM shall reserve volume for the dynamic envelope shown in Figure 3.2.1.1.1−1 and 3.2.1.1.1−2, Rack Dynamic Envelope, when the attachment points A, B, C and D defined in Figure 3.2.1.1.1−3 are for launch and landing.

(NASA ASI ONLY) Racks within the MPLM which utilize the ARIS shall reserve volume for the dynamic envelope shown in Figures 3.2.1.1.1−4, 3.2.1.1.1−5, and 3.2.1.1.1−6, ARIS Rack Dynamic Envelope, when the attachment points A, B, C and D defined in Figure 3.2.1.1.1−3, are for launch and landing

(NASA ASI ONLY) Racks within the MPLM which utilize the PaRIS shall reserve volume for the dynamic envelope as defined in paragraph 3.2.1.1.1, when the attachment points A, B, C and D defined in Figure 3.2.1.1.1–3, are for launch and landing.

3.2.2.1.2 MPLM ACCOMMODATION OF RACK

The MPLM shall accommodate racks designed in accordance with the rack static envelope as defined in Figure 3.2.1.1.2−1 side view and 3.2.1.1.2−2, Rack Static Envelope (Front View) for the launch/landing and on−orbit conditions.

(NASA ASI ONLY) The MPLM shall accommodate racks which utilize the ARIS in accordance with the static envelope as shown in Figures 3.2.1.1.2−3, 3.2.1.1.2−4, and 3.2.1.1.2−5, ARIS Rack Static Envelope for the launch/landing and on−orbit conditions.

(NASA ASI ONLY) The MPLM shall accommodate racks which utilize the PaRIS in accordance with the static envelope as shown in Figures 3.2.1.1.2–13 to 3.2.1.1.2–18, PaRIS Rack Launch/Landing Static Envelope for the launch/landing and on–orbit conditions.

3.2.2.2 MASS PROPERTIES

Each ISPR location within the MPLM shall accommodate the maximum integrated ISPR mass of 1773 lbs (804.2 kg).

All Modules shall accommodate Racks with an On Orbit mass of 1773 lbs (804.2 Kg) without operational restrictions.

Each ISPR location within the USL, APM, JEM and CAM shall accommodate the maximum integrated on orbit mass of 2200 lbs (997.9 Kg) with restrictions as noted below.

The JEM shall only accommodate an On Orbit mass of 2200 lbs (997.9 Kg) with operational restricions.

The APM shall accommodate one 2200 lbs (997.9 Kg) ISPR per stand off train, and no two such racks shall share the stand off in one bay. Each stand off train ISPR mass shall not exceed 7092 lbs (3217 Kg) in the APM.

3 − 48

3.2.2.3 STRUCTURAL/MECHANICAL

3.2.2.3.1 LAUNCH/LANDING/ON−ORBIT ATTACHMENT

The MPLM shall incorporate structural/mechanical provisions for attachment of the ISPR for the launch/landing/on−orbit event.

3.2.2.3.1.1 ON−ORBIT MODULAR ATTACHMENT

On−Orbit modules shall provide the ARIS standoff link interface and the Capture Mechanism as the module to rack interface at specified locations (excluding MPLM).

3.2.2.3.1.2 RACK TO MODULE INTERFACE

On−Orbit racks shall provide the KBAR as the rack to module interface.

3.2.2.3.2 GROUND HANDLING ATTACHMENT

Not Applicable

3.2.2.3.3 MINIMUM RESONANT FREQUENCY

Not Applicable

3.2.2.3.4 DELETED

3.2.2.3.5 BONDING (MPLM ONLY)

For Each R/F location, the MPLM shall provide a bonding strap for class R bonding in accordance with SSP 30245, space Station Electrical Bonding Requirements.

3.2.2.3.6 ARIS RACK COMPATIBILITY

The MPLM shall accommodate ARIS in the launch configuration in up to 6 locations.

3.2.2.3.7 PARIS RACK COMPATIBILITY

The MPLM shall accommodate PaRIS in the launch configuration in up to six (6) locations.

3.2.2.4 INDUCED ENVIRONMENTS

MPLM interfaces to the ISPR shall be capable of operation during and after exposure to any feasible combination of the following environments.

3 − 49

3.2.2.4.1 VIBRATION

3.2.2.4.1.1 LAUNCH ACOUSTICS

The MPLM shall impart an acoustic environment no greater than defined in Table 3.2.1.4.1.1−1, MPLM Internal Acoustic Noise Spectra.

3.2.2.4.1.2 RANDOM VIBRATION

MPLM interfaces to the ISPR shall be capable of operation during and after exposure to the random vibration environment defined in Table 3.2.1.4.1.2−1, MPLM Random Vibration Environment.

3.2.2.4.2 ACCELERATION

N/A

3.2.2.4.3 INTERFACE LOADS

Interface loads for launch and landing are the static, dynamic, and pressure loads exchanged between the module and the rack through the attach points A, B, C and D.