41015P1RG.pdf

SSP 41015, Part 1, Revision G

Common Hatch And Mechanisms T o Pressurized Elements Interface Control Document

Revision G September 23, 2005

Part 1

International Space Station Program

National Aeronautics and Space Administration International Space Station Program Johnson Space Center Houston, T exas Contract No. NAS15−10000 esa european space agency

Japan Aerospace Exploration Agency

SSP 41015 Part 1 Revision G 23 September 2005 ii

REVISION AND HISTORY PAGE

REV. DESCRIPTION PUB.

DATE

− BASELINE ISSUE (REFERENCE SSCBD BB003286 EFF. 02−25−92) 02−92

IRNs 0001 − 0022 (REFERENCE SSCBD BB003286A EFF. 04−03−92 04−92

IRNs 0024 − 0041 (REFERENCE SSCBD BB003286A EFF. 04−03−92) 04−92

IRN 0042 (REFERENCE SSCBD BB003286B EFF. 07−16−92) 07−92

A REVISION A (REFERENCE IRN 0043, SSCBD BB003286B EFF. 07−16−92) 07−92

IRNs 0044 − 0059 (REFERENCE SSCBD BB003286C EFF. 11−13−92 12−92

IRNs 0061 − 0073 (REFERENCE SSCBD BB003286C EFF. 11−13−92) 12−92

IRN 0074 (REFERENCE SSCBD BB003286D EFF. 12−18−92) 01−93

B REVISION B (REFERENCE IRN 0075, SSCBD BB003286D EFF. 12−18−92) 01−93

C REVISION C (REFERENCE SSCBD 000008, EFF. 3−23−94) 03−94

CHANGE 1, IRN 000145 (REFERENCE SSCN 000145, EFF. 10−31−95) 10−17−96

D REVISION D (REFERENCE SSCN 000430 EFF. 11−08−97) 08−13−97

IRN 0609 (REFERENCE SSCD 000609, EFF. 06−17−97) 03−16−98

E REVISION E (REFERENCE SSCD 001163, EFF. 08−04−98) 03−19−99

Incorporate the following Approved PIRNs:

AS−0004B, NA−0024, NA−0026A, NA−0027A, NA−0028B, NA−0029

F REVISION F (REFERENCE SSCD 006957, EFF. 09−17−02) 10−15−02

Incorporate the following PIRNs Associated with SSCNs:

PIRN IRN SSCN

41015−NA−0031B 1465 000721/001465

41015−NA−0032A 1268 001268

41015−NA−0033B N/A 006957

41015−NA−0034F 0010/0011 004025/004361

Revision F closes the following SSCNs as they were overcome by events:

000554, 000583, 000588, 000591, 000673, 000773, 000823, 000832, 000844, 000845, 000877, 000889, 000894, 000915, and 001026

NOTE: Due to past history of this document, IRNs 0002 and 0005 have been retired without use.

REVISION AND HISTORY PAGE

REV. DESCRIPTION PUB.

DATE

G REVISION G (REFERENCE SSCD 009703, EFF. 10−13−06) 12−12−06

Incorporate the following PIRNs Associated with SSCNs:

PIRN IRN SSCN

41015−NA−0035B 0012 006052

41015−NA−0035B N/A 006135

41015−NA−0035B N/A 006245

41015−NA−0038A N/A 009703

41015−NA−0039A 0013 008644

0001 001662 0007 002820 0008 003746 0009 002877

Revision G closes the following SSCNs as they were overcome by events:

000567, 000671, 001004, 001029, 001051, 001052, 001127, and 001386.

The following SSCN’s have been evaluated and it has been determined that they are of no impact to this ICD: 000780, 001594 and 002446.

ERU: /s/ J. Rivas 12−12−06 iv

PREFACE

SSP 41015, Common Hatch and Mechanisms to Pressurized Elements Interface Control Document (ICD) shall be implemented on all new Program contractual and internal activity and shall be included in any existing contracts through contract changes. This document is under the control of the International Space Station (ISS) Interface Control Working Group (ICWG), any changes or revisions will be approved by the ISS ICWG.

v

INTERNATIONAL SPACE STATION PROGRAM

COMMON HATCH AND MECHANISMS TO PRESSURIZED ELEMENTS

INTERFACE CONTROL DOCUMENT

PART 1

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INTERNATIONAL SPACE STATION PROGRAM

COMMON HATCH AND MECHANISMS TO PRESSURIZED ELEMENTS

INTERFACE CONTROL DOCUMENT

PART 1

SEPTEMBER 23, 2005

CONCURRENCE

Warren England Boeing

PREPARED BY: PRINT NAME ORGN

/s/ Warren England 11/17/06

SIGNATURE DATE

CHECKED BY: Quentin Henry Boeing

PRINT NAME ORGN

/s/ Quentin L. Henry 12/5/06

SIGNATURE DATE

NASA ICWG CHAIR BY: Chau Hong NASA/OM

PRINT NAME ORGN

/s/ Chau Hong 12/05/06

SIGNATURE DATE

DQA: Merry McClain Boeing

PRINT NAME ORGN

/s/ Merry Roberts 12/6/06

SIGNATURE DATE

SSP 41015 Part 1 Revision G 23 September 2005 vii

INTERNATIONAL SPACE STATION PROGRAM

COMMON HATCH AND MECHANISMS TO PRESSURIZED ELEMENTS

INTERFACE CONTROL DOCUMENT

PART 1

LIST OF CHANGES

SEPTEMBER 23, 2005

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

SSCBD ENTRY DATE CHANGE PARAGRAPH(S)

009703 09/23/05 NA−0038A 2.1, 3.2.1.3, 3.2.1.3.2.1.1, Table 3.2.1.3.2.1.1−2, 3.2.2.3.2, 3.2.2.3.3

008644 NA−0039A Table 3.2.1.1.2.3−1

006052/6135/006245 NA−0035B 3.1.1.2.3, Table 3.2.1.1.2.3−1

TABLE OF CONTENTS

PARAGRAPH PAGE

viii

1.0 INTRODUCTION 1 - 1

1.1 PURPOSE 1 - 1

1.2 SCOPE 1 - 1

1.3 PRECEDENCE 1 - 1

1.4 DELEGATION OF AUTHORITY 1 - 1

1.5 RESPONSIBILITY AND CHANGE AUTHORITY 1 - 1

2.0 DOCUMENTS 2 - 1

2.1 APPLICABLE DOCUMENTS 2 - 1

2.2 REFERENCE DOCUMENTS 2 - 2

3.0 COMMON HATCH AND HATCH MECHANISMS TO PRESSURIZED

ELEMENTS INTERFACES 3 −1

3.1 GENERAL 3 −1

3.1.1 INTERFACE DESCRIPTION 3 −1

3.1.1.1 HATCH DESCRIPTION 3 −1

3.1.1.2 PRESSURIZED ELEMENT DESCRIPTION 3 −1

3.1.1.2.1 UNITED STATES PRESSURIZED ELEMENTS 3 −1

3.1.1.2.2 INTERNATIONAL PRESSURIZED ELEMENTS 3 −1

3.1.1.3 INTERFACE PLANE DESCRIPTION 3 −2

3.1.1.4 COORDINATE SYSTEM 3 −4

3.1.1.5 ENGINEERING UNITS AND TOLERANCES 3 −4

3.1.1.5.1 TOLERANCE 3 −4

3.1.1.6 HATCH INTERFACE FUNCTIONS 3 −4

3.1.1.7 PRESSURIZED ELEMENT INTERFACE FUNCTIONS 3 −4

3.1.2 INTERFACE RESPONSIBILITIES 3 −6

3.1.2.1 RESPONSIBILITY FOR HATCH 3 −6

3.1.2.2 RESPONSIBILITY FOR PRESSURIZED ELEMENT 3 −6

3.1.2.2.1 RESPONSIBILITY FOR US LABORATORY ELEMENT 3 −6

3.1.2.2.2 RESPONSIBILITY FOR HABITATION ELEMENT 3 −6

3.1.2.2.3 RESPONSIBILITY FOR NODE 3 −6

3.1.2.2.4 RESPONSIBILITY FOR COLUMBUS ATTACHED PRESSURIZED

MODULE 3 −6

3.1.2.2.5 RESPONSIBILITY FOR JAPANESE EXPERIMENT MODULE 3 −6

3.1.2.2.6 RESPONSIBILITY FOR MINI PRESSURIZED LOGISTICS MODULE 3 −6

3.2 INTERFACE REQUIREMENTS 3 −6

3.2.1 HATCH INTERFACE REQUIREMENTS 3 −6

3.2.1.1 ENVELOPE REQUIREMENTS 3 −6

3.2.1.1.1 STATIC ENVELOPE 3 −6

3.2.1.1.2 RESERVED VOLUMES 3 −8

3.2.1.1.2.1 HATCH HARDWARE 3 −8

3.2.1.1.2.2 ACCESS/PASSAGEWAYS 3 −8

3.2.1.2 MASS PROPERTIES 3 −8

3.2.1.2.1 CENTER OF MASS 3 −8

3.2.1.2.1.1 MOMENTS OF INERTIA 3 −10

3.2.1.2.1.2 MASS LIMITATIONS 3 −10

TABLE OF CONTENTS − Continued

PARAGRAPH PAGE

ix

3.2.1.3 STRUCTURAL/MECHANICAL ATTACHMENT 3 −10

3.2.1.3.1 STIFFNESS AT THE INTERFACE PLANE 3 −10

3.2.1.3.2 STRUCTURAL LOADS 3 −10

3.2.1.3.2.1 INDUCED LOADS 3 −10

3.2.1.3.2.1.1 LIFT−OFF AND LANDING LOADS 3 −10

3.2.1.3.2.2 ON−ORBIT LOADS 3 −12

3.2.1.3.2.2.1 ON−ORBIT CREW INDUCED LOADING 3 −12

3.2.1.3.2.2.2 DELETED 3 −12

3.2.1.3.3 DELETED 3 −12

3.2.1.3.3.1 DELETED 3 −12

3.2.1.3.3.2 DELETED 3 −12

3.2.1.3.3.3 MAINTENANCE ACCESS CLEARANCES 3 −12

3.2.1.3.4 ATMOSPHERIC SEALS 3 −12

3.2.1.3.4.1 SEAL LEAKAGE 3 −12

3.2.1.3.5 PPRV INTERFACE 3 −12

3.2.1.4 INDUCED ENVIRONMENTS 3 −13

3.2.1.4.1 BONDING 3 −13

3.2.1.5 THERMAL 3 −13

3.2.2 PRESSURIZED ELEMENT INTERFACE REQUIREMENTS 3 −13

3.2.2.1 ENVELOPE REQUIREMENTS 3 −13

3.2.2.1.1 ENVELOPE 3 −13

3.2.2.1.2 RESERVED VOLUMES 3 −13

3.2.2.1.2.1 PRESSURIZED ELEMENT HARDWARE 3 −13

3.2.2.1.2.2 ACCESS/PASSAGEWAYS 3 −13

3.2.2.2 MASS PROPERTIES 3 −13

3.2.2.3 STRUCTURAL/MECHANICAL ATTACHMENT 3 −13

3.2.2.3.1 STIFFNESS AT THE INTERFACE PLANE 3 −13

3.2.2.3.2 STRUCTURAL LOADS 3 −13

3.2.2.3.3 ACCESS/PASSAGEWAYS 3 −14

3.2.2.3.3.1 DELETED 3 −14

3.2.2.3.3.2 DELETED 3 −14

3.2.2.3.3.3 MAINTENANCE ACCESS CLEARANCES 3 −14

3.2.2.3.4 ATMOSPHERIC SEALS 3 −14

3.2.2.3.4.1 SEAL LEAKAGE 3 −14

3.2.2.3.4.1.1 LEAKAGE DETECTION 3 −14

3.2.2.3.5 LEAK CHECK PORTS 3 −14

3.2.2.4 INDUCED ENVIRONMENTS 3 −14

3.2.2.4.1 BONDING 3 −14

3.2.2.5 THERMAL 3 −14

APPENDIX

A ABBREVIATIONS AND ACRONYMS A - 1

TABLE PAGE

TABLES

x

3.1.1.5.1−1 LINEAR TOLERANCES 3 −4

3.2.1.1.2.3−1 CBCS BERTHING HARDWARE APPLICABILITY 3 −8

3.2.1.3.2.1.1−1 LAUNCH RANDOM VIBRATION 3 −11

3.2.1.3.2.1.1−2 ALLOWABLE GROUND, LIFTOFF AND LANDING LOAD FACTORS 3 −11

FIGURE PAGE

FIGURES

xi

3.1.1−1 HATCH TO PRESSURIZED ELEMENT INTERFACE BLOCK DIAGRAM 3 −2

3.1.1.1−1 HATCH TO PRESSURIZED ELEMENT SEALING SURFACE INTERFACE 3 −3. . .

3.1.1.4−1 HATCH COORDINATE SYSTEM 3 −5

3.1.1.4−2 DELETED 3 −5

3.1.1.4−3 DELETED 3 −5

3.1.1.4−4 DELETED 3 −5

3.2.1.1.1−1 HATCH STATIC ENVELOPE AND PASSAGEWAY CLEARANCE 3 −7

3.2.1.2.1−1 HATCH ASSEMBLY, PART NUMBER 683−13000−004 CENTER OF MASS

ENVELOPE AND MOMENTS OF INERTIA 3 −9

3.2.1.3.2.2.2−1 DELETED 3 −12

3.2.1.3.3−1 DELETED 3 −12

3.2.1.3.3−2 DELETED 3 −12

3.2.1.3.3.2−1 DELETED 3 −12

1 - 1

1.0 INTRODUCTION

The Space Station Common Hatch and Mechanisms will be used on the National Aeronautics and Space Administration (NASA) elements, the Japanese Aerospace Exploration Agency of Japan (JAXA) elements, the European Space Agency (ESA) elements, and the Agenzia Spaziale Italiana (ASI) elements.

The Common Hatch and Mechanisms will be referred to herein as the Hatch. The United States (U.S.) Pressurized Elements and International Pressurized Elements will be referred to herein as the Pressurized Elements. Node Pressurized Element 1 and Node Pressurized Element 2 will be referred to herein as the Nodes.

In this ICD, the open position will also be referred to as the stowed position; the closed position is also referred to as the deployed position.

1.1 PURPOSE

The purpose of this document is to provide physical, functional, and environmental interface requirements between the common hatch, hatch mechanism, and all (ISS) Pressurized Elements that integrate the ISS Common Hatch.

1.2 SCOPE

The scope of this document is limited to the interfaces between the Hatch and Pressurized Elements.

1.3 PRECEDENCE

In the event of conflict between SSP 41000, Systems Specification for the International Space Station, and the contents of this ICD, the requirements of the Systems Specification for the International Space Station shall take precedence.

1.4 DELEGATION OF AUTHORITY

The Prime Contractor shall delegate the responsibility for preparation and maintenance of this

ICD.

1.5 RESPONSIBILITY AND CHANGE AUTHORITY

This document is prepared and maintained in accordance with SSP 30459, International Space Station Interface Control Plan.

2 - 1

2.0 DOCUMENTS

The following documents of the exact issue shown form part of this ICD to the extent specified herein

2.1 APPLICABLE DOCUMENTS

DOCUMENT NO. TITLE

ASTM E−380 Standard Practice for Use of the International System Rev A of Units (SI) (the Modernized Metric System) 1 Jan 93 References 3.1.1.5.1

SSP 30219 Space Station Reference Coordinate Systems Rev D 21 Jan 94

DCN 001

References 3.1.1.4

SSP 30245 Space Station Electrical Bonding Requirements Rev D, DCNs 004, 005, 006, 011 4 Jun 98

DCN 004, 005

References 3.2.1.4.1, 3.2.2.4.1

SSP 30459 International Space Station Interface Control Plan Rev F 23 Mar 94 References 1.5

SSP 30559 Structural Design and Verification Requirement Rev C References Table 3.2.1.3.2.1.1−2

SSP 50005 International Space Station Flight Crew Standard Rev B 9 Aug 95

DCN 001, 002, 003, 004,

005, and 006 References 3.2.1.3.2.2.1, 3.2.1.3.3.3, 3.2.2.3.3.3

2 - 2

SSP 50023 Thermal Control Plan Rev Basic 15 Apr 94 References 3.2.1.5, 3.2.2.5

NSTS−21000−IDD−ISS Shuttle Orbiter/International Space Station Cargo Rev A, CN 009, 010, 011 Standard Interfaces 012, 013, 014, 015 18 Feb 98 References 3.2.1.3.2.1.1

2.2 REFERENCE DOCUMENTS

DOCUMENT NO. TITLE

SSP 41000 System Specification

Reference 1.3

3 −1

3.0 COMMON HATCH AND HATCH MECHANISMS TO PRESSURIZED ELEMENTS

INTERFACES

3.1 GENERAL

3.1.1 INTERFACE DESCRIPTION

Interface requirements defined within this document include the Hatch and Hatch Mechanisms structural, mechanical, and common crew interfaces as they apply to NASA, ESA, and JAXA.

These include sealing surfaces, hatch mechanisms, attach points, and crew interfaces. An interface block diagram is shown in Figure 3.1.1−1, Hatch To Pressurized Element Interface Block Diagram.

3.1.1.1 HATCH DESCRIPTION

Hatch Installations are structural/mechanical components that seal element ingress/egress ports and provide sealed passageways between pressurized elements. There are two types of Hatch Installations: 1) Axial Hatch Installation, and 2) Radial Hatch Installation. The Hatch Installation is composed of a Hatch Assembly and deployment tracks. The axial hatch installation seals the pressurized element axial access port. The radial hatch installation seals the pressurized element radial access port. Both Hatch Installations are fully functional: 1) on the ground with the aid of Ground Support Equipment (GSE) only when deployed vertically and 2) on orbit.

The Hatch Installation consists of the following components/mechanisms: hatch plate (with a viewing port), axial port tracks or radial port tracks, latches, pressure equalization valve, seals, hatch handles, soft handle, latch drive mechanism, alignment guide, roller (track), and the crank handle.

The Hatch perimeter seal is provided with the Hatch Installation to form the seal with the Pressurized Element bulkhead. An illustration of the Hatch to Pressurized Element bulkhead sealing surface is provided in Figure 3.1.1.1−1, Hatch to Pressurized Element Sealing Surface Interface.

3.1.1.2 PRESSURIZED ELEMENT DESCRIPTION

The Pressurized Element is any ISS Pressurized Element, which utilizes the Hatch for providing a means of sealing the passageways.

3.1.1.2.1 UNITED STATES PRESSURIZED ELEMENTS

The U.S. Pressurized Elements herein consist of the U.S. Laboratory Element (USL), Habitation Element (Hab), and Nodes.

3.1.1.2.2 INTERNATIONAL PRESSURIZED ELEMENTS

The International Pressurized Element herein consist of the Columbus Attached Pressurized Module (APM), Japanese Experiment Module-Pressurized Module (JEM)−(PM), and Mini Pressurized Logistics Module (MPLM).

3 −2

FIGURE 3.1.1−1 HATCH TO PRESSURIZED ELEMENT INTERFACE BLOCK DIAGRAM

Hatch

Structural/Mechanical Attachment

Common Crew Interfaces

Pressurized Element

Passageway/Access

3.1.1.3 INTERFACE PLANE DESCRIPTION

The Hatch to Pressurized Element interface plane lies at the Pressurized Element bulkhead. The structural/mechanical interface planes are defined at the pressure seal−to−sealing surface interface, the latch mechanism, seal separation device, axial port tracks and radial port tracks, and alignment guide−to−bulkhead interfaces.

3 −3

Hatch to PE Bulkhead Seal Interface

FIGURE 3.1.1.1−1 HATCH TO PRESSURIZED ELEMENT SEALING SURFACE INTERFACE

Hatch Passageway

Seal Surface Interface

Pressurized Element (PE) Bulkhead

PE

Bulkhead

3 −4

The Hatch Mechanisms to Common Crew interface plane lies at the pressure equalization valve, seals, handholds, view port, latch position indicator, stowage handle, and crank handle.

3.1.1.4 COORDINATE SYSTEM

The Hatch Coordinate System is shown in Figure 3.1.1.4−1, Hatch Coordinate System.

The Coordinate Systems for the Pressurized Elements shall be as defined in SSP 30219, Space Station Coordinate Systems.

3.1.1.5 ENGINEERING UNITS AND TOLERANCES

Dimensions in this document are shown in the English (inch, pound, second) system of units followed by the equivalent International System (SI) (metric) value in parenthesis.

Measurements may be verified in either system of units.

3.1.1.5.1 TOLERANCE

Linear tolerances on English dimensions are as indicated in Table 3.1.1.5.1−1, Linear Tolerances.

Linear tolerances on metric dimensions are derived from the English measurements and tolerances as defined in ASTM E−380, Standard Practice for Use of the International System of Units (SI) (The Modernized Metric System), Section 4.5. Angular tolerances are ±0.1degrees on all angles unless otherwise stated.

TABLE 3.1.1.5.1−1 LINEAR T OLERANCES

ENGLISH DIMENSION IMPLIED TOLERANCE (INCHES)

±0.030

±0.010

X.XX

X.XXX

3.1.1.6 HATCH INTERFACE FUNCTIONS

Hatch shall support the following functions at the interface to the Pressurized Element:

A. Support Structural/Mechanical Attachment

B. Support Passageway/Access

C. Support Common Crew Interfaces

3.1.1.7 PRESSURIZED ELEMENT INTERFACE FUNCTIONS

Pressurized Element shall support the following functions at the interface to Hatch:

A. Support Structural/Mechanical Attachment

B. Support Passageway/Access

C. Support Common Crew Interfaces

3 −5

+Z

+Y

DIRECTION

OF

STOWAGE

ORIGIN (0,0,0) −− Located at the intersection of the geometric center of the hatch at the INBOARD/OUTBOARD interface plane and the module center line.

FIGURE 3.1.1.4−1 HATCH COORDINATE SYSTEM

INBOARD

OUTBOARD

+X (Module Center Line)

FIGURE 3.1.1.4−2 DELETED

FIGURE 3.1.1.4−3 DELETED

FIGURE 3.1.1.4−4 DELETED

3 −6

3.1.2 INTERFACE RESPONSIBILITIES

The Hatch and Pressurized Elements shall conform to the interfaces controlled by this document.

3.1.2.1 RESPONSIBILITY FOR HATCH

Boeing Defense and Space Group (BD&SG) is responsible for designing the Hatch to the interface requirements herein.

3.1.2.2 RESPONSIBILITY FOR PRESSURIZED ELEMENT

3.1.2.2.1 RESPONSIBILITY FOR U.S. LABORA TORY ELEMENT

Unless otherwise noted herein, BD&SG is responsible for designing the USL side of the USL to Hatch interface to the requirements imposed on the Pressurized Element.

3.1.2.2.2 RESPONSIBILITY FOR HABIT ATION ELEMENT

Unless otherwise noted herein, BD&SG is responsible for designing the HAB side of the HAB to Hatch interface to the requirements imposed on the Pressurized Element.

3.1.2.2.3 RESPONSIBILITY FOR NODE

Unless otherwise noted herein, BD&SG is responsible for designing the Node side of the Node to Hatch interface to the requirements imposed on the Pressurized Element.

3.1.2.2.4 RESPONSIBILITY FOR COLUMBUS A TTACHED PRESSURIZED MODULE

Unless otherwise noted herein, ESA is responsible for designing the APM side of the APM to Hatch interface to the requirements imposed on the Pressurized Element.

3.1.2.2.5 RESPONSIBILITY FOR JAP ANESE EXPERIMENT MODULE

Unless otherwise noted herein, JAXA is responsible for designing the JEM side of the JEM to Hatch interface to the requirements imposed on the Pressurized Element.

3.1.2.2.6 RESPONSIBILITY FOR MINI PRESSURIZED LOGISTICS MODULE

Unless otherwise noted herein, ASI is responsible for designing the MPLM side of the MPLM to Hatch interface to the requirements imposed on the Pressurized Element.

3.2 INTERFACE REQUIREMENTS

3.2.1 HATCH INTERFACE REQUIREMENTS

3.2.1.1 ENVELOPE REQUIREMENTS

3.2.1.1.1 STATIC ENVELOPE

The hatch static envelope is as shown in Figure 3.2.1.1.1−1, Hatch Static Envelope and Passageway Clearance.

3 −7

Hatch Envelope

50.00 (1270.0)

4X 13.50(342.9) Radius

4X 12.00(304.8) Radius

Hatch Passageway

INBOARD

OUTBOARD

Y

Z

53.00 (1346.2)

53.00 (1346.2)

50.00 (1270.0)

FIGURE 3.2.1.1.1−1 HATCH STATIC ENVELOPE AND PASSAGEWAY CLEARANCE

X

6.3 (160.0)

3.5 (89.0)

XHATCH=0

50.00 (1270.0)

53.00 (1346.2)

NOTES: 1) Hatch tracks are not included.

2) Latch drive crank handle in stowed position.

3) Latches protrude beyond 50.00 in. when deployed.

2X 1.50 (38.1)

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3.2.1.1.2 RESERVED VOLUMES

3.2.1.1.2.1 HATCH HARDWARE

The Hatch hardware mounting and operation shall not interfere with Pressurized Element hardware.

3.2.1.1.2.2 ACCESS/PASSAGEWAYS

While in the open position, there shall be no protrusions or obstructions into the passage envelope as shown in Figure 3.2.1.1.1−1.

3.2.1.1.2.3 CENTERLINE BERTHING CAMERA SYSTEM (CBCS) ST ATIC ENVELOPE

For those Elements whose Hatches implement CBCS hardware, there shall be no protrusions or obstruction into the volumes necessary to accommodate the hardware and viewing zone for the CBCS Berthing Target or Camera mounted on the hatch. The stay out envelope is defined in Part 2, paragraph 3.1.4.5. Table 3.2.1.1.2.3−1 shows which Element Hatches implement CBCS hardware. Hatch(s) defined as CBCS Mode “ACTIVE” shall have provisions for mounting the CBCS camera and shall meet the CBCS static envelope for CBCS ACTIVE CBMs. Hatch(s) defined as CBCS Mode “PASSIVE” shall have a CBCS target and shall meet the CBCS static envelope for CBCS PASSIVE CBMs.

TABLE 3.2.1.1.2.3−1 CBCS BERTHING HARDW ARE APPLICABILITY

HATCH

LOCATION

CBCS

MODE

HATCH

LOCATION

CBCS

MODE

HATCH

LOCATION

CBCS

MODE

NODE 1 FWD ACTIVE MPLM 2 PASSIVE NODE 3 STBD ACTIVE

NODE 1 STBD N/A MPLM 3 PASSIVE NODE 3 PORT ACTIVE

NODE 1 PORT ACTIVE NODE 2 FWD ACTIVE NODE 3 ZENITH PASSIVE

NODE 1 ZENITH N/A NODE 2 STBD ACTIVE NODE 3 NADIR ACTIVE

NODE 1 NADIR ACTIVE NODE 2 PORT ACTIVE NODE 3 AFT ACTIVE

NODE 1 AFT N/A NODE 2 ZENITH ACTIVE

US LAB FWD ACTIVE NODE 2 NADIR ACTIVE

US LAB AFT PASSIVE NODE 2 AFT PASSIVE

JEM PM STBD PASSIVE CAM PASSIVE

JEM PM ZENITH ACTIVE APM PASSIVE

JEM ELM−PS PASSIVE HAB N/A

MPLM 1 PASSIVE NODE 3 FWD ACTIVE

AIRLOCK N/A HTV PASSIVE

3.2.1.2 MASS PROPERTIES

3.2.1.2.1 CENTER OF MASS

The center of mass for the Hatch Assembly is as shown in Figure 3.2.1.2.1−1, Hatch Center of Mass Envelope and Moments of Inertia.

3 −9

+ZH +ZH

+YH +XH

XH = −1.00 to +3.00 (−25.4 to +76.2) YH = −2.00 to +2.00 (−50.8 to +50.8) ZH = −3.00 to +1.00 (−76.2 to +25.4)

FIGURE 3.2.1.2.1−1 HATCH ASSEMBLY, PART NUMBER 683−13000−004 CENTER OF MASS

ENVELOPE AND MOMENTS OF INERTIA

Center of Mass Envelope:

Moments of Inertia:

IX = 19 to 40 slug−ft2 (25.7 to 54.3 kg−m2) IY = 9 to 30 slug−ft2 (12.2 to 40.7 kg−m2) IZ = 9 to 30 slug−ft2 (12.2 to 40.7 kg−m2)

3 −10

3.2.1.2.1.1 MOMENTS OF INERTIA

The moments of inertia for the Hatch Assembly are as shown in Figure 3.2.1.2.1−1.

3.2.1.2.1.2 MASS LIMITATIONS

The mass of the Hatch Installation including perimeter seals shall not exceed 240 lbs.

3.2.1.3 STRUCTURAL/MECHANICAL A TTACHMENT

The Hatch shall supply structural and mechanical provisions for the mechanical attachment of the Hatch to Pressurized Element in accordance with the loads defined in Table 3.2.1.3.2.1.1−2, Allowable Ground, Lift−Off, and Landing Load Factors.

3.2.1.3.1 STIFFNESS AT THE INTERFACE PLANE

The Hatch to Pressurized Element interface stiffness shall meet the following criteria:

A. Limit gapping at the interface to meet the seal leakage requirements in paragraph 3.2.1.3.4.1.

B. Support structural loads defined in paragraphs 3.2.1.3.2 thru 3.2.1.3.2.2.

C. Deleted.

3.2.1.3.2 STRUCTURAL LOADS

3.2.1.3.2.1 INDUCED LOADS

The hatch shall withstand any feasible combination of the following induced loads without degradation of the interfaces documented herein, for twenty−five missions including one abort.

Abort is defined as a complete orbiter mission to and from ISS without a berthing operation.

3.2.1.3.2.1.1 LIFT−OFF AND LANDING LOADS

Loads on the hatch during launch and landing are due to accoustics, random vibration, and acceleration. The acoustic spectrum during launch is as shown in NSTS−21000−IDD−ISS paragraph 4.1.1.5. The launch random vibrations are as shown in Table 3.2.1.3.2.1.1−1. The lift−off and landing load factors for the hatch are as shown in Table 3.2.1.3.2.1.1−2.

3 −11

TABLE 3.2.1.3.2.1.1−1 LAUNCH RANDOM VIBRA TION

LOCATION FREQUENCY LEVEL

Hatch X−Axis 20 Hz 0.008 g2/HzHatch X−Axis

20 − 100 Hz +6.0 dB/octave

100 − 300 Hz .20 g2/Hz

300 − 2000 Hz −9.0 dB/octave

2000 Hz .00068 g2/Hz

Composite 8.7 grms

Hatch Y and Z−Axis 20 Hz 0.002 g2/HzHatch Y and Z−Axis

20 − 80 Hz +5.0 dB/octave

80 − 200 Hz .02 g2/Hz

200 − 2000 Hz −9.0 dB/octave

2000 Hz .00002 g2/Hz

Composite 2.2 grms

TABLE 3.2.1.3.2.1.1−2 ALLOW ABLE GROUND, LIFT OFF, AND LANDING LOAD F ACTORS

Liftof f accelerations shall be combined with the random vibration levels as per SSP 30559.

Accelerations apply concurrently in all possible combinations (2)

(1) y z for each event.

CONDITION

Lift−off/ Landing

Rotational

LOAD FACTORS

± 4.2 g

± 3.6 g

± 7.8 g

± 5.8 rad/s2

± 20.0 rad/s2

± 11.2 rad/s2

DIRECTION

x y z

Rx

Ry

Rz x

3 −12

3.2.1.3.2.2 ON−ORBIT LOADS

3.2.1.3.2.2.1 ON−ORBIT CREW INDUCED LOADING

Maximum crew−induced design limit loads are as specified in SSP 50005, International Space Station Flight Crew Integration Standard.

3.2.1.3.2.2.2 DELETED

FIGURE 3.2.1.3.2.2.2−1 DELETED

3.2.1.3.3 DELETED

FIGURE 3.2.1.3.3−1 DELETED

FIGURE 3.2.1.3.3−2 DELETED

3.2.1.3.3.1 DELETED

3.2.1.3.3.2 DELETED

FIGURE 3.2.1.3.3.2−1 DELETED

3.2.1.3.3.3 MAINTENANCE ACCESS CLEARANCES

The maintenance access clearance shall comply with SSP 50005, International Space Station Flight Crew Integration Standard, requirements for Intravehicular Activity (IVA) and Extravehicular Activity (EVA) accessibility.

3.2.1.3.4 ATMOSPHERIC SEALS

The Hatch shall provide atmospheric seals at the Hatch to Pressurized Element interface. The Hatch Assembly shall conform to the geometry of the Hatch to Pressurized Element sealing interface shown in Figure 3.1.1.1−1.

3.2.1.3.4.1 SEAL LEAKAGE

While on orbit and while isolating the element internal environment from its external environment, the closed Hatch Assembly shall limit the leak rate of air through the mating access port to no more than 2.5 x 10−2 sccs at 14.7 psid, includes all seals and valve through leakage.

While being launched in the NSTS cargo bay the closed Hatch Assembly shall limit the leak rate of air through the accompanying access port to no more than 2.5 x 10−2 sccs at 14.7 psid.

3.2.1.3.5 PPRV INTERFACE

The Hatch shall allow the PE developer to install a Positive Pressure Relief Valve (PPRV) − according to drawing number 683−16321−11 in substitution of the Pressure Equalization Valve (PEV) when needed.

3 −13

3.2.1.4 INDUCED ENVIRONMENTS

3.2.1.4.1 BONDING

The Hatch to Pressurized Elements structural/mechanical interface shall meet or exceed a Class S bond in accordance with SSP 30245, Space Station Electrical Bonding Requirements.

3.2.1.5 THERMAL

The Hatch to Pressurized Element interface shall function as described herein when exposed to the thermal radiation environment per SSP 50023, Thermal Control Plan. SSP 50023 specifies math models and/or thermal design analysis criteria for interface design.

3.2.2 PRESSURIZED ELEMENT INTERFACE REQUIREMENTS

3.2.2.1 ENVELOPE REQUIREMENTS

3.2.2.1.1 ENVELOPE

The Pressurized Element shall not interfere with the Hatch hardware during Hatch stowage and deployment.

3.2.2.1.2 RESERVED VOLUMES

3.2.2.1.2.1 PRESSURIZED ELEMENT HARDWARE

The Pressurized Element shall not interfere with any Hatch hardware mounting or operation.

3.2.2.1.2.2 ACCESS/PASSAGEWAYS

While in the open position, there shall be no protrusions or obstructions into the passage envelope as shown in Figure 3.2.1.1.1−1.

3.2.2.2 MASS PROPERTIES

The Pressurized Element shall accommodate a Hatch Installation with mass properties as defined in paragraph 3.2.1.2.1.2.

3.2.2.3 STRUCTURAL/MECHANICAL A TTACHMENT

The Pressurized Element shall supply structural and mechanical provisions for the mechanical attachment of the Hatch.

3.2.2.3.1 STIFFNESS AT THE INTERFACE PLANE

The Pressurized Element to Hatch interface stiffness shall meet the following criteria:

A. Limit gapping at the interface to meet the seal leakage requirements in paragraph 3.2.1.3.4.1.

B. Support structural loads defined in paragraphs 3.2.1.3.2 thru 3.2.1.3.2.2.

3.2.2.3.2 STRUCTURAL LOADS

The Pressurized Element to Hatch interface shall survive loads induced on the Hatch as defined in Table 3.2.1.3.2.1.1−2.

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3.2.2.3.3 ACCESS/PASSAGEWAYS

3.2.2.3.3.1 DELETED

3.2.2.3.3.2 DELETED

3.2.2.3.3.3 MAINTENANCE ACCESS CLEARANCES

All maintenance access shall comply with SSP 50005 requirements for IVA accessibility.

3.2.2.3.4 ATMOSPHERIC SEALS

The Pressurized Element shall conform to the geometry of the Pressurized Element to Hatch sealing interface shown in Figure 3.1.1.1−1.

3.2.2.3.4.1 SEAL LEAKAGE

While on orbit and while isolating the element internal environment from its external environment, the closed Hatch Assembly shall limit the leak rate of air through the mating access port to no more than 2.5 x 10−2 sccs at 14.7 psid, includes all seals and valve through leakage.

While being launched in the NSTS cargo bay, the closed Hatch Assembly shall limit the leak rate of air through the accompanying access port to no more than 2.5 x 10−2 sccs at 14.7 psid.

3.2.2.3.4.1.1 LEAKAGE DETECTION

The Pressurized Element design shall incorporate provision for detecting seal leakage, for each path greater than 18 linear inches (457 mm) in length.

3.2.2.3.5 LEAK CHECK PORTS

A minimum of two leak check ports shall be located on the hatch beam (bulkhead). The leakcheck ports are required to determine the post installation leak rates of the hatch perimeter seal installed on the pressurized elements. The JEM PM, JEM ELM−PS, MPLM, and Node 2 aft bulkhead shall require only one leak check port. The post installation leak check for these four elements will be qualitative only.

3.2.2.4 INDUCED ENVIRONMENTS

3.2.2.4.1 BONDING

The Hatch to Pressurized Elements structural/mechanical interface shall meet or exceed a Class S bond in accordance with SSP 30245, Space Station Electrical Bonding Requirements.

3.2.2.5 THERMAL

The Pressurized Element to Hatch interface shall function as described herein when exposed to the thermal radiation environment per SSP 50023. SSP 50023 specifies math models and/or thermal design analysis criteria for interface design.

A - 1

APPENDIX A ABBREVIATIONS AND ACRONYMS

A.1 ABBREVIATIONS AND ACRONYMS

APM Attached Pressurized Module

ASI Agenzia Spaziale Italiana

ASTM American Society for Testing Materials

BD&SG Boeing Defense And Space Group

CBCS Centerline Berthing Camera System

CBM Common Berthing Mechanism dB decibel

DCN Drawing Change Notice

DQA Drawing Quality & Assurance

EFF effective

ESA European Space Agency

EVA Extravehicular Activity

FT. Foot

Feet

FWD Forward g acceleration on earth’s surface due to earth gravity grms gravity, root mean square

GSE Ground Support Equipment

HAB Habitation Element

HTV H−II Transfer Vehicle

Hz Hertz

ICD Interface Control Document

ICWG Interface Control Working Group

in. inch

A - 2

APPENDIX A ABBREVIA TIONS AND ACRONYMS − CONTINUED

ISS International Space Station

IRN Interface Revision Notice

IVA Intravehicular Activity

JAXA Japanese Aerospace Exploration Agency

JEM Japanese Experiment Module

JEM ELM−PS Japanese Experiment Module Experiment Logistics Module − Pressurized Section kg Kilogram(s) lb(s) pound(s)

LAB Laboratory m Meters

Mass mm Millimeter(s)

MPLM Mini Pressurized Logistics Module

N/A Not Applicable

NASA National Aeronautics and Space Administration

NASDA National Space Development Agency

NSTS National Space Transportation System

PE Pressurized Element

PEV Pressure Equalization Valve

PIRN Preliminary Interface Revision Notice

PM Pressurized Module

PPRV Positive Pressure Relief Valve

PS Pressurized Section pisd pounds per square inch differential

A - 3

APPENDIX A ABBREVIA TIONS AND ACRONYMS − CONTINUED

PUB. Publish rad/s2 radians per second square

REV. Revision sccs standard cubic centemeter per second

SI System Internationals

SSCBD Space Station Change Board Directive

SSP Space Station Program

TBD To Be Determined

U.S. United States

USL United States Laboratory