1、Ob95534 0002084 930 pecial Copvright Notice o 1995 by the American Institute of Aeronautics and Astronautics. All rights reserved. STD-AIAA G-072-ENGL 199.5 0b95.534 0002205 37b ANSVAIAA G-072-1995 Utility Connector Interfaces for Serviceable Spacecraft STD-AIAA G-072-ENGL 1795 m Ob7553Li 000220b 20
2、2 m AIAA G-072-1995 Guide for Utility Connector Interfaces for Serviceable Spacecraft Sponsor American Institute of Aeronautics and Astronautics Abstract This Guide provides technical information for the development of spacecraft utility connectors. The perspective on utility connectors has been obt
3、ained from aerospace historical applications on commercial and military aircraft, rocket launch vehicles, and NASA Programs. Designers and project managers of future spacecraft can benefit from this document. A utility connector contains a multiple of utilities, which may include electrical power, d
4、ata, microwave, fiber optic, and fluids. This document classifies utility connectors as follows: Class I - Manual or EVA, Class II - Robotic System, and Class III - Automatic System. The use of standard utility connectors will contribute to cost effective on-ground and on-orbit servicing functions.
5、STD.AIAA G-072-ENGL 1995 W Ob9553Li 00112207 149 ANSVAIAA R-064-1994 Published by American Institute of Aeronautics and Astronautics 1801 Alexander Bell Drive, Reston, VA 22091 Copyright O 1996 American Institute of Aeronautics and Astronautics All rights reserved No part of this publication may be
6、reproduced in any form, in an electronic retrieval system or otherwise, without prior written permission of the publisher, Printed in the United States of America STDmAIAA L-072-ENGL 1995 Db75534 0002208 085 AIAA G-072-1995 Contents Paragraph Page . Foreword . III 1 .o 1.1 1.2 1.3 1.4 1.5 2.0 3.0 3.
7、1 3.2 3.3 3.4 3.5 3.6 3.7 3.8 3.9 3.10 3.1 1 3.12 3.13 3.1 4 3.1 5 3.16 3.1 7 3.18 3.1 9 4.0 4.1 4.2 4.3 4.4 4.5 INTRODUCTION . 1 Scope 1 Purpose . 1 Application . 1 Intended Use . 1 Applicable Documents 1 DEFINITIONS ,l GENERAL REQUIREMENTS 2 Standard Units of Measure 2 Coordinate System . 2 Interf
8、ace Considerations . 2 Design Considerations 3 Pin and Port Shape . 3 Definition of Mate/Demate Sequence 3 Application of Requirements . 3 Materials . 3 Interchangeability . 3 Protective Covers . 4 Launch Vehicle Safety 4 Failure Tolerance 4 Failure Deterrent . 4 Position Indicators 4 Indexing (Keyi
9、ng) . 4 Maintainability . 4 ORU Utility Connectors . 5 Non-Brazed or Non-Welded Fluid Lines . 5 Accessibility . 5 DETAILED REQUIREMENTS 5 Mechanical Design . 5 Electrical Design . 6 Fluid Design . 7 Optical Design 7 Thermal Design 7 iii AIAA G-072-1995 APPENDIX A A.l A.l.l A.2 A.2.1 A.2.2 A.2.3 A.2.
10、4 A.2.5 A.3 A.3.1 A.3.2 A.5 A.5.1 A.5.2 A.5.3 A.5.4 A.5.5 EXAMPLES OF AIRCRAFT UTILITY CONNECTORS 11 F-1 1 1 Pylon Blind Mate Disconnect . 11 EXAMPLES OF MISSILE UTILITY CONNECTORS 13 High Endoatmospheric Defense Interceptor (HEDI) Missile Umbilical Connector . 13 SRAM Missile Umbilical Connector .
11、15 Peacekeeper Missile Umbilical Connector 17 ICBM Umbilical Connector . 19 Minuteman Missile Umbilical Plug . 21 1 EXAMPLES OF SPACECRAFT CLASS I MANUAL OR EVA OPERATED SKYLAB Utility Connector . 23 Columbus Utility Connector . 24 EXAMPLES OF SPACECRAFT CLASS III AUTOMATIC UTILITY CONNECTORS Orbiti
12、ng Maneuvering Vehicle (OMV) Fluid Interface System . 25 Automated Umbilical Connector . 27 Explorer Platform Payload Equipment Deck 31 Multimission Modular Spacecraft Module Structure Assembly 33 Resupply Interface Mechanism 29 iv STD-AIAA L-072-ENGL L995 Ob95534 0002210 733 D Foreword This Guide f
13、or Utility Connector Interfaces for Serviceable Spacecraft has been sponsored by the American Institute of Aeronautics and Astro- nautics as part of its Standards Program. This Guide provides technical information for the development of spacecraft utility connectors. The perspective on utility conne
14、ctors has been obtained from aerospace historical applications on commercial and military aircraft, rocket launch vehicles, and NASA programs. Designers and project managers of future spacecraft can benefit from this document. A utility connector contains a multiple of utilities, which may include e
15、lectrical power, data, microwave, fiber optic, and fluids. This document classifies utility connectors as fol- lows: Class I - Manual or EVA, Class II - Robotic System, and Class III - Automatic System. The use of standard utility connectors will contribute to cost effective on-ground and on-orbit s
16、ervicing functions. The AIAA Standards Procedures provide that all approved Standards, Recommended Practices, and Guides are advisory only. Their use by any- one engaged in industry or trade is entirely volun- tary. There is no prior agreement to adhere to any AIAA standards publication and no commi
17、tment to conform to or be guided by any standards re- port. AIAA G-072-1995 Lana Arnold (Lockheed Martin) Steve Chucker (McDonnell Douglas) Ana del la Cruz (Kelly Air Force Base) Bob Davis (NASA Goddard Space Flight Center, Bob Dellacamera (McDonnell Douglas) Paul Elwell (Moog, Inc.) Glen Glassford
18、(Oceaneering Space Systems) Barney Gorin (Fairchild Space Company) Arnold Greenman (Space SystemsLoral) Albert G. Haddad (Lockheed Martin) Allan Leary (Ballistic Missile Defense Off ice) Neville Marzwell (Jet Propulsion Laboratory) Nancy Munoz (NASA Johnson Space Center) Robert Radtke (Tracor Applie
19、d Science) Leo Stytle (TRW Civil contains socket contacts. Receptacle - Connector half, with mounting flange typically hard-mounted to a panel, which re- ceives the plug housing; contains pin contacts. Robotic Mate/Demate - Utility connector operation with the aid of a robotic system manipulation wi
20、th or without a man in the control loop. Scoop Proof - Scoop proof refers to the impossibility of a mating plug connector being inadvertently cocked into a mating receptacle and damaging or electrically shorting the contacts. Self-aligning - Allows engagement to be accom- plished with angular/latera
21、l/rotational misalignment, within specified limits. Serviceable Spacecraft - Spacecraft specifically designed for ease of on-orbit servicing, including replacement of modular parts and refueling, reloading. Servicee - The spacecraft side of the utility con- nector. Servicer - The supply side of the
22、utility connector. TBD - To be determined Utility Connector - Also called a coupling or quick disconnect connector, consisting of a Servicer half and Servicee half, which when mated permits the safe transfer of utilities, including electric power, data, microwave signal, fiberoptic communication, an
23、d fluid flow across the interface. 3 .O GENERAL REQUIREMENTS 3.1 Standard Units of Measure Units designed to the requirements of this guide- line should incorporate the International System of units (SI) as the basic measurement system. These units are defined in DoD-Std-l376a. For measurement value
24、s not covered in DoD-Std- 1476a, the document Fed-Std-376a may be used as a supplement. Linear dimensions should be in whole millimeters. 3.2 Coordinate System An X, Y, Z three axis orthogonal coordinate sys- tem is defined for utility connectors, with the X coordinate is parallel to the connector i
25、nterface. The Y and Z axes are, by definition, perpendicu- lar to the X axis with the Z axis vertical toward a designated up index point around the X axis. The Y axis is perpendicular to the Z axis and is ori- ented lateral to the designated up index of the Z axis. 3.3 Design Considerations The desi
26、gn and mechanical interfaces should be kept as simple as possible, 3.4 Interface Considerations Considerations for the design of utility connector interface hardware must compensate for the worst case uncertainties to assure a successive mate and demate without damage to the internal connections. An
27、 example of a typical interface footprint with power, data, fiberoptic and fluid connections is illustrated in Figure 1. Conditions which must be considered in the inter- face design are: mate/demate engagement tol- erance, activation force limits, engagement over- center force limits, mounting stru
28、cture integrity requirements, impact momentum tolerance, tip- off dynamics limits, emergency disconnect provi- sions, thermal distortions, shell, electrical, data, 2 STD-AIAA G-072-ENGL L995 D Ob9553q 0002213 4LI2 microwave, fiberoptic and fluid interfaces align- ment, electrostatic differences at c
29、ontact, sizing, mass (lightest design for required strength), and reliability. 3.5 Pin and Port Shape Electrical pins, fiberoptic fiber ends, and fluid ports should be clearly identified and physically incompatible when they differ in content (e.g., dif- ferent voltages, fluids, etc.). (NASA-30550)
30、3.6 Definition of Mate / Demate Sequence 3.6.1 Initial Condition Capture / Centering Guide with suitable alignment the utility connector plug and receptacle shells into coincidence on the path required to complete a soft docking ac- tion. Fluid ports require added provision for a two phase engagemen
31、t: first, latching to resist pres- sure separation, and second, opening to permit fluid flow. AIAA G-072-1995 3.7.2 Utility Connector MateDemate Classifications When the engagement force exceeds the capac- ity for manual or EVA operation, it is necessary to use mechanical assistance for mate/demate.
32、 The mechanisms include special hand tools, and robotic and automatic systems. 3.7.2.1 Extravehicular Activity Class I - Manual or Manual or EVA utility connector activation may be performed when the z axis engagement or dis- engagement force does not exceed 8 Newton?s (20 pounds). 3.7.2.2 Class II
33、- Robotic System EVA and robotically compatible operations may be performed when z axis engagement or disen- gagement force are less than 8 newtons (20 pounds), or 40 newtons (100 pounds) when au- tonomous robotic systems are used. 3.7.2.3 Class 111 - Automatic System 3.6.2 Mate Complete the attachm
34、ent sequence contacting and completing the connection of utilities and locking the connector shells. Automatic operations may be performed when the z axis engagement or disengagement force exceeds the capacity of EVA and Robotic Systems, and when automatic operations are feasible. 3.6.3 Demate 3.8 M
35、aterials With a minimized change in dynamics, the above sequence is reversed. 3.7 Application of Requirements The connector should be constructed of materi- als that will not be affected by fluid media, space environment, or service life cycle specified. Detailed requirements described in this Guide
36、 3.9 Interchangeability can to be applied as appropriate to all spacecraft utility connectors. 3.9.1 Connectors 3.7.1 Ground-based and On-orbit Connectors of the same part number should be Operations interchangeable. This includes like assemblies, subassemblies, and replaceable parts. (NASA- Each op
37、eration requires different operating prac- 30550) tices. Where crew or robotic interfaces are in- volved, both NASA-Std-3000, Man-System 3.9.2 Resupply and docking/berthing Integration Standard and NASA SSP 30550, System Robotic Systems Integration Standard, applies. Where practical, have resupply t
38、ransfer system and docking and berthing system commonality (JSC 23920). 3 AIAA G-072-1995 3.1 O Protective Covers If required by the part standard drawing, covers are generally be required for each demated con- nector half as a means of protecting all exposed critical surfaces, seals, etc. from dama
39、ge and to minimize the entry of contaminants. Each cover should be tethered to its respective half. 3.1 3.3 Multiple Failures Failure propagation protection should be pro- vided such that transient out-of-tolerance condi- tions or component failures should not cause other component or subsystem fail
40、ures. (NASA- 30550) 3.1 3.4 Threaded Fasteners 3.1 1 Launch Vehicle Safety The connector should comply with the applicable safety requirement of launch and transportation vehicles in both the mated and demated posi- tions, and during all operational phases associ- ated with its use. 3.1 2 Failure To
41、lerance. 3.1 2.1 Critical Hazards Critical hazards should be controlled such that no single failure or operator error can result in dam- age to launch equipment, a disabling personnel injury, or the use of unscheduled safety proce- dures that affect operations. A utility connector hazard is exemplif
42、ied by the case of incompatible connector mating caused arcing in an explosive environment. 3.1 2.2 Catastrophic Hazards Catastrophic hazards should be controlled such that no single or combination of two failures or operator errors can result in the potential for a dis- abling or fatal personnel in
43、jury or loss of the launch vehicle, ground facilities, or equipment. 3.1 3 Failure Deterrent Positive locking on threaded parts and fasteners should be incorporated to prevented loosening during service. The use of safety wire should be pro hi bited. 3.1 3.5 Installation Backward or improper install
44、ation of unidirectional components or piece parts should be prevented by use of non-symmetry of configuration, differ- ent connecting sizes, or other comparable means. 3.1 3.6 Sliding Fits Sliding fits should be designed to preclude fric- tional failures and/or binding. (NASA-30550) 3.13.7 Induced E
45、nvironment Fatigue failure resulting from flow-induced vibra- tion in flexible sections should be prevented by proper design practices, engagement approach, and materials selection. 3.1 4 Position Indicators The connector should be designed with appro- priate indicators to provide indication that th
46、e connector has been fully mated or demated. The connector should be designed such that: 3.1 5 Indexing (Keying) 3.13.1 Liquid Traps Built-in liquid traps, which would cause malfunc- tion or failure, should be eliminated. (NASA- 30550) 3.13.2 Blind Pockets Hidden corrosion could develop in blind poc
47、kets and should therefore be prohibited. (NASA- 30550) The connector should incorporate an indexing feature to prevent mating with other connector part numbers and/or with the same connector pari number. (NASA-30550) 3.1 6 Maintainability When practical, the connector should be de- signed so that ma
48、intenance, overhaul, or adjust- ment during its operating life can be accom- plished on the sewicee half. 4 r- STD-AIAA G-072-ENGL L995 m Ob7553Li 00022L5 215 AIAA G-072-1995 3.1 7 ORU Utility Connectors ORUs requiring electrical power and data trans- fer should be designed with an integrated utilit
49、y connector. (NASA-30550) 3.1 8 Non-Brazed or Non-Welded Fluid Lines All non-brazed or non-welded liquid lines should be provided with a convenient to use, perma- nently installed connectors that permit in-orbit maintenance. (NASA-Std-3000). spacecraft structure, and should be capable of abotddisengagement by manual, manually com- manded, or autonomous means. Following emergency disconnection the design should be resetable to its pre-emergency disconnect oper- ational status. There should be no degradation in capability as a result of emergency disconnect. 4.1.2 EVA Handholds Where a
