AIAA S-133-4-2013 Space Plug-and-Play Architecture Standard Physical Interface.pdf

《AIAA S-133-4-2013 Space Plug-and-Play Architecture Standard Physical Interface.pdf》由会员分享，可在线阅读，更多相关《AIAA S-133-4-2013 Space Plug-and-Play Architecture Standard Physical Interface.pdf（33页珍藏版）》请在麦多课文档分享上搜索。

1、i Standard AIAA S-133-4-2013 S-102.2.5-2009 Space Plug-and-Play Architecture Standard Physical Interface AIAA standards are copyrighted by the American Institute of Aeronautics and Astronautics (AIAA), 1801 Alexander Bell Drive, Reston, VA 20191-4344 USA. All rights reserved. AIAA grants you a licen

2、se as follows: The right to download an electronic file of this AIAA standard for storage on one computer for purposes of viewing, and/or printing one copy of the AIAA standard for individual use. Neither the electronic file nor the hard copy print may be reproduced in any way. In addition, the elec

3、tronic file may not be distributed elsewhere over computer networks or otherwise. The hard copy print may only be distributed to other employees for their internal use within your organization. AIAA S-133-4-2013 Space Plug-and-Play Architecture Standard Physical Interface Sponsored by American Insti

4、tute of Aeronautics and Astronautics Approved May 2013 Abstract The Space Plug and Play Architecture (SPA) Physical Interface specifies the mechanical requirements and physical mounting considerations for SPA devices and panels. AIAA S-133-4-2013 ii Published by American Institute of Aeronautics and

5、 Astronautics 1801 Alexander Bell Drive, Reston, VA 20191 Copyright 2013 American Institute of Aeronautics and Astronautics All rights reserved No part of this publication may be reproduced in any form, in an electronic retrieval system or otherwise, without prior written permission of the publisher

6、. Printed in the United States of America ISBN 978-1-62410-232-5 AIAA S-133-4-2013 iii Contents Foreword . v Introduction vii 1 Scope . 1 2 Tailoring . 1 3 Applicable Documents . 1 4 Vocabulary . 2 4.1 Acronyms and Abbreviated Terms . 2 4.2 Terms and Definitions 2 5 Mechanical Requirements for SPA D

7、evices 3 5.1 Device Mounting 3 5.2 Dynamic Requirements 4 5.3 Deployables, Actuators, and Moving Mechanical Assemblies. 5 5.4 Protective Covers . 5 5.5 Maintainability 5 5.6 Reporting of Device Physical Characteristics 5 6 Thermal Requirements for SPA Devices . 6 6.1 General Thermal Requirements . 6

8、 6.2 Reporting of Device Thermal Characteristics 7 7 SPA Interface Connector and Cabling Requirements . 7 7.1 Introduction 7 7.2 Hot Plugging . 7 7.3 Valid Connector Types . 7 7.4 Valid Connector Combinations 8 8 SPA Endpoint 25-Pin Micro-D Basic Connector and Cable . 9 8.1 25-Pin Micro-D Power, Dat

9、a, Sync, and Test Connector 9 8.2 SPA Endpoint Basic Interface Wiring and Cable Assemblies 11 9 SPA Endpoint 15-Pin D-Subminiature 30A Power Interface Connector and Cable 12 9.1 15-Pin D-Subminiature 30A Power Connector 12 9.2 SPA Endpoint 30A Power Interface Wiring and Cable Assemblies . 13 10 SPA

10、Endpoint 25-Pin D-Subminiature 50A Power Interface Connector and Cable 14 10.1 25-Pin D-Subminiature 50A Power Connector 14 10.2 SPA Endpoint 50A Power Interface Wiring and Cable Assemblies . 16 11 SPA Endpoint 15-Pin D-Subminiature 12A Power, Synchronization, and Test Interface Connector and Cable

11、. 17 11.1 15-Pin D-Subminiature Power, Synchronization, and Test Connector 17 AIAA S-133-4-2013 iv 11.2 SPA Endpoint 12A Power, Sync, and Test Wiring and Cable Assemblies 18 12 SPA Endpoint Dual Quadrax HSSI Connector and Cable . 19 12.1 8-Pin Dual Quadrax HSSI Connectors . 19 12.2 SPA Endpoint Dual

12、 Quadrax HSSI Wiring and Cable Assemblies 20 Annex A Sample HSSI Part Numbers (Informative) 21 Figures Figure 1 Typical SPA device mounting pattern. . 4 Figure 2 SPA endpoint basic cable detail 11 Figure 3 SPA endpoint 30A power cable detail . 14 Figure 4 SPA endpoint 50A power cable detail . 16 Fig

13、ure 5 SPA endpoint power/sync/test cable detail . 18 Figure 6 Pin locations for dual quadrax as mounted . 19 Figure 7 SPA endpoint HSSI cable detail 21 Tables Table 1 Connectors, function, and cross-reference . 8 Table 2 Valid connector combinations . 9 Table 3 SPA endpoint basic connector pin assig

14、nments . 10 Table 4 SPA endpoint 30A power interface connector pin assignments . 13 Table 5 SPA endpoint 50A power interface connector pin assignments . 15 Table 6 SPA endpoint 12A power/sync/test connector pin assignments 17 Table 7 SPA endpoint dual quadrax HSSI connector 20 Table A.1 Part list fo

15、r sample SPA data dual quadrax HSSI connector 201 AIAA S-133-4-2013 v Foreword This standard was developed through a partnership of the Air Force Research Laboratory Space Vehicles Directorate, the Air Force Office of Operationally Responsive Space, numerous government contractor teams, independent

16、contractor teams, and academic experts. The Space Plug-and-Play Architecture is a collection of standards developed to facilitate rapid constitution of spacecraft systems using modular components. In order for a SPA system to meet expected performance requirements, the SPA components and spacecraft

17、must conform to a consistent and widely agreed upon grounding approach. This document includes specifications for SPA device and panel mechanical features. This particular volume of the SPA Physical Interface Standard contains information not recorded in previous documentation. It is part of a set o

18、f 10 documents describing other components of the standard: SPA Guidebook SPA Networking Standard SPA Logical Interface Standard SPA 28V Power Service Standard SPA System Timing Standard SPA Ontology Standard SPA Test Bypass Standard SPA SpaceWire Subnet Adaptation Standard SPA System Capability Gui

19、de At the time of approval, the members of the AIAA SPA Standards Committee were: Fred Slane, Chair Space Infrastructure Foundation Jeanette Arrigo Sierra Nevada Corporation Scott Cannon Utah State University Ken Center PnP Innovations Don Fronterhouse* PnP Innovations Rod Green Design Net Engineeri

20、ng Group Jane Hansen HRP Systems Doug Harris The Aerospace Corporation, ORS Office Paul Jaffe U.S. Naval Research Laboratory Stanley Kennedy* Comtech Aero-Astro Ronald Kohl R.J. Kohl however, the device designer may choose other approaches such as heat rejection to space via radiators. The SPA elect

21、rical connector interface consists of one or more connectors that contain provisions for power, data, a timing synchronization pulse, grounding connections, and (if specified) a Test Bypass (TB) data interface. There are two broad categories of requirements specified in this document that must be sa

22、tisfied for integration of SPA devices. First, specific interface requirements must be met by both SPA devices and the SPA spacecraft, such as mounting hole pattern dimensions. Second, SPA device data must be provided with the item at the time of delivery. This data allows the SPA spacecraft develop

23、er to configure the spacecraft for proper integration and operation of the SPA device. AIAA S-133-4-2013 1 1 Scope Mechanical, thermal and electrical connector interface requirements are contained in this document. These requirements include details of the mounting hole pattern, fastener clearance-h

24、ole sizes, and thermal control approaches. Reporting requirements for mechanical and thermal design data, such as mass, center of gravity, envelope, radiator and heater locations, and so forth are described. This standard does provide some limited electrical interface requirements. Electrical power

25、service requirements are included in AIAA S-133-5-2013. A more extensive common reference for both standards is AIAA S-122-2007, Electrical Power Systems for Unmanned Spacecraft. This document identifies the significant features of the SPA interface connector(s) and the associated cabling to allow S

26、PA device and cable manufacturers to build systems that interconnect successfully with SPA-enabled spacecraft. The connector type and pin assignments are described, along with definitions of connector gender and mechanical mounting. Requirements are provided for the associated cabling, including det

27、ails of shielding, shield termination, insulation and cable impedance Optional SPA connector interfaces are described in the following sections by type (i.e., Type A, Type B, etc.). 2 Tailoring When viewed from the perspective of a specific program or project context, the requirements defined in thi

28、s Standard may be tailored to match the actual requirements of the particular program or project. Tailoring of requirements shall be undertaken in consultation with the procuring authority where applicable. NOTE Tailoring is a process by which individual requirements or specifications, standards, an

29、d related documents are evaluated and made applicable to a specific program or project by selection, and in some exceptional cases, modification and addition of requirements in the standards. 3 Applicable Documents The following documents contain provisions which, through reference in this text, con

30、stitute provisions of this standard. For dated references, subsequent amendments to, or revisions of, any of these publications do not apply. However, parties to agreements based on this standard are encouraged to investigate the possibility of applying the most recent editions of the normative docu

31、ments indicated below. For undated references, the latest edition of the normative document referred to applies. AIAA S-122-2007 Electrical Power Systems for Unmanned Spacecraft AIAA G-133-10-2013 Space Plug-and-Play Architecture Guide System Capabilities AIAA S-133-5-2013 Space Plug-and-Play Archit

32、ecture Standard 28V Power Service ECSS-E-ST-50-12C SpaceWire Cabling GSFC S311-P-4 Connectors: Electrical, Subminiature, Rack and Panel MIL-DTL-24308 Connectors: Electric, Rectangular, Nonenvironmental, Miniature, Polarized Shell, Rack and Panel MIL-DTL-83513 Connectors: Electric, Rectangular, Micro

33、miniature, Polarized Shell AIAA S-133-4-2013 2 4 Vocabulary 4.1 Acronyms and Abbreviated Terms AIAA American Institute of Aeronautics and Astronautics ANSI American National Standards Institute AWG American Wire Gauge CG center of gravity DGND digital ground HSSI high-speed serial interface IGES Ini

34、tial Graphics Exchange Specification MKS meters, kilograms, seconds MLI multi-layer insulation NASTRAN NASA Structural Analysis a finite element analysis program PPS pulse per second RTN return SPA Space Plug-and-Play Architecture SPW SpaceWire STEP Standard for the Exchange of Project Model Data TB

35、 test bypass 4.2 Terms and Definitions For the purposes of this document, the following terms and definitions apply. SPA application a software SPA component SPA compliant adheres to applicable SPA standards SPA component a SPA compliant hardware or software component SPA core component a SPA compon

36、ent that provides one or more SPA services SPA device a hardware SPA component AIAA S-133-4-2013 3 5 Mechanical Requirements for SPA Devices 5.1 Device Mounting SPA devices shall include a set of mounting holes which align to a regularly spaced grid pattern. (Example: Figure 1 Typical SPA device mou

37、nting pattern). In the typical implementation, SPA devices are mounted to the spacecraft structure with fasteners passing through clearance holes located on the device and mating with threaded features on the spacecraft. 5.1.1 Mounting Method SPA devices shall provide clearance holes to accommodate

38、mounting fasteners. 5.1.2 Recommended Fastener Size Fastener type, size, and material are to be determined by the integrator of the SPA device. The fastener clearance hole sizes specified herein are intended for ANSI #8 (0.164 in.) or Metric M4 sized fasteners. 5.1.3 Mounting Pattern The mounting pa

39、ttern shall be a two-dimensional grid pattern with a typical center-to-center hole spacing of 5.0 cm. 5.1.4 Number of Mounting Holes The number of mounting holes and overall mounting pattern size shall be determined by the device designer in accordance with the strength requirements for the end-use.

40、 However, it is recommended there shall not be less than two mounting holes used for an individual device. 5.1.5 Device Mounting Hole Size and Positional Tolerance Device mounting features shall be a 0.478 cm (0.188 in.) nominal diameter clearance holes. Device mounting hole diameter tolerance shall

41、 be -0.003 / +0.028 cm (-0.001 / +0.011 in). Device mounting hole patterns shall maintain a positional tolerance of 0.025 cm (0.010 in) at a nominal mounting hole diameter of 0.188 in. The device mounting hole positional tolerance shall be at maximum material condition. AIAA S-133-4-2013 4 Figure 1

42、Typical SPA device mounting pattern. (Primary dimensional units are in centimeters, secondary units are in inches.) 5.1.6 Mounting Fastener Access The device design shall allow access to mounting fasteners for fastener installation, run-in, and application of final torque. 5.1.7 Mounting Surface Fla

43、tness The device and spacecraft mounting surfaces are recommended to have a flatness of no more than 0.0005 in. per 1.0 in. of linear distance, or 0.008 in., whichever is greater. EXAMPLE A device with a 30 cm (11.811 in.) linear dimension of mounting footprint is recommended to be flat within 0.008

44、 in. A device with a 60 cm (23.622 in.) mounting footprint is recommended to be flat within 0.012 in. 5.1.8 Mounting Surface Conductivity The mounting surfaces shall be electrically conductive such that the device and spacecraft are bonded with a maximum resistance of 2.5m across each faying surface

45、. This is consistent with AIAA S-122-2007. 5.1.9 Mounting Surface Properties 5.1.9.1 All metal surfaces shall be passivated, plated, treated, or otherwise finished to provide an inert exposed surface to prevent corrosion. 5.1.9.2 Surface treatments shall not inhibit electrical conductivity as specif

46、ied in section 5.1.8 of this document. 5.2 Dynamic Requirements Two cases for SPA device dynamics are provided under this specification: AIAA S-133-4-2013 5 a) SPA devices shall have no significant modes below 100Hz, or, b) In cases where a SPA device has significant modes below 100Hz, a structural

47、mathematical model (finite-element model) shall be provided with delivery of the device, sufficiently detailed to allow integration with the spacecraft structural model for prediction of worst-case deformations and stresses. It is recommended that the model shall be supplied in a NASTRAN-compatible

48、format. 5.3 Deployables, Actuators, and Moving Mechanical Assemblies 5.3.1 In order to meet the goals of rapid integration, SPA devices shall not employ pyrotechnic or explosive actuators such as initiators. 5.3.2 This type of deployment mechanism requires special consideration and clearance on the

49、structure that will increase the complexity of device placement. Nonexplosive actuators shall be used for all deployments and actuations, such as shape-memory alloy devices, paraffin actuators, or equivalent. 5.3.3 Shock sensitive devices and locations shall be identified. 5.4 Protective Covers 5.4.1 Protective covers shall be provided to preclude entrance of foreign particles to sensitive areas and to preclude damage during handling, assembly, integration, and test. 5.4.2 Protective covers not required for o