SAE AS 47643-2017 Verification Methods for MIL-STD-1760E Aircraft Station Interfaces.pdf

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1、 _ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising ther

2、efrom, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2017 SAE International All rights reserved. No part of this

3、publication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-49

4、70 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/standards.sae.org/AS47643 AEROSPACE STANDARD AS47643 Issued 2017-03 Verification Methods for MIL-STD-1760E Aircr

5、aft Station Interfaces RATIONALE MIL-STD-1760 has now reached Revision E and has introduced changes to the interface standard such that an updated version of the SAE verification standard is essential. FOREWORD This SAE Aerospace Standard (AS) is a document for validating aircraft station compliance

6、 with the interface requirements of MIL-STD-1760E. This document was prepared by the SAE AS-1B, MIL-STD-1760 User Task Group to provide industry guidelines to the U.S. Governments MIL-STD-1760E. This document was prepared to minimize unnecessary or undesirable variations in Aircraft Station Interfac

7、e verification against MIL-STD-1760E. For verification of aircraft designed to MIL-STD-1760A Notice 2 AS4764 Issued 1995-04 applies. For verification of aircraft designed to MIL-STD-1760B Notice 3 AS47641 Issued 1999-08 applies. Please send any comments to: SAE International Attention: AS-1B 400 Com

8、monwealth Drive Warrendale, PA 15096-001 SAE INTERNATIONAL AS47643 Page 2 of 190 TABLE OF CONTENTS 1. SCOPE 4 1.1 Purpose . 4 1.2 Application . 4 1.3 Tailoring . 4 1.4 Limitations . 4 1.5 Identification System . 4 2. REFERENCES 5 2.1 Applicable Documents 5 2.1.1 SAE Publications . 5 2.1.2 U.S. Gover

9、nment Publications 5 2.1.3 NATO Publications 5 2.2 Abbreviations and Acronyms . 6 2.3 Definitions 8 3. GENERAL REQUIREMENTS . 8 3.1 Introduction 8 3.2 Verification Techniques . 8 3.2.1 Test . 8 3.2.2 Analysis . 9 3.2.3 Inspection 9 3.3 Tailoring . 9 3.4 Test Conditions . 9 3.5 Measuring Equipment .

10、9 3.5.1 Equipment Type 9 3.5.2 Equipment Accuracy . 11 3.6 Operation of an ASI Under Test 11 3.7 Test Data . 11 4. DETAILED REQUIREMENTS . 11 4.1 Introduction 11 4.2 High Bandwidth (HBW) . 12 4.2.1 General Requirement 12 4.2.2 Special Considerations 13 4.3 MIL-STD-1553 (MUX) Data . 13 4.3.1 General

11、Requirements 13 4.3.2 Special Considerations 15 4.4 Low Bandwidth (LBW) . 15 4.4.1 General Requirement 15 4.4.2 Special Considerations 15 4.5 Release (REL) Consent 16 4.5.1 General Requirement 16 4.5.2 Special Considerations 16 4.6 Interlock (INL) 17 4.6.1 General Requirement 17 4.6.2 Special Consid

12、erations 17 4.7 Address (ADR) 17 4.7.1 General Requirements 17 4.7.2 Special Considerations 18 4.8 Structure Ground (GND) . 18 4.8.1 General Requirement 18 4.8.2 Special Considerations 19 4.9 28 VDCP . 19 4.9.1 General Requirement 19 4.9.2 Special Considerations 20 4.10 115 V/200 VACP . 21 4.10.1 Ge

13、neral Requirement 21 4.10.2 Special Considerations 22 SAE INTERNATIONAL AS47643 Page 3 of 190 4.11 270 VDCP . 22 4.11.1 General Requirement 22 4.11.2 Special Considerations 23 4.12 Fiber Optics . 24 4.12.1 General Requirement 24 4.12.2 Special Considerations 24 4.13 Initialization Procedures 24 4.13

14、.1 General Requirement 24 4.13.2 Special Considerations 25 4.14 Connector Intermateability 25 4.14.1 General Requirement 25 4.14.2 Special Considerations 26 4.15 Umbilical Cables 26 4.15.1 General Requirement 26 4.15.2 Special Considerations 27 4.16 Fiber Channel Interface (FCI) . 28 4.16.1 General

15、Requirements 28 4.16.2 Special Considerations 28 5. NOTES 28 5.1 Guidelines for Verification Plan Development . 28 5.1.1 Introduction 28 5.2 Test Sequence 29 5.3 Revision Indicator 29 APPENDIX A VERIFICATION METHODS 30 TABLE 1 HIGH BANDWIDTH VERIFICATION MATRIX . 12 TABLE 2 MIL-STD-1553 DATA BUS INT

16、ERFACE VERIFICATION TEST COMPLIANCE MATRIX 14 TABLE 3 LOW BANDWIDTH VERIFICATION MATRIX 15 TABLE 4 RELEASE CONSENT VERIFICATION MATRIX 16 TABLE 5 INTERLOCK VERIFICATION MATRIX . 17 TABLE 6 ADDRESS VERIFICATION MATRIX 18 TABLE 7 STRUCTURE GROUND VERIFICATION MATRIX 19 TABLE 8 28 VDC POWER VERIFICATIO

17、N MATRIX 20 TABLE 9 115 V/200 VAC POWER VERIFICATION MATRIX 21 TABLE 10 270 VDC POWER VERIFICATION MATRIX 23 TABLE 11 FIBER OPTIC VERIFICATION MATRIX . 24 TABLE 12 INITIALIZATION VERIFICATION MATRIX . 25 TABLE 13 CONNECTOR INTERMATEABILITY VERIFICATION MATRIX . 26 TABLE 14 UMBILICAL VERIFICATION MAT

18、RIX 27 TABLE 15 FIBER CHANNEL INTERFACE VERIFICATION TEST COMPLIANCE MATRIX 28 SAE INTERNATIONAL AS47643 Page 4 of 190 1. SCOPE This document establishes techniques for validating that an Aircraft Station Interface (ASI) complies with the interface requirements delineated in MIL-STD-1760 Revision E.

19、 1.1 Purpose The purpose of this document is to provide methods for validating that an aircrafts store electrical interface complies with the aircraft station interface (ASI) requirements of MIL-STD-1760. This document provides a modular, independent set of methods for each of the requirements in MI

20、L-STD-1760 that applies to aircraft requirements. For verification of aircraft designed to MIL-STD-1760A, AS4764 applies. For verification of aircraft designed to MIL-STD-1760B, AS47641 applies. For verification of aircraft designed to MIL-STD-1760C, AS47642A applies. 1.2 Application The methods her

21、ein apply to initial verification of an aircraft design to the requirements of MIL-STD-1760 and are expected to be conducted as part of aircraft design verification (as opposed to qualification test, quality conformance test, flight line test, etc.). The methods contained in this document are suffic

22、ient to cover the Class I interface. Aircraft with Class II ASIs will use the appropriate subset of these Class I methods. 1.3 Tailoring The methods contained herein are general methods for conducting ASI verification and, as such, do not provide detailed procedures for these methods. It is intended

23、 that detailed procedures for verification of a specific ASI will be covered by tailored test plans and procedures prepared specifically for that aircraft. These tailored test procedures would, for example, address those peculiar commands required to step through sufficient operations and states to

24、demonstrate compliance with the particular aircraft/store electrical interconnection system (AEIS) requirement under test. 1.4 Limitations The methods contained herein are based on MIL-STD-1760E. In addition, this document addresses testing compliance of an aircraft to MIL-STD-1760 based on the assu

25、mption that all tests are conducted at the aircrafts ASI connector and measurements of performance occur only at this ASI. 1.5 Identification System The test methods contained in this document are designated by an alphanumeric identification scheme. Each method is identified by a three alphabetical

26、character combination followed by a three-digit number. The meaning of the first three individual letters is: a. HBW: High Bandwidth Interface b. MUX: Digital Multiplex Data Interface c. LBW: Low Bandwidth Interface d. REL: Release Consent Interface e. INL: Interlock Interface f. ADR: Address Interf

27、ace g. GND: Structure Ground h. 28 V: 28 VDC Power Interface i. ACP: 115 V/200 VAC Power Interface SAE INTERNATIONAL AS47643 Page 5 of 190 j. HVP: 270 VDC Power Interface k. FOC: Fiber Optic Channel l. INT: Initialization m. CON: ASI Connector n. UMB: Umbilical Cable o. FCI: Fiber Channel Interface

28、The three numbers following the letter code is a sequentially assigned number such that numbers 101 through 199 are for ASI requirements and 201 through 299 are reserved for mission store interface (MSI) requirements. When applicable, the letter following this three-digit number is the test method r

29、evision letter. For example, HBW101 represents the original version of the first test requirement (TR) for the ASI HBW interface while HBW101A represents the first revision of that requirement. 2. REFERENCES 2.1 Applicable Documents The following publications form a part of this document to the exte

30、nt specified herein. The latest issue of SAE publications shall apply. The applicable issue of other publications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited herein, the text of this document takes pr

31、ecedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. ISO 10012:2003 Measurement Management Systems Req. for measurement process and measuring equipment 2.1.1 SAE Publications Available from SAE International, 400 Commo

32、nwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or +1 724-776-4970 (outside USA), www.sae.org. AS4113 Verification Test Plan for the Digital Time Division Command/Response Multiplex Data Bus, Bus Controllers 2.1.2 U.S. Government Publications Copies of these docum

33、ents are available online at http:/quicksearch.dla.mil. MIL-C-38999 Connectors Electrical, Circular, Miniature, High Density, Quick Disconnect MIL-STD-704 Electric Power, Aircraft, Characteristics and Utilization of MIL-STD-1498 MIL-STD-1553 Digital Time Division Command/Response Multiplex Data Bus

34、MIL-STD-1560 Insert Arrangements for MIL-C-38999 and MIL-C-27599 Electrical Circular Connectors MIL-STD-1760E Aircraft/Store Electrical Interconnection System 2.1.3 NATO Publications Available from the Document Automation and Production Service (DAPS), Building 4/D, 700 Robbins Avenue, Philadelphia,

35、 PA 19111-5094, Tel: 215-697-6257, http:/assist.daps.dla.mil/quicksearch/. STANAG 3350 AVS Analogue Video Standard for Aircraft Applications SAE INTERNATIONAL AS47643 Page 6 of 190 2.2 Abbreviations and Acronyms AC Alternating Current ACP Alternating Current Power ADR Address AEIS Aircraft/Store Ele

36、ctrical Interconnection System AS Aerospace Standard ASD Avionics Systems Division ASI Aircraft Station Interface AUX Auxiliary BC Bus Controller COM Communication CON Connector CSSI Carriage Store Station Interface dB Decibel dBm Decibels above 1 mW DC Direct Current DCP Direct Current Power DoDISS

37、 Department of Defense Index of Specifications EIA Electronic Industries Association FOC Fiber Optic Channel GHz Gigahertz GND Ground HB High Bandwidth HBW High Bandwidth HVP High Voltage Power Hz Hertz ICD Interface Control Document INL Interlock INT Initialization SAE INTERNATIONAL AS47643 Page 7

38、of 190 kHz Kilohertz LB Low Bandwidth LBW Low Bandwidth mA Milliamp MHz Megahertz MIL Military ms Millisecond MSG Message MSI Mission Store Interface MUX Multiplex N/A Not Applicable P-P Peak-to-Peak REL Release RNASP Routing Network Aircraft System Port RT Remote Terminal RMS Root Mean Squared STAN

39、AG Standardization Agreement STD Standard TDP Technical Data Package TR Test Requirement TRMS True Root Mean Squared UUT Unit Under Test V Volts VSWR Voltage Standing Wave Ratio SAE INTERNATIONAL AS47643 Page 8 of 190 2.3 Definitions 2.3.1 AEIS TERMS Terminology peculiar to the AEIS is defined in MI

40、L-STD-1760. 2.3.2 UNIT UNDER TEST (UUT) The UUT is defined as the “production configuration aircraft” undergoing verification tests. The test point for all electrical tests is the ASI. 2.3.3 VERIFICATION Verification is defined as the process whereby the final design of an AEIS is evaluated to deter

41、mine its compliance with the requirements imposed by MIL-STD-1760. This compliance evaluation is accomplished using a combination of techniques including tests, analysis, and inspections. This verification is conducted to determine that the design complies with MIL-STD-1760 under nominal ambient con

42、ditions. While this verification may be part of an aircrafts qualification test (if specified in the aircrafts system specification), it is not necessarily intended to be conducted under all aircraft environmental and operational conditions and, as such, does not specifically “qualify” the aircraft

43、to its system specification/interface control document (ICD) requirements. The addition of a new column, titled “Shall Statement”, in each of the fourteen (14) Verification Tables, clearly identifies the requirement to be validated. The numbers in the column are directly linked to the corresponding

44、“shall” statement in the order that it appears in the MIL-STD-1760 paragraph. For example, In Table 6 Address Verification Matrix, MIL-STD-1760 paragraph 5.1.6, the first two (2) shall statements, as they appear on 1760, are validated using test method ADR101 while the third (3) shall statement is v

45、alidated using test method ADR102. In this way, the requirement is easily identified, traceable to MIL-STD-1760 and therefore must be followed or adhered to (tested) to verify overall system compliance to MIL-STD-1760. 3. GENERAL REQUIREMENTS 3.1 Introduction As part of an aircrafts qualification to

46、 its system specification requirements, the AEIS design shall be validated against the requirements of MIL-STD-1760. The specific verification effort for a given ASI will be defined in a test plan prepared for the AEIS. The methods defined in this document provide guidance for the preparation of the

47、 test plans by delineating the pertinent requirements in MIL-STD-1760 and verification methodology. For those requirements that can be validated by test or analysis, this document also provides test techniques. Section 4, herein, presents verification details associated with each requirement in MIL-

48、STD-1760. 3.2 Verification Techniques Verification of a design to the requirements of MIL-STD-1760 can be accomplished through the use of a number of techniques. A general listing of these techniques includes: a. Test b. Analysis c. Inspection 3.2.1 Test Tests are those methodologies that measure ch

49、aracteristics or performance under specified conditions. Tests also include techniques that “demonstrate” operation of circuitry or system performance. SAE INTERNATIONAL AS47643 Page 9 of 190 3.2.2 Analysis Analyses are those methodologies that verify design compliance with the designated requirements of MIL-STD-1760 without performance of verification test or inspection. These methodologies will primarily be based on technical evalu