SAE-AS-94900-2007.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 there
2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2007 SAE International All rights reserved. No part of this publication m
3、ay 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: 724-776-4970 (outside USA)
4、 Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org AS94900 AEROSPACE STANDARD Issued 2007-07 Aerospace - Flight Control Systems - Design, Installation and Test of Piloted Military Aircraft, General Specification For RATIONALE This document provides a comprehensive de
5、finition of the general performance, design, test, development and quality assurance requirements for military aircraft Flight Control Systems. Specific focus areas are flight safety and integration of the Flight Control System with other aircraft systems and subsystems, such as the electrical and h
6、ydraulic systems. It includes the applicable legacy requirements from U.S. Military Specifications MIL-H-9490D, and the inactive MIL-F- 18372. TABLE OF CONTENTS 1. SCOPE4 2. REFERENCES4 2.1 Applicable Documents 4 2.1.1 SAE Publications.4 2.1.2 U.S. Government Publications5 2.1.3 Other Publications.8
7、 2.2 Abbreviations, Acronyms, Symbols and their Definitions .9 2.3 Definitions .12 2.3.1 Classifications, Flight Categories, and Envelopes12 2.3.2 FCS Classifications.14 2.3.3 FCS Operational State Classifications15 2.3.4 FCS Criticality Classifications.15 2.3.5 Structural Classifications.16 2.3.6 D
8、ocument Definitions16 3. REQUIREMENTS.16 3.1 General System Requirements.16 3.1.1 Safety and Operability Considerations .16 3.1.2 Reliability Considerations18 3.1.3 Redundancy Considerations.18 3.1.4 Maintainability Considerations19 3.1.5 Survivability Requirements .20 3.1.6 Electromagnetic Interfer
9、ence (EMI) Limits24 3.2 System Performance Requirements.24 3.2.1 General FCS Performance Requirements24 3.2.2 Primary FCS Requirements31 3.2.3 Secondary FCS (SFCS)33 3.2.4 Automatic Flight Control Function (AFCF) Performance Requirements 35 3.3 System Testability Requirements .50 3.3.1 System Test a
10、nd Monitoring Provisions .50 3.3.2 Built-In-Test (BIT) Equipment .50 3.3.3 Maintenance BIT.51 3.3.4 Preflight or Pre-engage BIT for Fly-By-Wire (FBW) Systems.51 3.3.5 Preflight BIT Status Annunciation.51 Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/59
11、13977001 Not for Resale, 12/04/2007 19:54:44 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AS94900 - 2 - 3.3.6 Portable Test Equipment 51 3.3.7 Use of Cockpit Instrumentation.51 3.3.8 Ground Power Requirements for System Test.51 3.3.9 Protection Against Dormant Failur
12、es52 3.4 System Design Requirements 52 3.4.1 System General Design Requirements 52 3.4.2 Mechanical FCS Design .52 3.4.3 Fixed Wing V/STOL Aircraft Requirements53 3.4.4 Rotorcraft Requirements.54 3.4.5 Electrical FCS Design.54 3.4.6 Computational Methods and Software57 3.5 Subsystem Design Requireme
13、nts 59 3.5.1 Subsystem General Design Requirements.59 3.5.2 Electrical Power Subsystems59 3.5.3 Hydraulic Power Subsystems.60 3.5.4 Pneumatic Power Subsystems.60 3.5.5 Actuation Subsystems 60 3.5.6 Trim Subsystem73 3.5.7 Artificial Feel Subsystem.73 3.5.8 Display and Annunciator Subsystem74 3.5.9 Se
14、nsors.75 3.6 Component Design and Fabrication Requirements76 3.6.1 General Component Requirements76 3.6.2 Mechanical Components 77 3.6.3 Electrical and Electronic Components83 3.6.4 Assembly Design 85 3.6.5 Component Installation .87 3.6.6 Component Fabrication.87 3.6.7 Specific Component Requiremen
15、ts 88 4. QUALITY ASSURANCE PROVISIONS91 4.1 General Requirements91 4.1.1 Methods for Demonstration of Compliance 91 4.2 Analysis Requirements .92 4.2.1 Piloted Simulations93 4.2.2 Reliability and Failure Mode, Effects and Criticality Analysis93 4.2.3 Vulnerability Analysis93 4.2.4 Maintainability An
16、alysis.93 4.2.5 System Safety Analysis.93 4.2.6 Operation in Turbulence Analysis.94 4.2.7 Stability Analysis.94 4.2.8 Nuclear Survivability Analysis.94 4.3 Software Verification.94 4.4 Test Requirement95 4.4.1 General Test Requirements95 4.4.2 Laboratory Tests.96 4.4.3 Aircraft Ground Tests97 4.4.4
17、Aircraft Flight Tests.98 4.5 Qualification (Preproduction) Tests 98 4.5.1 Reliability Development Tests.98 4.5.2 Maintainability Demonstration.98 4.5.3 Human Factors Engineering Verification Tests 98 4.5.4 Production/Acceptance Testing99 4.6 Documentation99 4.6.1 FCS Development Plan 99 4.6.2 FCS Sp
18、ecification100 4.6.3 Design and Test Data Requirements100 4.6.4 Software Documentation.102 Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:54:44 MSTNo reproduction or networking permitted without license from IHS
19、-,-,- SAE AS94900 - 3 - FIGURE 1 ACCELERATION WEIGHTING FUNCTIONS40 FIGURE 2 H/HC FREQUENCY RESPONSE REQUIREMENT45 TABLE 1 FCS QUANTITATIVE FLIGHT SAFETY REQUIREMENTS 17 TABLE 2 GAIN AND PHASE MARGIN REQUIREMENTS26 TABLE 3 TURBULENCE INTENSITY EXCEEDANCE PROBABILITY.28 TABLE 4 ROOT-MEAN-SQUARE GUST
20、INTENSITIES FOR SELECTED CUMULATIVE EXCEEDANCE PROBABILITIES (FEET PER SECOND TRUE AIRSPEED) .29 TABLE 5 FAILURE TRANSIENTS.31 TABLE 6 MINIMUM ACCEPTABLE CONTROL ACCURACY.37 TABLE 7 PROBABILITY OF EXCEEDANCE OF RIDE DISCOMFORT INDICES39 Copyright SAE International Provided by IHS under license with
21、SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:54:44 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AS94900 - 4 - 1. SCOPE This specification establishes general performance, design, test, development and quality assurance requirements for the
22、Flight Control Systems of military piloted aircraft. Flight Control Systems (FCS) include all components used to transmit flight control commands from the pilot or other sources to appropriate force and moment producers. Flight control commands normally result in control of aircraft altitude, airspe
23、ed, flight path, attitude, aerodynamic or geometric configuration, ride quality, and structural modes. Among components included are the pilots controls, dedicated displays and logic switching, system inertial and air data sensors, signal computation, test devices, mechanical transmission devices, a
24、ctuators, power sources, and signal transmission lines dedicated to flight control. Excluded are aerodynamic surfaces, engines and engine control systems, rotorcraft rotors, fire control devices, crew displays and electronics not dedicated to flight control. In the event of conflict between this spe
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