SAE ARP 4729-1992 DOCUMENT FOR 270 VOLTAGE DIRECT CURRENT (270 V DC) SYSTEM《270 V直流(270 V DC)系统文件》.pdf

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1、SAE ARPu4727 92 W 7743725 05LL2L3 584 W AEROSPACE RECOMMENDED he Engineering Society mA=For Advancing Mobility -Land Sea Air and Spaces INTERNATIONAL 400 Commonwealth Drive, Warrendale, PA 15096-0001 PRACTICE Submitted for recognition as an American National Standard ARP4729 Issued 1992-09-18 DOCUME

2、NT FOR 270 VOLTAGE DIRECT CURRENT (270 V DC) SYSTEM FOREWORD This document was prepared by the panel members of the AE-IC Systems High Voltage Direct Current (HVDC) Panel under the overall direction of the SAE-AE7 Aerospace Electrical Power and Equipment Committee. The document is in accordance with

3、 the SAE Technical Report Style Manual, dated May 1992. 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

4、 use, including any patent infringement arising therefrom, 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. CAE invites your written comments and suggestions. Copyright 1992 Society of Auto

5、motive Engineers, Inc. All rights reserved. Printed in U.S.A. COPYRIGHT SAE International (Society of Automotive Engineers, Inc)Licensed by Information Handling ServicesSAE ARP4729 I 1 . SCOPE . 3 TABLE OF CONTENTS 1.1 Purpose 3 2 . APPLICABLE DOCUMENTS . 3 2.1 SAE Publications . 3 2.2 Military Publ

6、ications . 3 2.3 Other Publications 4 3 . 270 V DC SYSTEM. . 5 3.1 3.2 3.2.1 3.2.2 3.2.3 3.3 3.3.1 3.3.2 3.3.3 3.3.4 3.3.5 3.3.6 3.4 3.4.1 3.4.2 3.4.3 3.4.4 3.5 Generic Description 5 Performance 5 Dutycycle 5 Reliability 7 Electromagnetic Interference and Compatibility 7 Interface Requirements 7 Ele

7、ctrical Power Interface 7 Control Signal Interface . 7 Mechanical Interface . 8 Envelope . 8 Thermal Interface . 8 Operator Interface 8 Design and Construction 9 General 9 Generators and Generator Control Units 9 Protection and Control Devices 10 Power Conditioning and 270 V DC Utilization Equipment

8、 . 10 Environmental Requirements 10 4. QUALITY ASSURANCE REQUIREMENTS 11 4.1 4.1.1 4.2 4.2.1 4.2.2 4.2.3 4.2.4 4.3 General. . 11 Responsibility for Tests . 11 Quality Conformance Inspections 11 Exami nation 11 Demonstration . 11 Test . 12 Analysis . 12 Quality Assurance Measurement Tolerance 12 5 .

9、SHIPPING AND HANDLING . 12 6 . GENERAL NOTES . 12 APPENDIXA 13 COPYRIGHT SAE International (Society of Automotive Engineers, Inc)Licensed by Information Handling ServicesSAE ARP*4729 92 7943725 0511917 5Tb SAE ARP4729 1. SCOPE This SAE Aerospace Recommended Practice (ARP) provides technical design a

10、nd application information related to the generation, distribution, control, and utilization of aircraft 270 V DC electrical power systems and support equipment. compari sons of various electrical systems and components. This document also provides references and definitions to permit 1.1 Purpose: T

11、he purpose of this document is to consolidate industry recommended practices for 270 V DC systems and equipment to enable a common understanding of their specification, design, and use. 2. APPLICABLE DOCUMENTS: Specific 270 V DC requirements will be contained within the governing procurement specifi

12、cation; however, all or part of the following documents may form a part of that specification. A working knowledge of their scope, purpose, and use is recommended. Where applicable, these documents are referenced within specific sections of this document. Selection of specifications and standards fo

13、r necessary commodities and services not specified herein should be selected in accordance with MIL-STD-143. 2.1 SAE Publications: Available from SAE, 400 Commonwealth Drive, Warrendale, PA 15096-0001. AS486 Aircraft Circuit Breaker and Fuse Arrangement ARP926 Faul t/Fail Ure Analysis Procedure ARP9

14、35 Suggested electromagnetic interference (EMI) Control Plan Outline AS1212 Electric Power, Aircraft, Characteristics Utilization of AIR1221 Electromagnetic Compatibility System Design Checklist AIR1277 Cooling of Modern Electronic Equipment AIR1406 Lightning Protection and Static Electrification AS

15、1831 Electrical Power, High Vol tage Direct Current, Aircraft, Characteristics and Utilization of ARP1870 Aerospace Systems Electrical Bonding and Grounding for Electromagnetic Compati bi 1 i ty and Safety 2.2 Military Publications: Available from Standardization Documents Order Desk, Building 4D, 7

16、vv Robbins Avenue, Philadelphia, PA 19111-5094. MI L-STD- 143B MIL-STD-210C MIL-STD-454K Standard General Requirements for Electronic Equipment MI L-STD-461C MIL-STD-462 EM1 Characteristics, Measurements of Mi 1 i tary Standards and Speci fi cat i on , Order of Precedence for the Selection CI imatic

17、 Information to Determine Design and Test Requirements for Military Systems and Equipment Electromagnetic and Susceptibility Requirements for the Control of Electromagnetic interference -3- COPYRIGHT SAE International (Society of Automotive Engineers, Inc)Licensed by Information Handling ServicesSAE

18、 ARP*4729 92 7943725 05LL9L8 432 SAE ARP4729 2.2 (Continued): MI L-STD-704E MI L- STO- 785 MI L-STD-81 OD MI L-STD- 1553 MI L-STD-1629A MIL-STO-2073 MI L-B- 50878 MIL-C-7115E MI L-C-81991 MIL-E-5400T MI L- E-60510 MIL-E-7016F MIL- E-25499C MI L-E-81910A(AS) MI L-G-21480A MIL-I-8500D MIL- 1-27273 MI

19、L-P-81653C (AS) MI L-R-6 106 J MI L-T-23103A( AS) MIL-9-9858 Electric Power, Aircraft, Characteristics Re1 iabil ity Program for Systems and Equipment, Development and Product i on Environmental Test Methods Aircraft Internal Time Division Comnand/Response Mu1 tiplex Data Base Procedures for Perform

20、ing a Failure Modes, Effects and Cri tical i ty Analysis Pac kag i ng Requ i remen t s Bonding, Electrical, and Lightning Protection, Aerospace Sys tems Military Specification Converters, Aircraft, General Speci fi cat i on Converters, Aircraft, dc to dc, Boost, General Specification for Electronic

21、Equipment , Airborne Electromagnetic Compatibil ity Requirements, Systems Mi 1 i tary Speci fi cat i on El ectri c Load and Power Source Capacity, Aircraft , AnalysS s Military Specification Electrical Systems, Aircraft, Design and Installation of, General Specification Military Specification Electr

22、ical Power Generating and Control Equipment, Aircraft, Testing, General Specification Military Specification Generator System 400 Hertz, Alternating Current, Aircraft General Specification Interchangeabil i ty and Rep1 aceabil ity of Component Parts for Aircraft and Missiles Military Specification I

23、nverter, Power, Static, General Specification Military Specification Power Controller, Sol id State, General Speci fi cati on Mi 1 i tary Specification Re1 ays, Electromagnetic (including Established Re1 iability (ER) Types), General Specification Mi 1 i tary Speci fi cati on Thermal Performance Eva

24、1 uat i on, Airborne Electronic Equipment and Systems, General Requirement Quality Program Requirements 2.3 OTHER PUBLICATIONS: DOD-STD-1686 NADC-60-TS-7803 NASA CR-1205 Electrostatic Discharge Control Program for Protection of Electrical and Electronic Parts, Assemblies and Equipment Generator Syst

25、em, 270 Vdc, Oil Cooled, Aircraft, General Specification for Compendium of Human Responses to the Aerospace Environment, Volume 1, Section 5 COPYRIGHT SAE International (Society of Automotive Engineers, Inc)Licensed by Information Handling ServicesSAE ARP*4729 92 7943725 0511919 379 = SAE ARP4729 3.

26、 270 V DC SYSTEM: 3.1 Generic Description: 270 V DC aircraft systems typically consist of a variety of electrical power and control equipment that have been selected and integrated to meet the specific design application requirements. Such requirements include electrical performance, power/control a

27、nd source/load redundancy, component/system reliability, and maintainability. generic presentation of a 270 V DC system is shown in Figure 1. and component arrangement is intended to show typical power flow and interconnections, not a specific recommended configuration. or elements and their charact

28、eristics are discussed in subsequent sections of this document and include the following: A The system The components a. Generators and generator control units (GCU) b. 270 V DC power conditioning c. 270 V DC distribution (load management panel and bus structure) d. Power switching devices (contacto

29、rs, circuit breakers, and power control 1 ers) e. 270 V DC utilization (direct, direct current converters and inverters) f. Power control processor (system/el ement monitoring and bui 1 t-in test capabil i ties) 3.2 Performance: This section should contain all the requirements for establishing the o

30、verall 270 V DC system as well as the specific power generation, conditioning, distribution, control, and utilization equipment designs. based on the electrical power interface in accordance with MIL-STD-704 and the methodology for establishing the electrical load in accordance with This should be M

31、IL-E-7016. 3.2.1 Duty Cycle: A descriptive of the loads and their duration should be specified so that the heat-sensitive 270 V DC equipment/components can be sized to handle the resulting thermal loads. This duty cycle specification is particularly important for electronic power equipment as oppose

32、d to hydromechanical counterparts. specified for a typical and worst case mission in terms of consecutive time intervals for identifiable mission segments such as takeoff, cruise, special maneuvers (if appl icable) , and 1 anding. The time duration of each segment should be specifically indicated. I

33、f the typical mission is likely to be repeated according to a predictable schedule (such as for commercial aircraft), the ground time between mission cycles should be included in the duty cycle speci fi cat ions . In some cases, the worst-case loading occurs on the ground during training or maintena

34、nce exercises during which the amplitude of the steady state and/or dynamic loading can be set artificially high compared to in-flight values. If such conditions are expected, the nature and duration of such ground-based loading should be specified. It is recommended that the duty cycle be -5- COPYR

35、IGHT SAE International (Society of Automotive Engineers, Inc)Licensed by Information Handling ServicesSAE ARP*Y729 92 W 79Y3725 0555920 OSO SA ARP4729 I n u O c, U o) L o c O u a a- o h N U 2. W C W CI I .P ril COPYRIGHT SAE International (Society of Automotive Engineers, Inc)Licensed by Information

36、 Handling ServicesSAE ARPS4727 72 7743725 0533723 T27 SAE ARP4729 3.2.2 Reliability: The mean time between failure (MTBF) for the 270 V DC system when operating within the loading and environmental levels specified should be defined. The analysis using a mathematical model should be performed in acc

37、ordance with MIL-STD-785. The failure mode, effect, and criticality analysis (FMECA) should be in accordance with ARP926 and MIL-STD-1629. Based on the results of the FMECA and/or the MTBF, some systems will require full or partial redundancy in order to meet mission re1 i abi 1 i ty . should be spe

38、cified. 3.2.2.1 Redundancy: Both the phi 1 osophy and degree of redundancy required 3.2.2.2 Fault Tolerance: The degree of fault tolerance and resultant 270 V DC system performance under fault conditions should be def i ned . 3.2.3 Electromagnetic Interference and Compatibility: Unless otherwise spe

39、cified in the procurement specification, the generation and susceptibility to EM1 for all electrical and electronic equipment should be evaluated early in the design phase in accordance with ARP935 with control and testing in accordance with MIL-STD-461 and MIL-STD-462, respectively. Special attenti

40、on should be given to the 270 V DC waveform distortion specified in MIL-STD-704E and the allowable MIL-STD-461 limits. 3.3 Interface Requirements: 3.3.1 Electrical Power Interface: The electrical input power, both direct current and/or alternating current, to the system should be defined. definition

41、 should include the normal range which the system will see, for the majority of the time, the abnormal or transient range of short time duration and if applicable the emergency input power range. maximum permissible power draw limit for any circuit, it should also be specified. similar electrical po

42、wer specification that has been developed for the industry, such as AS1212 or AS1831. This If there is a The input power definition can be specified as MIL-STD-704 or a 3.3.1.1 Regenerated Power: The utilization loads, such as electric actuation, The probable choices are either to put the power will

43、 represent significant aiding loads during portions of their operation. This regenerated power should be recognized and its method of disposal specified. back into the aircraft electrical system for other load demands or dissipate it across a load resistor. 3.3.2 Control Signal Interface: The contro

44、l signal interface should be defined as all signals, mechanical, fluidic, electrical or optical but excluding input electrical power, that are either input to or output from the 270 V DC system. The definition of this interface shall include but not be limited to: a. b. Data or control content of ea

45、ch interface c. Ranges, scales, resolutions, frequencies d. Vol tages, impedances, currents, bit rate e. Applicable specifications, such as MIL-STD-1553 and DOD-STD-1686 Number and types of interfaces -7- COPYRIGHT SAE International (Society of Automotive Engineers, Inc)Licensed by Information Handl

46、ing Services3.3.3 Mechanical Interface: The mounting configuration for the 270 V DC system should be specified. This should include airframe attachment points and desired location of electrical connections. If there is a particular location for mounting a specific 270 V DC equipment, this should als

47、o be shown along with access distances. The information for this paragraph is best provided with a written requirement paragraph referring to a figure elsewhere in the specification or to a specification drawing, 3.3.3.1 Bonding and Grounding: Bonding of electrical and electronic components should b

48、e in accordance with MIL-6-5087, Each electrical or electronic assembly other than sensors should have a ground return isolated from the power return lead or connector pin. 3.3.4 3.3.5 3.3.6 Envelope: The maximum envelope available for the 270 V DC equipment should be shown as a figure in the specif

49、ication or on a separate specification drawing. If the center of gravity of a particular 270 V DC equipment is required, it can be shown as a to be determined requirement of this paragraph The envelope may be specified as “The equipment shall be as small as practical using good design practices and shall be within the envelope(s) shown in Figure 1.“ NOTE: It may be practical to provide “mechanical interface“ and “envelope“ Thermal Interface: The 270 V DC system contains electrical and electronic components that generate heat and the performance, reliability, and life of thes