AIR FORCE AFGS-87219 B-2012 ELECTRICAL POWER SYSTEMS AIRCRAFT.pdf

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1、 NOT MEASUREMENT SENSITIVE AFGS-87219B 23 October 2012 SUPERSEDING AFGS-87219A 30 March 1993 DEPARTMENT OF DEFENSE AIR FORCE GUIDE SPECIFICATION ELECTRICAL POWER SYSTEMS, AIRCRAFT This guide specification is for guidance only. Do not cite this document as a requirement. Comments, suggestions, or que

2、stions on this document should be addressed to the Air Force Life Cycle Management Center, Engineering Standards Office, AFLCMC/ENRS, 2145 Monahan Way, Wright-Patterson AFB OH 45433-7017; DSN 674-5476, commercial (937) 904-5476 or by email to Engineering.Standardswpafb.af.mil. Since contact informat

3、ion can change, you may want to verify the currency of this address information using the ASSIST Online database at https:/assist.dla.mil/. AMSC N/A FSC 61GP DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. Provided by IHSNot for ResaleNo reproduction or networking p

4、ermitted without license from IHS-,-,-AFGS-87219B CONTENTS PARAGRAPH PAGE 2 1. SCOPE 7 1.1 Scope. 7 1.2 Application. 7 1.3 Use. . 7 1.3.1 Structure. 7 1.3.2 Instructional handbook. 7 1.3.3 Navigation of document. 7 1.4 Deviation. 8 2. APPLICABLE DOCUMENTS8 2.1 General. . 8 2.2 Government documents.

5、8 2.2.1 Specifications, standards, and handbooks. 8 2.3 Non-Government publications. . 9 2.4 Order of precedence. 9 3. REQUIREMENTS .9 3.1 System description. 9 3.2 Performance requirements. 10 3.2.1 Electric power characteristics. 10 3.2.2 Capacity. 10 3.2.3 Uninterruptible power. . 10 3.2.4 Emerge

6、ncy power. 10 3.2.5 External ground power. 10 3.2.6 Auxiliary power. 11 3.2.7 Power distribution. . 11 3.2.8 Control and protection. 12 3.2.9 Major components 13 3.2.10 Environmental conditions. 14 3.3 Electromagnetic interference. 15 3.4 Integrity. 15 Provided by IHSNot for ResaleNo reproduction or

7、 networking permitted without license from IHS-,-,-AFGS-87219B CONTENTS PARAGRAPH PAGE 3 3.5 Maintainability. 15 3.6 System safety. 15 3.7 Interface requirements. 15 3.8 Supportability. . 16 3.8.1 Integrated diagnostics and testability. . 16 3.8.2 Tools. . 16 4. VERIFICATION . 16 4.1 General. . 16 4

8、.2 Performance requirements. 16 4.2.1 Electrical power characteristics. . 17 4.2.2 Capacity. 17 4.2.3 Uninterruptible power. . 17 4.2.4 Emergency power. 17 4.2.5 External ground power. 17 4.2.6 Auxiliary power. 18 4.2.7 Power distribution. . 18 4.2.8 Control and protection. 18 4.2.9 Major components

9、 18 4.2.10 Environmental conditions. 18 4.3 Electromagnetic interference. 18 4.4 Integrity. 18 4.5 Maintainability. 19 4.6 System safety. 19 4.7 Interface requirements. 19 4.8 Supportability. . 19 4.8.1 Integrated diagnostics and testability verification. 19 4.8.2 Packaging, handling, storage, and t

10、ransportation. . 19 4.8.3 Tools verification. 19 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AFGS-87219B CONTENTS PARAGRAPH PAGE 4 5. PACKAGING 19 5.1 Packaging. 19 6. NOTES . 20 6.1 Intended use. . 20 6.2 Acquisition requirements. 20 6.3 Definit

11、ions. 20 6.3.1 Abnormal operation. . 20 6.3.2 Electrical power system (EPS). 20 6.3.3 Emergency operation. . 20 6.3.4 External power source. . 20 6.3.5 Normal operation 20 6.3.6 Uninterruptible power. . 21 6.3.7 Utilization equipment. 21 6.4 Subject term (key word) listing. 21 6.5 International stan

12、dardization agreement implementation. . 21 6.6 Responsible engineering office. 21 6.7 Changes from previous issue. . 21 APPENDIX A A.1 SCOPE . 22 A.1.1 Scope. 22 A.1.2 Format. 22 A.1.3 Responsible engineering office. 22 A.2 APPLICABLE DOCUMENTS. 23 A.2.1 Government documents. 23 A.2.1.1 Other Govern

13、ment documents, drawings, and publications. 25 A.2.2 NonGovernment publications. 25 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AFGS-87219B CONTENTS PARAGRAPH PAGE 5 A.3 REQUIREMENTS AND VERIFICATIONS 26 A.3.1 System description. 26 A.4.1 General

14、. . 26 A.3.2 Performance requirements. 26 A.4.2 Performance requirements. 27 A.3.2.1 Electric power characteristics. 27 A.4.2.1 Electrical power characteristics. . 28 A.3.2.2 Capacity. 29 A.4.2.2 Capacity. 30 A.3.2.3 Uninterruptible power. . 31 A.4.2.3 Uninterruptible power. . 32 A.3.2.4 Emergency p

15、ower. 33 A.4.2.4 Emergency power. 34 A.3.2.5 External ground power. 35 A.4.2.5 External ground power. 37 A.3.2.6 Auxiliary power. 38 A.4.2.6 Auxiliary power. 39 A.3.2.7 Power distribution. . 39 A.4.2.7 Power distribution. . 40 A.3.2.8 Control and protection. 41 A.4.2.8 Control and protection. 43 A.3

16、.2.9 Major components 44 A.4.2.9 Major components 45 A.3.2.10 Environmental conditions. 55 A.4.2.10 Environmental conditions. 57 A.3.3 Electromagnetic interference (EMI). . 58 A.4.3 Electromagnetic interference. 58 A.3.4 Integrity. 59 A.4.4 Integrity. 59 A.3.5 Maintainability. 60 A.4.5 Maintainabili

17、ty. 60 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AFGS-87219B CONTENTS PARAGRAPH PAGE 6 A.3.6 System safety. 61 A.4.6 System safety. 61 A.3.7 Interface requirements. 61 A.4.7 Interface requirements. 62 A.3.8 Supportability. . 62 A.3.8.1 Integrat

18、ed diagnostics and testability. . 62 A.4.8 Supportability. . 63 A.4.8.1 Integrated diagnostics and testability verification. 63 A.3.8.2 Packaging, handling, storage, and transportation (PHST). . 67 A.4.8.2 Packaging, handling, storage, and transportation. . 68 A.3.8.3 Tools. . 68 A.4.8.3 Tools verif

19、ication. 69 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AFGS-87219B 7 AIR FORCE GUIDE SPECIFICATION ELECTRICAL POWER SYSTEMS, AIRCRAFT This specification is approved for use by the Department of the Air Force and is available for use by all Depar

20、tments and Agencies of the Department of Defense within the distribution limitations noted at the bottom of the cover page. 1. SCOPE 1.1 Scope. This specification establishes the performance requirements and verifications for electric power subsystems (EPS) for aerospace vehicles, including aircraft

21、, helicopters, and missiles. 1.2 Application. This specification is applicable to aerospace vehicles and is mandatory for use by the Department of the Air Force. Utilization equipments must be compatible with the power quality requirements specified herein. 1.3 Use. This specification cannot be used

22、 for contractual purposes without supplemental information relating to the performance requirements of electric power subsystems for aircraft. 1.3.1 Structure. The need for supplemental information is indicated by blanks within the specification. 1.3.2 Instructional handbook. The instructional handb

23、ook, which is contained in the appendix herein, provides the rationale for requirements, guidance for the tailoring of requirements, and a lessons learned repository. 1.3.3 Navigation of document. Microsoft Wordand Adobe Acrobatversions of this document contain active hyperlinks which appear in blue

24、 font. These hyperlinks provide the user a means to navigate within the document and to reference Websites. The simplest way to return to the most-recently-viewed page within a Microsoft Worddocument is to utilize the “back arrow” and “forward arrow” after a hyperlink has been selected. These icons

25、may be included in a users “Quick Access Toolbar” in this manner: select the Microsoft Office Button ; select “Word Options”; and then select “Customize”. In the “Choose commands from” list, select “All Commands” and then select “Back”; click “Add”; then select “Forward” and click “Add”. This same m

26、ethod can be employed in the toolbar area of Adobe Acrobatversions of this document: select “View” and “Toolbars” on the menu bar, and within the drop-down box select “Page Navigation Toolbar” and the “Previous View” Button and the “Next View” Button and click “OK”. Provided by IHSNot for ResaleNo r

27、eproduction or networking permitted without license from IHS-,-,-AFGS-87219B 8 1.4 Deviation. Any projected design for a given application that results in improved system performance, reduced life cost, or reduced development cost through deviation from this specification, or where the requirements

28、of this specification result in a compromise of operational capability, the details of the change should be brought to the attention of the procuring activity for consideration. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are specified in sections 3, 4, or 5 of this spe

29、cification. This section does not include documents cited in other sections of this specification or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they must meet all specified require

30、ments of documents cited in sections 3, 4, or 5 of this specification whether or not they are listed. 2.2 Government documents. 2.2.1 Specifications, standards, and handbooks. The following specifications, standards, and handbooks form a part of this document to the extent specified herein. Unless o

31、therwise specified, the issues of these documents are those cited in the solicitation or contract. INTERNATIONAL STANDARDIZATION AGREEMENTS ASIC AIR STD 25/18 Connectors for 28 Volt DC Servicing Power NATO STANAG 3109 Symbol Marking of Aircraft Servicing and Safety/Hazard Points NATO STANAG 7073 Con

32、nectors for Aircraft Electrical Servicing Power DEPARTMENT OF DEFENSE SPECIFICATIONS MS17793 Schematic Wiring Diagram (External AC Power Connector, Aircraft) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AFGS-87219B 9 DEPARTMENT OF DEFENSE STANDARD

33、S MIL-STD-704 Aircraft Electric Power Characteristics MIL-STD-1796 Avionics Integrity Program (AVIP) MIL-STD-1798 Mechanical Equipment and Subsystems Integrity Program MIL-STD-2161 Paint Schemes and Exterior Markings for U.S. Navy and Marine Corps Aircraft (Copies of these documents are available on

34、line at https:/assist.dla.mil/quicksearch/ or from the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 19111-5094.) 2.3 Non-Government publications. The following documents form a part of this document to the extent specified herein. Unless otherwise specified,

35、 the issues of these documents are those cited in the solicitation or contract. SAE INTERNATIONAL SAE AS35061 Connector, Receptacle External Electric Power, Aircraft, 28 Volt DC Operating Power SAE AS90362 Connector, Receptacle, External Electric Power, Aircraft, 115/200 Volt, 400 Hertz (This standa

36、rd is available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001 or online at http:/www.sae.org.) 2.4 Order of precedence. Unless otherwise noted herein or in the contract, in the event of a conflict between the text of this document and the references cited herein, the text

37、 of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3. REQUIREMENTS 3.1 System description. The electrical power system (EPS) shall provide for the onboard generation, conversion, storage, di

38、stribution, diagnostics, and control of the electric power required for all phases of vehicle operation, including ground maintenance. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AFGS-87219B 10 3.2 Performance requirements. 3.2.1 Electric power c

39、haracteristics. The electrical power system shall provide electric power to the terminals of the power utilization equipment in accordance with the following characteristics: _. 3.2.2 Capacity. The EPS shall be capable of supplying all electric power requirements for all modes of vehicle operation p

40、lus additional capacity to provide for growth loads as follows: _. The buses, conductors, and circuit breakers should be capable of handling the load growth provisions. 3.2.3 Uninterruptible power. Flybywire flight controls and other flight critical subsystems and components which cannot tolerate po

41、wer interruption, shall be provided with power from fulltime redundant power sources. During flight each redundant power source shall be fully active and shall be either powering the critical loads or capable of assuming such loads without power interruption in the event of failure of other sources.

42、 a. Uninterruptible power (is) (is not) required. b. A minimum of _ failures of sources of uninterruptible power shall be accommodated without interruption or degradation of power to flightcritical loads. This requirement shall be met without crew action or automatic reconfiguration of the power sys

43、tem. 3.2.4 Emergency power. An independent emergency power source shall be provided to supply all essential loads in the event of failure of the primary power source(s). a. The power rating and total available energy shall be sufficient to supply all loads identified as essential for control of the

44、vehicle and personnel safety. b. The transfer of essential loads to and from the emergency power source shall be accomplished without transients of a magnitude hazardous to the vehicle or personnel. c. A convenient means of verifying the operational readiness of the emergency power source prior to f

45、light shall be provided. d. Other emergency power requirements are as follows: _. 3.2.5 External ground power. The EPS shall accept power from an external source for ground operations as required. The EPS shall be compatible with MIL-STD-704 quality power supplied by the following external electrica

46、l power sources: _. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AFGS-87219B 11 a. The EPS shall be capable of handling the maximum external power required for ground operations while maintaining power characteristics in accordance with 3.2.1. b.

47、The EPS shall provide protection to prevent unsuitable external power from being applied to the aircraft. c. The EPS shall provide for the power transfer from the external power source to the on-board power source(s) and in the reverse direction in a manner consistent with the transient and power in

48、terruption requirements of 3.2.1. Power transfer is required as follows: _. d. Receptacles for 28volt DC external power shall be in accordance with either SAE-AS35061or ASIC AIR STD 25/18, and shall be connected in accordance with NATO STANAG 7073. Receptacles for 115 volt, 400 Hz external power shall be in accordance with SAE-AS90362, and shall be connected in accordance with either MS17793 or STANAG 7073. Receptacles shall be isolated from aircraft power circuits when the mating plug is disengaged to ensure that dan