NAVY MIL-D-7890 A-1968 DESIGN AND INSTALLATION OF ANTI-G SUIT PRESSURE SYSTEMS IN JET PROPELLED AIRCRAFT《喷气式飞机中反G压力系统的设计和安装》.pdf

《NAVY MIL-D-7890 A-1968 DESIGN AND INSTALLATION OF ANTI-G SUIT PRESSURE SYSTEMS IN JET PROPELLED AIRCRAFT《喷气式飞机中反G压力系统的设计和安装》.pdf》由会员分享，可在线阅读，更多相关《NAVY MIL-D-7890 A-1968 DESIGN AND INSTALLATION OF ANTI-G SUIT PRESSURE SYSTEMS IN JET PROPELLED AIRCRAFT《喷气式飞机中反G压力系统的设计和安装》.pdf（6页珍藏版）》请在麦多课文档分享上搜索。

1、MIL-D-7SOA Lb m 7777906 0286307 b m _-A 3- /sJ $if- MTILTARY SPECIFICATION DESIGN AND INSTALLATION OF ANTI-G SUIT PRESSURF: SYSTEMS IN JET PROPEW AIRCRAFT This specification has been approved by the Department of the Air Force and by the Naval Air Systems Command, 1. SCOPE 1.1 This specification cov

2、ers the design and installation of anti-G suit pressure systems in jet-propelled aircraft. 2. APPLICABLE DOCUMENTS 2.1 The followihg documents, of the issue in effect on date of invitation for bids or request for proposal, form a part of this specification to the ex- tent specified herein: SPECIFICA

3、TIONS Federal BB-N-411 WW-T-700 Military MIL-L- 5 67 MIL-H-26385 STANDARDS Military MIL-STD-101 MILSTD-Uc3 E22064 m24350 E33658 AN6532 AND10059 Nitrogen, Technical Tube, Aluminum Alloy, Drawn, Seamless; General Specification for Leak Detection Compound, Oxygen Systems Hose, Gxygen and Pressurization

4、, Ozone Resistant Color Code for Pipelines and for Compressed Gas Specifications and Standards, Order of Precedence Clamp, Oxygen Hose Valve, Automatic Regulating Pressure, Anti-G Fitting End, Hose Connection, Standard Dimensions for Connector, Assembly, Hose, Quick Acting, Female, Anti4 Suit Use Fi

5、ttings - Styles of Pipe Threaded, Flared - Tube and Hose Cylinders for the Selection of - THIS DOCUMENT CONTAINS 6 PAGES, I -* Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-7SOA Lb 7979706 0186308 NIL-D-78WA ( AS) (Copies of specifications, s

6、tandards, drawings, and publications required by suppliers in connection with specific procurement functions should be ob- tained from the procuring-activity or as directed by the contracting officer.) 3, REQUIREMENTS 3.1 Materials. - 3.1.1 Selection of materials.- Specifications and standards for m

7、aterials, parts, and processes not specified herein shall be selected in accordance with MIL-STD-lft3. 3.1.2 Metal tubinK.- Metal tubing shall be 5/8 inch outside diameter and shall conform to WW-T-700. 3.1.3 Fittings.- Fittings shall be in accordance with AND10059. 3.1.4 Hose.- Unless otherwise spe

8、cified herein, all hose. shall be 5/8 A clamp in accordance with inch inside diameter conforming to MIL-H-26385. 1522064 shall be used to secure each end of the hose to the associated fitting. 3.2 Design.- The anti-G suit pressure system shall be designated to provide pressurization for an anti-G su

9、it, using the aircraft engine compressor as a source of regulated air pressure. hose, valves, connections, and any other items necessary for the anti-G suit pres- sure system. ?he installation shall comprise tubing, fittings, t 3.3 Installation.- 3.3.1 System P1umbinq.- Metal tubing shall be used in

10、 the system plumbing from the air source to the regulating valve except where flexibility is required for installation or removal of equipment. Where flexibility is required, a hose of the minimum length necessary shall be used. Tubing shall not be installed in an area of the aircraft which will bes

11、ubjected to a temperature of 350“ F or greater. Use of hose is limited to areas of the aircraft which do not exceed i600 F: 3.3.2 Remlating valve.- An anti-G valve conforming to MS2.4350 shall be installed for each crew member of the aircraft. seat aircraft, the anti-G valve shall be located in the

12、aft portion of the left console, adjacent to the seat, within reach of the crew member. side seating, the anti-G valve for the left seat shall be located as specified for a single-place aircraft. the right seat shall be located in the aft portion of the center console, ad- jacent to the seat, within

13、 reach of the crew member. so that the pressure regulating unit is vertical and is perpendicular to the horizontal plane of flight of the aircraft. In single-place and tandem- For side-by- For side-by-side seating, the anti-G valve for The valve shall be mounted 2 Provided by IHSNot for ResaleNo rep

14、roduction or networking permitted without license from IHS-,-,-MIL-D-7SOA Lb W 7777706 OLb307 T 3.3.3 E.iection seat plumbing.- Metal tubing shall be used in the plumbing from the regulating valve to the ejection seat or seat kit disconnect, except where flexibility is required for installation or r

15、emoval of equipment or for seat adjustment. Where flexibility is required, a hose of the minimum length necessary .shall be used. 3.3.3.1 Disconnect.- A disconnect shall be provided either on the left rear portion of the ejection seat or in the left rear portion of the seat kit. The disconnect shall

16、 permit separation of the seat from the aircraft portion of the anti-G suit pressure system automatically upon ejection from the aircraft. The inlet and the outlet fittings of the disconnect shall conform to MS33658-10. 3.3.3.2 Personnel services,- Personnel services shall be provided, using a hose

17、from the top of the disconnect to a connector conforming to AN6532. hose length shall permit the users movement during his normal dubies at his station and shall not provide excessive length with resultant bulkiness. The 3.3.4 Capsule plumbing.- A hose shall be provided from a terminal point at the

18、left rear of the seat to a connector conforming to AN6532. length shall permit the users movement during his normal duties at his station and .shall not provide excessive length with resultant bulkiness. Metal tubing shall,be used in the plumbing from the regulating valve to the terminal point, exce

19、pt where flexibility is required for installation or removal of equipent. Where flexibility is required, a hose of the minimum length necessary shall be used. The hose 3 .A 3.4.1 System functional performance,- When tested as specified in 4.5.2,. the anti-G suit pressure system shall provide, to the

20、 regulating valve, an air flow of at least 500 liters per minute at a temperature not greater than 400“ F and at a pressure of 125 +5 pounds per square inch gage. Contamination of the system shail not exceed 1-ounce increase in filter weight. Perf ormance - 3.4.2 Leakage.- When tested as specified i

21、n 4.5.3, the anti-G suit pressure 3.5 Identification mark%.- The plumbing of the-anti-G suit pressure system shall not leak. system shall be marked for identification in accordance with MIL-STD-101. 3.6 Workmanship.- The anti-G suit pressure system shall be uniform in quality and shall be free from

22、irregularities, defects, or foreign matter which could adversely affect safety, performance, reliability, or durability. 4. QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for inspection.- Unless otherwise specified in the con- Except as otherwise specified, the tract or pwchase order, the supplier

23、is responsible for the performance of all inspection requirements as specified herein. .- 3 - _- -. L I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-789OA (ASG) supplier may utilize his own facilities or any commercial laboratory acceptable

24、to the Government. inspections set forth in the specification where such inspections are deemed necessary to assure supplies and services conform to prescribed requirements. The Government reserves the right to perform any of the 4.2 Classification of inspection.- The examination and testing of the

25、anti-G suit pressure system shall be classified as quality conformance inspection. 4.3 Quality conformance inspection,- The quality conformance inspection shall consist of all the ednations and tests in this specification and shall be conducted on each anti-G suit pressure system to determine its co

26、nformance to the reqGirements specified herein, 4.4 Test conditions,- 4.4.1 Temperature and pressure ,- Unless otherwise specified, tests shall be conducted at local ambient temperatwe and barometric pressure. ature and the barometric pressure shall be recorded at the time of inspection. This inform

27、atlon shall be available for computation of test data, where required, to normal temperature and pressure conditions, pressure conitions are 29,92 inches of mercury and 70 F, shall be calibrated or adjusted accarding to their required usage in conducting individual tests, The temper- The normal temp

28、erature and Test instruments 4.4.2 Leak test comwund.- The leak detection compound employed in testing Care shall be ex- the anti-G suit pressure system shall conform to EL-L-25567, ercised to remove all traces of leak testing material from the plumbing after all leakage tests. 4.4.3 (;as.- The pres

29、surized gas used in testing the anti-G suit pressure system shall Ge either water-pumped nitrogen conforning to type I, class 1, grade B of BB-M-411 or compressed air equivalent in dryness to the nitrogen specified herein. 4.5 InsDection methods.- 4.5.1 Visual. examination.- The anti-G suit pressure

30、 system shall be examined to determine conformance to this specification and applicable drawings With respect to all the requirements not covered by tests. 4.5.2 System functional test,- The plumbing of the anti-G suit pressure system shall be disconnected from the inlet of the regulating valve; app

31、ropriate flow, pressure, and temperature measuring equipment shall be connected to the system plumbing. The aircraft engine shall then be operated at rated pwer; measurements of flow, pressure, and temperature shall be made. of this test, a suitable molecular sieve filter shall be attached to the sy

32、stem plumbing so that the full flow passes through the filter for at least 30 minutes. Difference in filter weight, before and after flow, shall be determined. After completion 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MILD-j8qOA( ASG) 4.5.3

33、Leakaae.- The plumbing of the anti-G suit pressure system shall be disconnected at the aircraft engine compressor, and a gaseous pressure of 300 pounds per square inch gage shall be applied to the anti-G suit pressure system. checked for leakage, using leak detection compound. 5. PIBPARATION FOR DEL

34、IVERY Under these conditions, all fittings and hose connections shall be 1 Not applicable. 6. NOTES 6.1 Intended use,- The installation requirements specified herein are intended for use in designing and installing anti4 suit pressure systems in jet-propelled fighter and trainer aircraft, 6.2 Orderi

35、m data.- Frocurement documents should specify: (a) (b) Data required (see 6.3). Title, number, and date of this specification. 6.3 I&.- For the information of contractors and contracting officers, any of the data specified in (a) 6.3.1 of this specification, (b) applicable documents listed in sectio

36、n 2 of this specification, or (e) referenced lower- tier documents need not be prepared for the Government and shall not be furnished to the Government unless specified in the contract or order. furnished to the Goverment will be listed on DD Form U23 (Contractor Data Requirements List) or NavWeps F

37、orm 4200/15 (Drawings, Lists, and Specifications - Required) which will be attached to and made a part of the contract or order. The data to be 6.3.1 Drawings.- (a) Drawings should include the following and shall be in accordance with MIL-CTD-100: At least 60 days prior to the preparation of the dra

38、wings covering the installation of the anti4 suit pressure system, a schematic diagram of the anti-G suit pressure system shall be submitted to the procuring activity. shall include the description of the relative location of the regulating valves. Al drawings covering the installation of the anti4

39、suit pressure system shall be submitted to the procuring activity for approval. anti4 suit pressure system in the aircraft and the position of the regulating valves in relation to the crew member9 seats. The schematic diagram (b) The drawings shall show the position of the 6.4 International standard

40、ization agreement.- Certain provisions of this specification which pertain to anti-G protection performance are the subject of international standardization agreement STANAG No. 3200. 5 When amendment, revision, Provided by IHSNot for ResaleNo reproduction or networking permitted without license fro

41、m IHS-,-,-. . . MIL-D-7870A 16 = 7777906 OLA6312 T W MIL-D-789OA( ASG) or cancellation of this specification is proposed, the departmental custodians will inform their respective Departmental Standardization Offices so that appropriate action may be taken respecting the international agreement concerned, Custodian: Air Force - 11 Reviewer activities : Navy - AS Air Force - 11, 7i I International interest (see 6.4) Preparing activity: Air Force - U. Project No, 1660-FOo4 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-