NAVY MIL-R-81367-1966 RAIN REMOVAL SYSTEM AIRCRAFT WINDSHIELD JET AIR BLAST《排雨水系统 飞机挡风玻璃 飞机鼓风机》.pdf

《NAVY MIL-R-81367-1966 RAIN REMOVAL SYSTEM AIRCRAFT WINDSHIELD JET AIR BLAST《排雨水系统 飞机挡风玻璃 飞机鼓风机》.pdf》由会员分享，可在线阅读，更多相关《NAVY MIL-R-81367-1966 RAIN REMOVAL SYSTEM AIRCRAFT WINDSHIELD JET AIR BLAST《排雨水系统 飞机挡风玻璃 飞机鼓风机》.pdf（11页珍藏版）》请在麦多课文档分享上搜索。

1、MIL-R-81367 (WP) 4 April i966 MILITARY SPECIFICATION- - RAIN REMOVAL SYSTEM, AIRCRAFT WINDSHIELD,JET AIR BLAST This specification has been approved by the Bureau of Naval Weapons, Department of the Navy. 1. SCOPE 1.1 This specification covers jet air blast rain removal systems for use on the windshi

2、elds of rnanned aircraft. 2. APPLICABLE DOCUMENTS 2.1 Government documents normally furnished - The following documents, of the issue in effect on date of invitation for bids or reques-t for proposal, form a part of this specification to the extent specified herein. SPECIFICATIONS Military MIL- A- 8

3、 8 06 Acoustical Noise Level in Aircraft, General Specification for MIL-B- 81365 Bleed Air Systems, General Specification for STANDARDS Military MIL- STD- 210 Climatic Extremes for Military Equipment 933574 Dimensions, Basic, Cockpit, Stick- Controlled, Fixed Wing ,4Lrcraft f Provided by IHSNot for

4、ResaleNo reproduction or networking permitted without license from IHS-,-,-1 MIL-R-1367 1b 77777Ob 0204565 T MIL-R-$1367 (WP) STANDARDS Military(c0ntinued) MS33576 Dimensions, Basic, Cockpit, Wheel Controlled, Fixed Wing Aircraft (When requesting applicable documents, refer to both title and number.

5、 Copies of unclassified documents may be obtained from the Commanding Officer, Naval Supply Depot (Code 1051), 5801 Tabor Avenue, Philadelphia, Pennsylvania 19120. Requests for copies of classified documents should be addressed to the Naval Supply Depot, via the cognizant Government inspector.) 3. R

6、EQUIREMENTS -x 3.1 Prototype component inspection - The jet air blast rain removal system furnished under this specification shall be a product which has been inspected and has passed the prototype component inspection specified herein. 3.2 General - The requirements f MIL-Ba1365 shall apply as requ

7、irements of this specification with the exceptions and additions noted herein, When the two specifications conflict this specification shall govern. 3.3 Design and construction - 3.3.1 Controls - The system shall be operated by an on-off control. Any necessary regulation within the system shall be a

8、utomatic, The on-off control shall be suitably protected to prevent inadvertent operation. u- 3.3.2 Overheat caution - An overheat caution system shall be provided to indicate overheat of the windshield, adjacent structure, or accessories. Overheat condition shall be indicated by a caution light. 3.

9、3.3 Acousticalnoise level - Operation of the rain removal system shall not raise the acoustical noise level in any part of the aircraft intended for occupancy by the crew or other personnel above the short duration requirements of MIL-A-8806 during takeoff, or above the normal requirements during cr

10、uise, approach, landing, and taxiing. 3.3.4 Safety - All components of the sys.tem shall be failsafe. 2 -. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,

11、-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-R-BL367 Lb W 9799706 OZ04568 5 I- MIL-R-81367 (WP) 4.6.1 Examination - The system shall be thoroughly examined to determine conformance with -this specification and applicable drawings with resp

12、ect to all the requirements not covered by tests. 4.6.2 Proof pressure - The jet air blast rainremoval system shall be subjected to and shall pass the proof pressure test specified in MIL-B%1365. Endurance - The jet air blast rain removal system shall be 3, 4.6.3 subjected to and shall pass the endu

13、rance test specified in MIL-B-81365, 4.6.4 Flow resonance - The jet air blast rain removal system shall be subjected to and shall pass the flow resonance test specified in MIL-B-81365. 4.6.5 Burst pressure - The jet air blast rain removal system shall be subjected to and shall pass the burst pressur

14、e test specified in MIL-B-81365. 4.6.6 Visibility 4.6.6.1 The jet air blast rain removal system shall be installed in a functional mock-up of the forward fuselage including the windshield panels and adjacent structures. The mock-up shall be instrumented to monitor critical windshield and structural

15、temperatures and jet air blast flow rates. The mock-up shall be operated to ensure that: (a) Simulated flight velocity range is equal to that of the aircraft. (b) Jet air blast patterns cover the required clear area (see Figure 1). (c) Rain droplet size and intensity can be controlled to the values

16、specifid in Table I. TABLE I Rain Defiiiiiions Rain Precipitation Droplet Diam. Milligrams Grains of Colidi tion Intensity mm. of Liquid Liquid Water . mm. per inciles Water per p-per CU. ft. hour per hour meter of air -of air Light Rail1 1.00 O. 04 0.45 138.9 0.06 Heavy Rain 15.00 0.59 1.5 833.3 0.

17、365 Moderate Rain 4.00 . 0.16 1. o 277.8 o. 12 I (Air density as at O“ C and 740 mm Hg pressure) 5 Ca e, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-R-1367 1b MIL-R-81367 (WP) d 2 .rl . l-4 +- !3 cd a, 2 r- Provided by IHSNot for ResaleNo rep

18、roduction or networking permitted without license from IHS-,-,-MIL-R-81367 (I 4.6.6.2 Local visibility factors - Local visibility factors shall be determined from the description in Table II. TABLE II Local Visibility Factors Observed Windshield Physical Conditions Local Intensity Evaporation Runbac

19、k Visibility thru Factor Visibility (See Table I) Runbac k - - - 10 None - 9 Light Immediate - - - 8 Light Partial 1 inch - 8 Moderate Immediate - - 7 Light. a Partial 2 inch 7 Moder at e Partial 1 inch - - - - 7 Heavy Immediate 6 Light Partial Consider able - 6 Moderate Partial 2 inch 6 Heavv Parti

20、al 1 inch - - 4 “ Light Unno tic e able Continuous Good Moderate Partial Considerable - Eeavy Partid 2 inch - Light Unno tic eable Continuous Fair Moderate Unno tic eable Continuous Good Keavg Partial Considerable - c 4 I Light Unno tic eable Continuous Poor 4 I Moderate Unnoticeable Continuous Fair

21、 p= 2 2 Heavy Unno t ic eable Continuous Good Light Unnoticeable Continuous Moderate Unnoticeable Con tinu ous Poor Heavy Unnoticeable Continuous Fair Moderate Unno tic eable Continuous Very Poor Heavy Unnoticeable - Continuous Poor Heavy Unno tic eable Continuous Very Poor Very Poor 4.6.6.3 Require

22、d clear area - The limits of the required clear area on the external surface of the windshield panel(s) shall be determined with respect to the pilots (copilots) eye position defined by MS 33574 or MS 33576. The minimum upper limit of the clear area shall be defined by the external intersection of t

23、he windshield panel(s) and a horizontal plane passing through the pilots (Co-pilots) eye position with the aircraft at maximum expected nose-down atti-de. during I 7 _-II_- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-R-81367 (WP) approach and

24、 landing. The minimum transverse extent of the clear area shall be defined by the external intersection of the windshield panel(s) and two vertical planes passing through and measured from the pilots (co-pi1ots)eye position, one 13 degrees horizontally to the left and one 13 degrees horizontally to

25、the right. The lower limit of the clear area shall be defined by the lower extent of the windshield panel(s) or the upper limit of intervening structure as viewed from the pilots (co-pilots) eye position. 4.6.6.4 Visibility index - The visibility index for the required clear area shall be defined as

26、 the area weighted average of the local visibility factors. It shall be computed as given below and illustrated in Figure 1. Visibility index = ELocal visibility factor x local area) E(Loca1 areas comprising required clear area) structure. (“1 4.6.6.5 Clearance demonstrations - Clearance conforming

27、to the minimum visibility index shall be demonstrated at velocities, mock-up angles of attack, and jet air blast nozzle configurations corresponding to the following conditions. There shall be no overheating or overstressing of the windshield panels or adjacent Power approach at minimum practical la

28、nding gross weight for a 90F day with light, moderate, and heavy rain. The minimum visibility index shall be 6.0. and speed of (V -5 knots) power approack minimum Power approach at maximum landing design gross weight and speed of 1.4(V stall moderate, and heavy rain, The minimum visibility index sha

29、ll be 6.0 ) landing for a 90F day with light, Landing with an idle engine power setting at minimum practical landinggross weight and speed of (V landing for a 90“ F day with light, moderate, and heavy rain. The minimum visibility index shall be 4.4. ) stall Landing with an idle engine power setting

30、at maximum landing design gross weight and speed of 1.2 (V landing for a 90“ F day with light, moderate, and heavy rain. The minimum visibility index shall be 4.4. ) stall Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-R-81367 (WP) (e) Power app

31、roach configuration at optional gross weight, speed, temperature, and rain conditions selected for the most feasible comparison required by the flight tests (see 4.6.6.7). The minimum visibility index shall be 6.0. 4.6.6.6 Temperature demonstrations - Temperature effects of system operation shall be

32、 demonstrated using the mock-up system at velocities, mock-up angles of attack, and jet blast nozzle configurations corresponding to the following conditions. There shall be no overheating or overstressing of the wind- shield panels or adjacent structure and the minimum visibility index shall be 6.0

33、. (a) Takeoff at minimum operational gross weight and speed of 1.2 (Vstall) takeoff for a 90“ F day with light rain for 3 minutes. (b) Power approach at maximum landing design gross weight and speed of 1.4 (Vstall) landing for a 90“ F day until wind- shield temperature stabilization is reached. (c)

34、Ground static conditions and takeoff power for a 103“ I? day without rain for 30 seconds. 4.6.6.7 Flight test - Flight tests shall be conducted on the jet air blast rain removal system under conditions closely duplicating those of 4.6.6.5 (e) to verify the clearance or to provide an approximate corr

35、ection factor. The minimum visibility index shall be 6.0. 4.6.7 Vibration - The jet air blast rain removal system shall be subjected to and shall pass the vibration test specified in MIL-B- 81365. 5. PREPARATION FOR DELIVERY (Not applicable) 6. NOTES 6.1 Intended use - The jet air blast rain removal

36、 system is intended for use to remove rain from the windshields of manned aircraft. 6.2 specie the following: Information for contracting officer - Contracts or orders should Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-R-1367 Lb = 7797706 020

37、L1573 7 MIL-R-81367 (WP) (a) Title, number, and date of this specification (b) Items of data required (see 6.3) (c) Engineering change procedure in accordance with BUWEPSINST 4275.2A, enclosure (1) (d) Rain removal systems subjected to tests other than those listed under quality conformance inspecti

38、on are not to be considered or shipped as part of the contract or order. 6.2.1 Contracts or orders should specify the following provisions for prototype component inspection, 6.2.1.1 Whether prototype component inspection is required, When a contractor is in continuous production of the items from c

39、ontract to contract, consideration should be given to waive the prototype component inspection. If prototype component inspection is required, indicate: (a) where the prototype component inspection is to be conducted (at the contractors plant or Government or commercial laboratory), (b) that the app

40、roval of prototype samples or the waiving of the prototype component inspection shall not relieve the contractor of his obligation to fulfill all other requirements of the specification and contract. 6.3 - Data - Data information shall be in accordance with MIL-B-81365. 6.3.1 Prototype data - When p

41、rototype samples are submitted (see6.2) they should be accompanied by one complete set of manufacturers drawings, the contractors model specification, a parts list, and a complete test report showing the results of the contractors tests. The test report should include the following: (a) Report of al

42、l tests, graphically presented when possible, together with a detailed statement indicating compliance or extent of noncompliance with all requirements of this specification, referring specifically to paragraph numbers. Whenever a requirement is considered to be not applicable, the report should so

43、state. 10 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-(b) Summary of visibility tests. (c) Diagrams of test setups. (d) Reproducible outline and description of tests and test conditions. Where tests specified in this specification are not considered appli- cable, the reasons and the substituted tests should be clearly described. (e) Copies of test log sheets. (f) Photographs wlen available. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-