NAVY MIL-F-85596-1983 FIN RETARDER AIR INFLATABLE BSU-85 B《BSU-85 B空气充气缓速器翼》.pdf

1、 MIL-F-5596 13 7999906 036537b O MIL-F-85596(AS) 9 May i983 MILITARY SPECIFICATION FIN, RETARDER, AIR INFLATABLE This specification is approved for use by the Naval Air Systems Command, Department of the Navy and is available for use by all Departments and Agencies of the Department of Defense. 1. S

2、COPE BSU-8 5 /B - 1.1 This specification establishes the performance, design, development, and test requirements for a low-drag stabilizer and high-drag retarder (BSU-85/B) for attachment to the MK 83 bomb. 2. APPLICABLE DOCUMENTS 2.1 Government documents. 2.1 .I Specifications, standards and handbo

3、oks. Unless otherwise specified the following specifications, standards and handbooks of the issue listed in that issue of the Department of the Defense Index of Specifications and Standards (DODISS) specified in the solicitation form a part of this specification to the extent specified herein. SPE

4、CI FI CATIONS Military MIL-1-8500 Interchangeability and Replaceability of Component Parts for Aircraft and Missiles MIL-A-8591 Airborne Stores and Associated Suspension Equipment, General Design Criteria for MIL-W-8611 MIL-P -9024 MIL-H-46855 Welding, Metal, Arc and Gas, Steel and Corrosion and Hea

5、t Resistent Alloys, Process for Packaging, Handling and Transportability in System/Equipment Acquisition Human Engineering Requirements for Military Systems, Equipment and Facilities Beneficial Comments (recommendations, additions, deletions) and any pertinent data which may be used in improving thi

6、s document should be addressed to: Commanding Officer, Naval Air Engineering Center, Engineering Specifications and Standards Department (ESSD) Code 93, Lakehurst , NJ 08733 by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document

7、 or by letter. DOCUPwIENT GQPdTAKYS a 0 PAGESE FSC 1325 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2.1.1 Specifications, Standards, and Handbooks - continued STANDARDS Federal FED-STD-102 Military MIL-STD- 12 9 MIL-STD- 130 MIL-STD-210 MIL-STD-7

8、94 MIL-STD-8 10 MIL-STD-882 MIL-STD-889 MIL-STD-965 MIL-STD-1289 MIL -STD-1472 MIL-STD-1523 MIL-STD-1763 MIL-STD-45662 HANDBOOKS Military MIL-HDBK-5 MIL-HDBK-17 MIL -HDBK-23 Preservation, Packaging Levels and Packing Marking for Shipment and Storage Identification Marking of US Military Property Cli

9、matic Extremes for Military Equipment Parts and Equipment, Procedures for Packaging of Environmental Test Methods System Safety Program Requirements Dissimilar Metals Parts Control Program Ground Fit and Compatibility Tests of Airborne Stores, Procedure for Human Engineering Design Criteria for Mili

10、tary Systems, Equipment Facilities Age Controls of Age-Sensitive Elastomeric Material Aircraft/Stores Certification Procedures Calibration System Requirements Metallic Materials and Elements for Aerospace Vehicle Structures Plastics for Aerospace Vehicles Notice ti, Ill Part 1 Reinforced Plastics St

11、ructural Sandwich Composites 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-a -. -7. O a MIL-F-85596 13 7799906 0365378 4 = _ MIL-F-85596 (AS) 2.1.2 Other Government documents, drawings and publications. The following drawings form a part of this

12、specification to the extent specified herein. DRAWINGS Naval Air Systems Command (Code Indent 30003) 2841464, 982537 2841464, 4902089 Bomb, General Purpose, 1000 Pound, MK 83, Mod 4, Loaded Bomb, General Purpose, 1000 Pound, MK 83, Mod 5, Thermally-Coated, Loaded (Copies of specifications, standards

13、, handbooks, drawings, and publications, required by manufacturers in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the Contracting Officer. ) 2.1.3 Order of precedence. In the event of a conflict between the text of this specificat

14、ion and the references cited herein, the text of this specification shall take precedence. 3 . REQUIREMENTS 3.1 Item description. The BSU-85/B stabilizer/retarder, hereinafter referred to as %he item“, shall be an attachment to the MK 83 GP Bomb. The item shall consist of a low-drag stabilizer assem

15、bly, a deployable retarder, and a lanyard operated deployment system. The combination of the item with either configuration of the MK 83 bomb listed in 3.1.2.1 shall make up the system, 3.1.1 Item diagrams. The air carriage release envelope diagram is shown in FIGURE 1. 3.1.2 Interface description.

16、3.1.2.1 The item shall be capable of attaching to the MK 83 bomb body in accordance with Drawing 982537 and Drawing 4902089 by interface with the attaching ring. The item shall incorporate an indexing provision for the purpose of orienting the fins at 45 degrees relative to the bombs suspension lugs

17、. Item to MK 83 bomb. 3.1.2.2 The item, when attached to the MK 83 bomb, shall be capable of being loaded and carried on the Multiple Ejector Racks (MERS), Item to launch aircraft. Improved Multiple Ejector Racks (IMER) , Triple Ejection Racks (TERs) , Improved Triple Ejector Racks (ITER) Vertical E

18、jector Rack (VER) and 1000 pound compatible parent racks on the A-4, A-6, A-7, AV-8, F-4, P-3, S-3, and F/A 18 aircraft. The bomb rack compatibility requirements shall be as specified in TABLE I. Procedures for ground fit and compatibility tests shall be in accordance with MIL-STD-1289. Deployment o

19、f the retarder shall be controlled by a lanyard. The lanyard shall attach by means of a frangible link to an arming solenoid on the bomb rack. The 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-F-5576 13 9977906 0365379 b MIL-F-85596 (AS) TABL

20、E I. MK 83/BSU-85/B air bomb rack/store compatibility requirements. LIRCRAFT I SERVICE A-4 1 i 1) (MI I A-6 A-7 AV-8 A/C AV-8B F-4 F/A-18 p -3 s-3 BOMB RACKS AERO-TA, AERO-20A, MER 7, TER-7, IMER, ITER AERO-TA, AERO-7B, MER-7, TER-7 IMER, ITER BRU-10, MER-7 TER-7, IMER, ITER ERU-119 BRU-36, TER-7, I

21、TER MER-7, TER-7, IMER, ITER BRU-32, TER-7, BRU-33 (VER), ITER BRU-15 External Carriage Only BRU-11, TER-“ ITER External Carriage Onl: (N) = Navy (M) = Marines frangible link shall have a solenoid attachment loop of .O78 plus or minus .O02 inch diameter material, with a radius of .375 minus .O10 inc

22、h. When the system is released with the arming solenoid unenergized, the retarder shall not deploy, and the system shall separate from the aircraft in the low drag mode. When released with the arming solenoid energized, the system shall separate from the aircraft in the high drag mode. No part of th

23、e lanyard other than the attachment link shall remain with the aircraft after release. The interface lanyard pull force shall be between 25 and 150 pounds and operate with existing bomb rack solenoid. No debris shall be released by the item during separation of the system from the aircraft in either

24、 the low or high drag configuration. 3.1.2.3 Accessory physical interface. The FMU-139, and MK 376 bomb fuzes shall require the use of external arming wires which shall be routed along the bomb and shall pass through the item structure. The item shall have both an entrance and an exit hole for the a

25、rming wire. The centerline of these holes shall be located not greater than one inch off a vertical plane through the lug line, and shall be 2.00 plus or minus .25 inches from the bomb/item interface. The holes shall be not less than 0.35 inches in diameter and shall have guides to prevent sharp ben

26、ding of the arming wire. Nose mechanical fuzing (M904), when used with retarded deliveries, requires that its initiation be dependent on retarder deployment, which shall be accomplished by the use of one arming wire between the nose fuze and the retarder. The point at which this wire is attached to

27、the retarder shall be capable of providing a force of not less than 100 pounds over a stroke of not less than 4.5 inches. The item shall permit installation and routing of arming wiredlanyards after the item has been attached to the bomb. 3.1.2.4 Fuze installation. Access to those items installed in

28、 the rear fbze well, MK 376 and FMU-139 shall be available through the side of the item, so as to permit settings to be made or safety pins removed prior to flight. The access shall be located so that a visual check can be made of the arm/safe status of the fuze when installed in the bomb, and the p

29、roper assembly and routing of the arming wire. The .- e access shall allow installation of the fuze in the MK 83 aft fuze well when the item is attached. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-F-85576 13 7777906 O365380 2 3.1.2.5 Fuze fu

30、nction. The item, when attached to the MK 83 bomb and released at 450 Knots Calibrated Airspeed (KCAS) and above, shall provide deceleration along the bomb longitudinal axis of 4 gs in not greater than 0.57 seconds after release of cover and remain at 4 gts or more for not less than 0.75 seconds. Wh

31、en released at 550 KCAS or less, the deceleration along the bomb longitudinal axis shall be not greater than 13 gs after 0.71 seconds from aircraft release. When the system is released in the low-drag mode within the delivery speed and altitude envelope specified in FIGURE 1, the item shall not prod

32、uce deceleration along the bombs longitudinal axis greater than 1.4 gs. The item, when the system is released in the low drag mode, shall not pull the arming wire/lanyard for any retarder initiated fuze. 3.1.3 Major component list. Not applicable. 3.1.4 Government furnished property list. Not applic

33、able. 3.1.5 Government loaned property list Not applicable. 3.2 Characteristics. 3.2.1 Performance. The item, when attached to the MK-83 bomb, shall perform as specified herein and under the following conditions. a. b. C. d. e. f. g. h. Airspeed (1) Carriage and release; limits of the basic aircraft

34、 (LBA) or 650 KCAS whichever is less. Acceleration ( 1 ) (2) Carriage - LBA or -3 .O g to +7.5 g whichever is less Release - +0.5 g to +5.0 g Maximum dive angle for release: (1) Unretarded - 60 degrees (2) Retarded - 45 degrees Aircraft Loading (1 ) All 1,000 lb compatible parent racks - 1 (2) (3) M

35、ultiple Ejector Rack (MER) - 3 Triple Ejector Rack (TER) - 3 Minimum Release Interval from the same MER/TER: (1) 100 ms desired (2) 200 ms required Accuracy (1 Unretarded - 4.0 MILS CEP (300-550 KCAS) ; 5 MILS CEP (550-650 KCAS) (2) Retarded - 12.0 MILS CEP (300-550 KCAS); 14 MILS CEP (550-650 KCAS)

36、 Fuze Compatibility (1) FM-139 and M904 required (2) MK 376 desired High/Low Drag Pilot Option 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-j. k. m, n. P* 9- r. S. MIL-F-85596 (AS) Physical/visual access to tail fuze (ensure correct fuze and arm

37、ing wire installation) Retarder arming wire for arming M904 fuze No debris and all arming wire integral to fin Compatible with existing GP bomb GSE (ground support equipment) Non-explosive AIR system No special tools required Service life of one year Shelf life of ten years 3.2.1.1 Flight. The item

38、shall be capable of meeting all the requirements of 3.2.1when carried and released within the flight envelope shown in FIGURE 1 and at a maximum aircraft dive angle release of 60 degrees unretarded and 45 degrees retarded. 3.2.1.2 Temperature. The item shall be capable of operation at the high tempe

39、rature extremes specified in MIL-STD-210, and over the range of dynamic pres- sures defined by the envelope shown in FIGURE 1. 3.2.1.3 Aircraft separation. The item, when attached to the MK 83, shall separate from the delivery aircraft under the conditions specified in FIGURE 1 such that no contact

40、between the bomb and the aircraft shall occur and no contact shall occur between the bomb and any part of the bomb rack or adjacent stores. 3.2.1.4 Retarder deployment. When released in the high drag mode and within the high-drag envelope of FIGURE 1, the retarder shall deploy in no greater than 1.0

41、 second at 250 KCAS release airspeed. The deployment times at 500 and 650 KCAS release airspeed shall be not greater than 0.500 and 0.400 seconds, respectively. Deployment time is described as the time from the initiation of the retarder deployment process until attainment of maximum drag. The retar

42、der shall remain fully deployed throughout the systems trajectory. 3.2.1.5 Accuracy. The accuracy threshold shall be determined using the procedures and conditions as specified in 4.2.3 and 4.2.4. The accuracy threshold of the system when released in the low-drag mode shall be a ballistic dispersion

43、 not greater than 4 mils, Circular Error Probability (CEP) at 300-550 KCAS and not greater than 5 mils CEP at 550-650 KCAS. The accurracy threshold of the system when released in the high-drag mode shall be a ballistic dispersion of not greater than 12 mils CEP at 300-550 KCAS and not greater than 1

44、4 mils CEP at 550-650 KCAS. 3.2.1.6 Structural adequacy. The item shall be capable of meeting the load requirements of MIL-A-8591. For the carriage phase, the safety factor between the - limit load and the yield load shall be not less than 1.15 and the safety factor between the limit load and the ul

45、timate load shall not be less than 1.5. The item shall be capable of supporting the abloads when the system is released from the aircraft. A factor of safety of 1.0 shall be applied between limit load and yield 6 I- .- Provided by IHSNot for ResaleNo reproduction or networking permitted without lice

46、nse from IHS-,-,-n 2 Co I 9 c - MIL-F-85596 13 W 9799906 0365382 b W _ w v1 4 w d w l 1 1 1 1 O O d C eJ O Irl C w C ln h Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-F-85596 13 9999906 0365383 8 W MIL-F-85596 (AS) load. The factor of safety

47、between limit and ultimate load shall be not less than 1.25. The factor of safety for castings shall be not less than 1.33, The margin of safety shall be positive for all other structures, seams, and joints. Allowable material stress values shall be as specified in MIL-HDBK-5, MIL-HDBK-17, and MIL-H

48、DBK-23. The item shall have the structural integrity to withstand, without yield, the most severe combined loading condition resulting from the aerodynamic carriage loads specified in FIGURE 1 and the inrtial loads specified in MIL-A-8591. The item shall have the structural integrity to withstand, w

49、ithout deformation detrimental to the item performance, the loading condition resulting from the deployment of the item in the high-drag mode. The fins shall be capable of withstanding impact without structual damage attributed to a hung bomb on the centerline stations of the MER and TER bomb rack. 3.2.2 Physical characteristics. All fittings shall include an additional safety factor of 1.2. I I- 3.2.2.1 The item weight