NAVY MIL-A-60837-1968 ACTUATOR EXPLOSIVE ROTARY 1000-48 ASSEMBLY《1000-48 旋转式火药致动装置》.pdf

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1、MIL-A-60837(MJ) 24 January 1968 l4InTARY SPECIFCATION ACINATOR, ExpIioSIVE, ROTARY 1000-48 ASSEMBSJY 1. SCOPE 1.1 This specification is the applicable detail specification for Actuator, Explosive, Rotary 1000-48 Assembly, loaded with cartridge 5000-1, for use in conjunction with other propellant act

2、uated devices in aircrew emergency escape systems. 2.1 !he following documents of the issue in effect on date of invitation for bids or request for proposal form a part of this specification to the extent specified herein, SPECIFICATIONS Military MILA-2550 - Ammunition and Special Weapons, General S

3、pecifica- tion for STANDARDS Military MIL-STD-105 MILSTD-109 MILSTD-U - Ammunition Data Card MS-28741 - Sampling Procedures and Tables for Inspection by - Quality Assurance Terms and Definitions - Hose Assembly - Detachable End Fitting, Medium Attributes Pressure DRAWINGS Munitions Command 9218443 c

4、9218YA - Carton, Packing, Ammunition, for Rotary Actuator, - Box, Packing Ammunition, for Rotary Actuator, 1000 or 1925 Series 1000 or 1925 Series Talley Industries 1000-4-8 - Rotary Actuator Assembly (Copies of specifications, standards and drawings required by contractors in connection With specif

5、ic procurement functions should be obtained from the pro- curing activity or as directed by the contracting officer.) 3 tl THIS DOCUMENT CONTAINS Ifz. PAGES. - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-A-60837 13 7777706 0391482 O MIGA-6083

6、7 (NU) 3. REQmms 3.1 General.- Materials, parts and assemblies shall comply with the requirements specified on the applicable drawings and referenced specifications. Breakamy torque.- All threaded joints of the assembled actuator shall 3.2 withstand a breakaway torque application of 200 inch pounds

7、without loosening or deformation. 1 3.3 Residual magnetism.- The actuator shall not deflect the indicator of the approved compass more than 3 degrees in either direction when passed in front of the compass at a distance of 6 inches. 3.4 Initial lock security.- The hck pin shall secure the piston com

8、ponent of the ball screw assembly so that the strap dmM component is not free to ro- tate. 3.5 Functional. 3.5.1 The actuator shall not fail to fire. 3.5.2 The actuator shall function without mechanical failure (See 6.1). 3.5.3 Initiation.- The actuator shall be fired by a source delivering an outpu

9、t equal to that of an M3AlInitiator at the end of i5 feet of aircraft hose, Size 4, Standard 28741, at TO0 - + 5OF. 3.5.4 Ba1iistics.- The actuator loaded with an accepted cartridge and tem- perature conditioned, when fired, shall separate and eject a 400 pound load from the approved aircraft; seat

10、within an operating time of .i50 seconds minimum and -500 seconds maximum, and function within the performance limits specified in Table I. Tengerature Pressure (psi) -65O 70F 2000 to 4800 65O to 7597 2000 to 4800 2000 tb 4800 . 200 to 205% Acceleration (g) 0.85 to 3.0 0.85 .to 3.0 - 0.85 to 3.0 2 .

11、 . - - 2 f s a:% .- s. - c- ,c - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-i l MIL-A-60837 13 7777706 03V14b 8 = MT LA; 60837 (IN) 4.2.2.4 (Contd) qefect MINOR 201. kcation labels incorrect 202. Shipping plug missing 203. Protective finish inad

12、equate or defective Method of Inspection Visual Visual Visual 4.2.2.5 Packing in Fiber Box, Drawing c921842C3. CRITICAL None defined MAJOR None defined MINOR 201. Sealing strips missing, loose or improperly applie Visual 202. Contents loose Manual 203. Fhps loose or distorted Vi sua1 204, Cut or dat

13、mged through ail impregnated layers Visual 205. Marking, missing incorrect or illegible Visual 4.2.2.6 Packing in Wooden Box, Drawing c9218hU. CRITICA5 None defined MAJOR 201. Contents loose Manual 202. Hardware missing, loose, broken or improperly Manual Lock security.- Each actuator shall be subje

14、cted to an initial lock test. 3.4 shall be cause for rejection of the assembly. Failure of any actuator to comply with the requirements of 4.2.3.4 Functional %estS.- The following tesks shall be performed by the Government. 4.2.3.4.1 Ballistics.- Twenty-one units shall be tested as specified in 4.3.

15、4 to determine compliance with the requirements of 3.5.1 to 3.5.4. The units shall be temperature Wnditioned as provided in Table III and 4.3.4.1. Failure of any unkt to comply with the requirements shall be cause for rejection of the lot. Temperature Sample Size -65O to -70F 650,ta 7* 200 to 205% 7

16、. 7 7 4.2.4 Inspection equipment,- The examLnation and tesks shall be made ushg -I equipment approved by the Government, 7 i: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1-A-60837( MJ) 4.3 Test methods and procedures. 4.3.1 Breakaway torque.- A t

17、orque wrench, set at the torque requirements specified in 3.2 shall be used in conjunction with an adapter to determine the adequacy of the joints. The actuator shall be secured in a holding device and the breakaway %orque applied to the end closure and breech assemblies. 4.3.2 Initial lock security

18、.- The actuator shall be tested for initial lock security by securing the actuator body in a holding device and manually pulling on the strap assembly to assure that the webbing cannot be extended or retracted. 4.3.3 Residual mametism.- The actuator shall be tested for excessive re- sidual magnetism

19、, in an area free of local magnetic effects, by placing the actuator six inches from and at the same height as the compass in a north-south horizontal position (breech end at south) with the compass set in an east-west heading as shown in Figure I. The actuator shall be moved slowly past the com- pa

20、ss in a longitudinal irection for its entire length, rotated 90 degrees in the horizontal position abou% its longitudinal axis and moved slowly past the compass. This procedure shall be repeated for each 90 degree rotation of the actuator, 4.3.4 Functional tests. 4.3.4.1 Temperature conditioning.- P

21、rior to conducting the ballistic test specified in b.3.4.3, the actuator samples shall be subjected to the temperature condition specified in 3.5.4. containing a temperature sensitive element shall be placed in the temperature conditioning chaniber at the same time as the actuator samples. time shal

22、l be a minimum of one hour longer than the time necessary to bring the element contained in the dummy cartridge to the required temperature. A simulated actuator loaded with a dumnny cartridge The conditioning 4.3.4.1.1 Upon completion of the required temperature conditioning, each actuator sample s

23、hall be ballistically tested within 5 minutes after removal from the conditioning chmber. Samples shall be reconditioned if this time is exceeded. I -. 4.3.4.2 Method of testiq.- me actuator tested under the conditions speci- The fixture shall be designed to cover at least fied herein shaU be mounte

24、d on an aircraft; seat in the proper position. a fixture on the aircraft seat. 8C$ of the area comprising the bottom and back of the aircraft; seat. Mount an accelerometer on the fixture to record acceleration of the ejected mass on a line which bisects the angle between the seat bottom and the seat

25、 back. A recording system shall be used to determine the amount of time required to eject the mass after actuation of the actuator under load conditions. Install 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIEA-60837(MLJ) 4,3.4.3 Balhstic test.

26、- Utilize the test fixture specified in 4.3.4.2. The weights shall be Snstalled in the fixture and secured to prevent shifiing. An M3Al initiator or simulated method shall be used to actuate the actuator under test, to actuate the actuator and to measure the amount of ballistic gas pressure in the a

27、ctuator during operation. A pressure port shall be installed in the actua- tor end closure assembly for recording the ballistic gas pressure. The pressure sensitive device for measuring the amount of pressure used to actuate the actua- tor shall be inserted into the system by means of a Tee coupling

28、 between the actuator and the actuating device. ance with the functional requirements of 3.5 within the time specified. 5. PREFARATION FOR DELVERY pressure sensitive devices shall be used to measure the pressure exerted The actuator sample shall be tested in accord- -% 5.1 Packing and marking.- Leve

29、l A.- Packing and marking shall be in accord- ance with Drawings C921443 and C92l8444. 5.2 Data cards.- Data card infom-bion shall be as specified in MILSTD-1167. 6, NOTES 6.1 A “mechanical failure“ is defined as any deformation or breakage of a part, the occurrence of which is other than a design f

30、unction. Custodian: AZ7W-W Preparing activity: Av-M Project No. 1377-A2ll 9 i Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-A-60837 13 m 7799906 03Ll1Ll70 T W MIL-A-60837 (m) I O O 4 R icn H I ! IE ,. 8 ! I , - - .- .L . rl 19 E H k O n t /O Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-