NAVY MIL-A-60657-1967 ACTUATOR ROTARY 1000-39 ASSEMBLY《1000-39 旋转致动装置》.pdf

1、. 1. SCOPE 1.1 This specification is the applicable detail. specification for Actuator, Rotary 1000-39 Assembly, loa conjunction with other propellant actu cape systemi. 2. AFPLICABLJ3 DOCUMENTS . 2.1 Tlie following documents of the issue i for bids or request for proposal form a-part of this specif

2、ication to the ex- tent specified herein * e 5000-1, for ase in On Of= SPECIFICATIONS. Military MIL-A-2550 - Ammunition an6 Special Weapons, General Specification for STANDAI1i)S Military MIL-STD-105 MI L-STD- 109 MIL-STD-1167 - tion Data Card MS - 28741 - Sampling Procedures and Tables for Inspecti

3、on y Assurance Terms and Definitions - Hose Assembly - Detachable End Fi%ting, Medium Pressure DRAWINGS Munitions Command ackhg, Ammunition, for Rotary Actuator, 1000 or.1925 Series Cg218443 C9218444 - Box, Packing Ammunition, for Rotary Actuator, Talley Industries 1000- 39 -, pi-1377 -_.=.-.r- , -

4、- -_ - 1- _ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- ,MIL-A-60657 13 = 7777706 0340604 5 MIGA-60657 (MU) (Copies of specifications, standards and drawings required by contractors in connection with specific procurement functions should be obt

5、ained from the procuring activity or as directed by the contracting officer, ) 3. REQUIREMENTS 3.1 General.- Materials, parts and assemblies shall comply with the re- quirements specified on the applicable drawings andcreferenced specifications. 3.2 Breakaway torque.- All threaded joints of the asse

6、mbled Actuator shall withstand a breakaway torque application of 200 inch pounds without loosening or deformation. 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

7、of 6 inches. 3.4 of the ball screw assembly so that the strap drum component is not free to rotat e. Initial lock security.- The lock pin shall secure the piston component 3.5 Funct ional. 3.5.1 The actuator shall not fail to fire. 3.5.2 The actuator shall function without mechanical failure (See 6.

8、1). 3.5.3 Initiation.- The Actuator shall be fired by a source delivering an output equal to that of an M3AlInitiator at the end of i5 feet of aircraft hose, Size 4, Standard MS28741, at TO0 - + 5OF. 3 5.4 Ballistics. - The actuator loaded with an accepted cartridge and temperature conditioned, when

9、 fired, shall separate and eject a 400 pound load fromthe approved aircraft seat within an operating time of .i50 seconds minimum and .5OO seconds maximum, and function within the performance limits specified in Table I. TABU I Temp erature Pressure (psi) Acceleration (g) 65 to 75OF. 2000 to 4800 0.

10、85 to 3.0 s. 6 Workmnship . - The requirements for workmanship are as specified on the applicable drmings, referenced specifications and the following: 2 - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction o

11、r networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-A-60657 13 7777706 0310607 0 - -_ - - MEL-A-60657 (W) MAJOR (Conk d) Method of In sp ec t ion Defect MINOR None defined CRITICAL - MNOR None defi

12、ned 4-2.2.4 ASsembly Drawing 1000-39, CRI TI CAL 1. ny part missing except 2 Marking missing, incorrect or illegibl MAJOR 101. Length overall 102. Length of str 103. Length of sts 104. Shear studs loose 105. Cap screw loose 106. Threads damaged Gage Gage Gage Visual and Manual Visual and Manual sua1

13、 - -. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-202. Contents loose 203. Flaps loose or distorted 204. 205. Cut or damaged through all impregnated layers Marking, missing incorrect or illegible 4.2.2.6 Packing in Wooden Box, Drawing C9218444.

14、 CRITI CAL None defined MAJOR None defined MINOR 201. Contents loose 202, Hardware missing, loose, broken, or improperly engaged 203. Strapping missing, loose, broken or improperly as sembled 6 f- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provi

15、ded by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-A-60657 13 E 7797706 03LiObLO O Ei MIL-A-60657 (MU) 4.3.3 Residual magnetism.- - The actuator shall be tested for excessive residual magneti.sm, in an area free of lwal magnetic effects, by placing . the

16、 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 compass in a longitudinal direction for its entire length, rotated

17、 90 degrees in the horizontal position about its longitudinal axis and moved slowly past the compass, each 90 degree rotation of the actuator. This pocedure shall be repeated for 4.3.4 Functional tests, 4.3.4 1 Temperature conditioning e - Prim to conducting the ballistic test specified in 4.3.4.3 t

18、he actuator samples shall be subjected to the temperature condition specified in 3.5.4. a dummy cartridge containhg a temperature sensitive element shall be placed in the temperature conditioning chamber at the same time as the actuator samples. the time necessary to bshg the element contained in th

19、e dummy cartridge to the required temperature, R simulated actuator loaded with The conditioning time shallbea mbhum of one hour longer than 4.3.4.1.1 Upon completion of tbe required temperature conditioning, each actuator sample shall be ba,lEas%ically tested within 5 minutes after removal from the

20、 conditioning chamber, is exceeded. Sanlles shall be reconditioned if this time 4.3.4.2 Method of testing.- The actuator tested under the conditions specified herein shall. be mounted on an aircraft seat in the proper position. Install a fixture on the aircraft; seat. The fixture shall be designed t

21、o cover at least 8$ of the area comprising the bottom and back of the aircraft seat. of the ejected mass can be adjusted from 100 to 400 pounds, 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 back. A reco

22、rding system shall be used to determine the amount of tirap required to eject the mass after actuation of the actuator under load renditions. Removable weights may be incorporated in the fixture so that the weight Mount an 4.3.4.3 Ballistic tes$.- Utilize the -best fixkure specified in 4.3.4.2. The

23、weights shall be installed in the fixkusie and secured to prevent shifting. An M3A1 initiator or simulated method shall be used to actuate the actuator under test. Pressure sensitivedeuices shall be used to measure the pressure exerted to actuate the actuator and to measure the amount of baUistic ga

24、s pressure in the actuator during operation. A pressure port shall be installed in the actuator end closure assembly for recording the ballistic gas pressure. 8 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-,-,-I MIL-A-bOh57 13 M 7777906 0340b12 4 m: n .I 10 f f 4 i3 fi r-! *US. GOVERNMENT PRINTING OFFICI: 198?-251-520/6502 5 -. S . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-