NAVY MIL-A-60681-1967 ACTUATOR ROTARY 1000-37 ASSEMBLY《1000-37 旋转致动装置》.pdf

1、11-60681(u) 25 April 1967 K.OiiO MILITARY SPECIFICATION ACTUATOR, ROTARY 1000-37 ASSEMBLY 1. SCOPE 1.1 This specification is the applicable detail specification for Actuator, Rotary 1000-37 AssenMy, loaded with cartridge 5OOO-l, for use in conjunction with other propellant actuated devices in aircre

2、w emergency escape systems. 2. APPLICABLF: DOCUMENTS 2.1 The 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 MIL-A- 2550 Military - Ammunition and Special Weapons, Gener

3、al Specification for s-s Military MIL-STD-105 - Sampling Procedures and Tables for Inspection MIL-STD-109 MIL-STD-1167 - Ammunition Data Card MS - 28741 by Attributes - Quality Assurance Terms and Definitions - Hose Assembly - Detachable End Fitting, yedim Pressure DRAWINGS Munitions Command Cg21844

4、3 Cg218444 - Carton, Packing, Amrainition, for Rotary Actuator, 1000 or 1925 Series - Box, Packing Ammunition, for Rotary Actuator, 1000 or i925 Series Talley Industries 1000-37 - Rotary Actuator Assembly h THOS D6CUMENP CONTAINS PAGES, Provided by IHSNot for ResaleNo reproduction or networking perm

5、itted without license from IHS-,-,-MIL-A-60681 13 H 7799906 0390848 O m MIL-A-60681( MJ) (Copies of specifications, standards and drawings required by contractors in connection with specific procurement functions should be obtained from the procuring activity or as directed by the contracting office

6、r.) 3. REQUIRFSIENTS 3.1 General.- Materials, parts and assemblies shall comply with the requirements specified on the applicable drawings and referenced specifica- tions. 3.2 Breakaway torque.- All threaded joints of the assembled Actuator shall withstand a breakaway torque application of 200 inch

7、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 of 6 inches. 3.4 Initial lock security.- The lock pin shall secure the pist

8、on component of the ball screw assembly so that the strap drum component is not free to rotate. ._ 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

9、an output equal to that of an Ma1 Initiatog at the end of i5 feet of air- craft liose, Size 4, Standard 28741, at 70 - + 5OF. Ballistics. - The Actuator loaded with an accepted cartridge and 3.5.4 temperature conditioged, when fired, shall separate and eject a 400 pound load fromthe approved aircraf

10、t seat within an operating time of .i50 seconds minimum and .SOO seconds maximum, and function within the performance limits specified in Table I. TABLE 1 Temperature Pressure (psi) Acceleration (g) 65 to 75OF 2000 to 4800 0.85 to 3.0 3.6 Florkmanshig.- The requirements for workmanship are as specif

11、ied on the applicable drawings, referenced specifications and the following: 3.6.1 Metal defects.- All components shall be free from cracks, splits, cold shuts, inclusions, porosity or any similar defects. - -_-_ 2 - . Provided by IHSNot for ResaleNo reproduction or networking permitted without lice

12、nse from IHS-,-,-MIL-A-6068L 13 m 7777706 03LtOBLt7 2 a MIL-A -60 4.2.3.3 Initial lock security.- Each actuator shall be subjected to an Failure of any actuator to comply with the requirements initial lock test. of 3.4 shall be cause for rejection of the ass&iy. 4.2.3.4 Functional tests.- The follow

13、ing tests shall be performed by the Government: 4.2.3.4.1 Ballistics.- Twenty-two units shall be tested as specified in 4.3.4 to determine compliance with the requirements of 3.5.1 to 3.5.3. units shall be temgerature conditioned at 65O to 75OF as provided in 4.3.4.1. The 4.2.4 Inspection equipment.

14、- The examination and tests shall be made using equipment approved by the Government. 4.3 Test methods and procedures. 4.3.1 Breakaway torque,- A torque wrench, set at *he torque require- ments specified in 3.2 shall be used in conjunction with an adapter to deter- mine the adequacy of the joints. d

15、evice and the breakaway torque applied to the end closure and breech assemblies. The actuator shall be secured in a holding 4.3.2 Initial lock security.- The actuator shall be tested for initial lock security by securing the actuator body in a holding device and manually pulling on the strap assembl

16、y to assure that the webbing cannot be extended or retracted. 4.3.3 Residual magn etism.- The actuator shall be tested for excessive residual magnetism, 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 horizonta

17、l position (breech end at south) with the compass se% in an east-west heading as shown in Figure I. The actuator Shan be moved slowly past the compass in a longitudinal direction for its entire length, rotated 90 degrees in the horizontal position about its longi-budinal axis and moved slowly past t

18、he compass. 90 degree rotation of the actuator. This procedure shall be repeated for each 4.3.4 Functional tests. 4.3.4.1- Teqperature conditioninq.- Prior to conducting the ballistic test specified in 4.3.4.3, the actuator samples shall be subjected to the temperature condition specified in 3.5.4.

19、A simulated actuator loaded with a dummy cartridge containing a tenrperature sensitive element shall be placed in the temperature conditioning chamber at the srne time as the actuator the time necessary to bring the element contained in the d- cartridge to the required temperature, sangles. The cond

20、itioning time shall be a minimum of one hour longer than ,- 7 -. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-e- MIL-A-bObL 13 = 7777706 03L10854 b rn MIL-A-o ( MU) 4.3.4.1 .a Upon completion of the required temperature conditioning , each actuato

21、r sqle shall be ballistically tested within 5 minutes after removal from the conditioning chaniher. is exceeded. Samples shall be reconditioned if this time 4.3.4.2 Method of testh&,- The actuator tested under the conditions The fixture shall be designed to specified herein shall be mounted on an ai

22、rcraft seat in the proper position. Install a fixture on the aircraft seat. cover at least 80% of the asea comprising the bottom and back of the aircraft seat. of the ejected mass can be adjusted from POO to 400 pounds. accelerometer on the fixture to record acceleration of the ejected mass on a lin

23、e which bisects the angle between the seat bottom and the seat back. A recording system shall be used to determine tale amount of time required to eject the mass after actuation of the actuator under load conditions. Removable weights may be incorporated Ln the fixture so that the weight Mount an 4.

24、3.4.3 Ballistic test.- Utilize the test fixture specified in 4.3.4.2. The weights shall be installed in the fixture and secured to prevent shifting. An M3A1 initiator or simulated method shall be used to actuate the actuator under test. exerted to actuate the adc%uator and $0 meetsue the amount of b

25、allistic gas pressure in the actuator during o-pzi*%ion. A pressure port shall be installed in the actuator end closme assecibiy for recording the ballistic gas pressure. The pressure sensitive device :?or %sasuring the amount of pressure used to actuate the actuator shall be fncerted into the syste

26、m. by means of a Tee coupling between the actuator axid the actuating device. shall be tested in accordance with the hnc-bional requirements of 3.5 within the time specified. Pressure sensitive devices sh&Li. be used to measure the pressure The actuator sample 5. PREPARATION FOR DELFJEEX 5.1 Packing

27、 and Markinge- Level A.- Packing and marking shall be in 5.2 Data cards.- Data card hf034ti.On shall be as specified in accordance with drawings c!92184,43 and C9218W+4. MIL-STD-1167 9 6. NOTES 6.1 A “mechanical failure“ is defined EB any deformation or breakage of a part, the occurrence of which ia

28、 other than a design function. Custodian: Army - MU Preparing activity : Army - M Project No. 1397-Ai82 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . 1. - LZJ II I 1L-A-60681( MJ) n Fr O *US. GOVERNMENT PRINTING OFFICE: 1987-251-519/6374 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-