NAVY MIL-A-85802-1986 ACTUATOR ELECTROMECHANICAL LINEAR《线性机电舵机》.pdf
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1、II -. MIL-A-5802 LO = 7777906 03bb043 O W i(- 0H-q MIL-A-85802(AS) 10 October 1986 MILITARY SPECIFICATION ACTUATOR, ELECTROMECHANICAL, LINEAR This specification is approved for use within the Naval Air Systems Command, Department of the Navy, and is available for use by all Departments and Agencies
2、of the Department of Defense. 1. SCOPE 1.1 Scope. This specification establishes the requirements for the manufacture and inspection of one type of electromechanical linear actuator. The test limits in this specification define minimum acceptable capabilities. 2. APPLICABLE DOCUMENTS 2.1 Government
3、Documents. 2.1.1 Specifications and standards. The following specifications and standards form a part of this specification to the extent specified herein. Unless otherwise specified, the issues of these documents shall be those listed in the issue of the Department of Defense Index of Specification
4、s and Standards (DODISS) and supplement thereto, cited in the sol ici tation. SPECIFICATIONS MILITARY MIL-T-7743 MIL-E-17555 Electronic and Electrical EauiPment. Accesories and Testing, Store Suspension and Release Equipment, General Specification for AMSC NIA Repair Parts, Packaging and Packing of
5、Beneficial comments, recommendations, additions, deletions) and any pertinen data which may be of use in improving this document should be addressed to the Naval Air Engineering Center, Systems i Engineering and Standardization Department (Code 931, Lakehurst, j NJ 08733-5100, by using the self-addr
6、essed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter. FSC 1095 DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. . THIS DOCUMENT CONTAINS / cocked and uncocked. At the completion of each resonance search
7、 test, the actuator shall be activated utilizing 28 VDC. 4.6.10.4 Resonance dwell. The actuator shall be subjected to a sinusoidal vibration resonance dwell test in each of three mutually perpendicular axes. The test level shall be 0.060 D.A. or 10 gs whichever is less. The total number of cycles in
8、 each axis shall be 540,000 cycles. The number of cycles shall be divided equally among the resonant points determined in 4.6.10.3 (see example). The actuator shall be vibrated at the four most severe resonant frequencies. If no resonant frequencies are noted, the actuator shall be vibrated at 50 Hz
9、 for 3 hours in each axis. each of the two actuator modes, cocked and uncocked. The total test time shall be 18 hours for the 50 Hz dwell test. The test shall be repeated for 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. MIL-A-85802 LO m 9Ob 03
10、bb052 L MIL-A-85802(AS) Exampl e : Given: Total number of cycles per axis required: 540,000 cycles Number of resonant frequences determined per axis: 2, 1.200 Hz 2.500 Hz Calculated: Number of cycles per resonant point: 540,000 = 270,000 cycles. 2 Test time at 200 Hz: 270,000 cycles = 22.5 minutes 2
11、00 Hz x 60 seclmin Test time at 500 Hz: 270,000 cycles = 9.0 minutes 500 Hz x 60 sec/min Total test time = 31.5 minutes 4.6.11 Service life. The actuator shall be subjected to 5,000 cycles of operation. The actuator shall be mounted as indicated by the applicable drawing, The firing circuit shall be
12、 energized once for each cycle to activate the actuator, The duty cycle for the actuator shall be 20% on and 80% off (see 3.3.10.1). After every 500 cycles, the actuator shall be subjected to the test of 4.6.2.3. The last 1,000 cycles shall be conducted with the actuator plunger striking the lever o
13、f a test fixture which offers a 20 pounds resistance. plunger shall contact the 20 pound load after it moves 1/16 inch. actuator shall be subjected to the test of 4.6.2.3 after the completion of 5,000 cycles. 4.6.12 Shock. 4.6.12.1 Shock pulses. The actuator shall be subjected to the shock pulses in
14、 each of the three mutually perpendicular axes, not in any specific order. The test parameter tolerances shall be as follows: pulse duration: 1 millisecond. The actuator shall be mounted to the shock table by means of a rigid fixture utilizing the mounting area as indicated by the applicable drawing
15、. The control accelerometer shall be mounted on the test fixture, adjacent to the mounting area of the actuator. activation of the actuator plunger, failure of the actuator to function, or structural damage to the actuator shall be cause for rejection. 4.6.12.2 Test. The actuator, in the cocked posi
16、tion, shall be subjected to two half-sine shock pulses in each axis. The acceleration level shall be 125 gs with a pulse duration of 11 milliseconds. The fixture shall be designed so that the actuator The acceleration: -c lo%, Inadvertent 4.6.13 Post test. 4.6.13.1 Salt fog, internal. All of the int
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