NAVY MIL-E-81910 A (1)-1978 ELECTRICAL POWER GENERATING AND CONTROL EQUIPMENT AIRCRAFT GENERAL SPECIFICATIONS FOR《飞机电力发电和控制设备一般规格》.pdf

《NAVY MIL-E-81910 A (1)-1978 ELECTRICAL POWER GENERATING AND CONTROL EQUIPMENT AIRCRAFT GENERAL SPECIFICATIONS FOR《飞机电力发电和控制设备一般规格》.pdf》由会员分享，可在线阅读，更多相关《NAVY MIL-E-81910 A (1)-1978 ELECTRICAL POWER GENERATING AND CONTROL EQUIPMENT AIRCRAFT GENERAL SPECIFICATIONS FOR《飞机电力发电和控制设备一般规格》.pdf（2页珍藏版）》请在麦多课文档分享上搜索。

1、4 -74-50 MIL-E-81910A( AS) Amendment 1 23 June 1978 MILITARY SPECIFICATION Electrical Power Generating and Control Equipment, Aircraft, General Specification For This amendment forms a part of Military Specification MIL-E-81910A(AS) dated 21 November 1977. PAGE 6 Table II Column 2 change 2,6,8 etc.

2、to read 2,6,10 etc. PAGE 9 Paragraph 4.6.3.1.2, lines 10 and 11: Delete “the component shall be. varied as follows: in successive four hour cycles: one hour each“ and substitute “the component shall be varied in successive cycles as follows: four hours each.“ PAGE 13 i Paragraph 4.6.9: Delete, and s

3、ubstitute: Vibration. Components shall be classified as engine mounted (starters, generators, constant speed drives, etc. ) or non-engine mounted (inverters, converters, regulators, power monitors , etc). and qualification verification components shall be subjected to sinusoidal type forcing functio

4、ns . Non-engine-moun teci qual if i cati on components shall be subjected to both sinusoidal and random vibration forcing functions. Non-engine-mounted qualification verification components shall be subjected to random vibration forcing functions only. Engine mounted qualification PAGE 15 Paragraph

5、4.6.9.2: Delete, and substitute: “Non-engine-mounted components. Non-engine-mounted components shall be vibrated in accordance with Procedure lA, Method 514.2, MIL-STD-810. Procedure 1A s ha1 1 be accompl i shed using broadband random vi brati on. Two test levels are required, a functional level and

6、 an endurance level. .For each axis of the three orthogonal axis of the component, one half of the functional test shall be conducted first, then the endurance test, followed by the second half of the functional test. The acceleration power spectral density (G/Hz) of applied vibration and test envel

7、ope for the functional and endurance tests shall be as depicted in Figures 4 and 5, respectively. The functional and endurance test time durations ,- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-81910A( AS) Amendment 1 23 June 1978 shall be

8、one hour each for each axis. In addition, another sample shall be subjected to sinusoidal cycling via Procedure I, Method 514.2, MIL- STD-810. The vibration levels and test envelope shall conform to the requirements of curve M, Figure 514.2-3 and the test time schedule of Table 514.2-111, for compon

9、ents mounted without vibration isolators. During the functional and cycling test, the component shall operate at full electric load, and.when functioning as a control component, it shall control the other components of the system as specified in the equipment specification. During the endurance test

10、, the component shall be operating but need not be monitored for specified performance. component, however, shall be observed for catastrophic failures. deterioration or change in performance of the component shall not exceed that defined per 4.5. At the conclusion of the test, the component shall b

11、e operated and inspected per 3.3. cracking or rupture of any solder connection or part of the component, or of the mounting assembly. “ The Any There shall be no evidence of Preparing Activity NAVY - AS Project NP. 6110-N22-4 *V.S. GOVERNMENT PRINTING OFFICE: 1978-709-22/9249 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-