Downloaded from https://www.everyspec.com MIL-STD-810D 19 July 1983 d. ~. This procedure generally conforms’to requirements for pyrotechnic shock testing in MIL-STD-1540 (USAF) for space vehicles. The’ pyrotechnic type shock test typically requires that the eauioment to be tested be subjetted to an intense, high-frequency to meet the test response spectrum using a usually result in a severe overtest at the the higli-frequenty requirements. oscillatory disturbance. An attempt single acceleration pu19e will lower frequencies in order to meet I-3.1“0 lrO~edure VIII -.. a. Procedure VIII is for equipment that will be transported by rail.
It is intended to determine the effect of normal railroad car impacts that occur during rail shipment; b. Ik2stric-. Procedure VIII is not intended for testing small individually packaged pieces of equipment separately when they would normally be shipped (and tested) mounted on a pallet. . c. Test cqmi2Mma. . . This test is conducted by mou~ting the test item in its rail shipment configuration in a rail car which undergoes a series of impacts at 13, 14.5, or 16.2 Km/hr (eight, nine, or ten miles per hour).
If the test item can be’shipped only in one orientation, it shall be impacted twice in each directton of that orientation at speeds of 13, 14.5, and 16.2 Km/hr (eight, nine, and ten miles per hour)”,~ five percent, for a total of 12 impacts. If the test item can be shipped in two orientations, it shall be impacted once in each direction of each orientation at speeds of 13, 14.5, and 16.2 Km/hr for a total of 12 impacts. ,. d. Data for the rail impact test were derived from statistical data on frequency of impacta”with relationship to apeed and frequency of occurrence. Brakes are used on.the buffer car to make the teat conservative. 1-3.11 ~ e a. ~.
This procedure is intended for equipment mounted in or on fixed-wing aircraft that are subjected to catapult launches and arrested landings. \ b. None c. lest Condlfmmi. . . Whenever possible, teat conditions shall be derived from measured data on applicable’carrying aircraft (see General Requirements, paragraph 4.3, Use of Field/Fleet Data), since shock responses can be affected by local influences such as wing and fuselage bending modes, pylon interfaces, and structural damping. . . .~ However, if acceptable field-derived data are ‘notavailable, the following guidance is offered in which a sinusoidal burst is used to simulate each catapult or launch event. . .
METHOD 516.3 19 July !983 516.3-15