I 1, Downloaded from https://www.everyspec.com MIL-STD-81OC 4.6.3.1.2 Captive flight. Two test levels are required, a functional level and an endurance 1evel. For each axis, one-half of the functional test shall be conducted first, then the endurance test, followed by the secOnd. half of the functional test. The equipment shall perform according to the equipment specification operating requirements in accordance with General Requirements, 3.2.during the functional testing. The accelerationpower spectral density (G2/Hz) of applied vibration, as measured on the test fixture at mounting points of the test item, shall be according to table 514.2-IV and figure 514.2-4 except as noted below.
The functional and endurance test time durations and other test conditions shall be determined from the test level requirements and other parameter values from table 514.2-IV. If the computed functional and endurance (T=l) test levels (w2) are less than O.04 G2/Hz, use W2 = O.04 G2/HZ and T = 1 for the endurance test. ., I I 4.6.3.1.3 Free flight functional test.. For stores that are deployed by separation from the aircraft [free flight) such as bombs and missiles, a free flight functional test shal1 be conducted in addition to the captive flight tests of 4.6.3.1.2.
The equipment shall perform according to the equipment specification operating requirements in accordance with General Requirements, 3.2 during the functional testing. 4.6.3.1.1, 4.6.3.1.2, table 514.2-IV, and figure 514.2-4 shall be used to determine the test pro- cedures, levels and frequency spectra for the free flight test except as noted below. In this case, factors Al, A2, and (N/3T) shall be set equal to one.~ The value of q shall be the maximum value attainable during free flight. The duration of this functional test, per axis, shall equal the maximum free flight time expected at maximum q, but not less than 30 seconds.
i In the event that all free flight functional checks are made during the cap- tive functional test and the captive functional test levels are larger than or equal to those derived here (4.6.3.1.?.),no free flight functional test is required. NOTE: Items marked DISCONTINUED refer to items of the superseded issue of MIL-STD-810 including notices thereto. 4.6.3.1.4 References a. Dreher, J. F., Lakin, E. D., Tone, E. A., “Vibracoustic Environment and Test Criteria for Aircraft Stores During Captive Flight,” Shock and Vibration Bulletin No. 39, Supplement, (PP lS-40), NRL, Wash., DC, April 1969. b. Dreher, J. F., ,,Effects of Vibration and Acoustical Noise on Aircraft/ Stores Compatibility Proc.
Aircraft Store Compatibility Symp., Vol. 6, pp 245-272, Eglin AFB, Florida, November ~969. MEll+OD“514.2 514.2-10 / \ I