Downloaded from https://www.everyspec.com MIL-STD-810D 19 July 1983 FIGURES - Centinued Ease 514.3-36 Minimum integrity test - aircraft/external store 514.3-37 514.3-AI 514.3-A2 515.3-1 equipment Example of acceptable performance within tolerance Vibration test specification development Test exaggeration curve Suggested 1/3 octave band spectra for acoustical noise 514.3-5’I 514.3-70 514.3-79 514.3-80 515.3-2 test One-third octave band spectrum for acouatic testing 515.3-8 of asaembled externally carried aircraft stores Typical store profile Cavity resonance acoustic teat levels Test shock response spectrum for use if measured data 515.3-11 515.3-11 515.3-12 515.3-3 515.3-4 516.3-1 ,.
is not available Random test input spectral density yielding equivalent 516.3-4 516.3-2 516.3-3 test shock response spectra shown in figure 516.3-1 Example of a shock time history showing effective 516.3-6 transient duration (TE) Terminal-peak sawtooth shock pulse configuration and 516.3-7 516.3-4 its tolerance limits (for use when shock response spectrum analysis capability ia not available Trapezoidal ,shockpulse configuration and its tolerance 516.3-5 516.3-8 limits Typical response of equipment to catapult launches 516.3-10 516.3-6 and arrested landings showing oscillatory nature of transient 519.3-1 519.3-2 519.3-3 519.3-4 519.3-5 519.3-6 519.3-7 516.3-16 Generalized gunfire induced vibration spectrum shape 519.3-4 This distance parameter (D) and the depth parameter (Rs) 519.3-6 Multiple guns, closely grouped Test level reduction due to gun standoff parameter Test level reduction due to equipment mass loading Teat level reduction due to depth parameter Decrease in vibration level with vector distance from 519.3-7 519.3-8 519.3-11 519.3-12 519.3-8 520.0-1 520.0-2 520.0-3 520.0-4 520.0-5 520.0-6 gun muzzle Gunfire peak vibration reduction with distance Test profile generation flow diagram Bottom up view of a test cycle Schematic mission profile, altitude and Mach “number Altitude vs pressure Qualification ‘teatcycle example Dynamic pressure (q) as function of Mach number and 519.3-13 519.3-14 520.0-4 520.0-5 520.0-7 520.0-20 520.0-21 altitude Typical aircraft operational mission profile Temperature profile for a single mission type Temperature profile for composite mission Climatic set of temperature profiles for composite 520.0-22 523.0-9 523.0-9 523.0-10 523.0-1 523.0-2 523.0-3 523.0-4 8 mission Climatic set plan showing offset sequence Dynamic pressure, q, profile for composite mission Typical arrangement of apparatus 523.0-10 523.0-11 523.0-11 523.0-12 523.0-5 523.0-6 523.0-7 ix