SURVIVABILITY SEAT DESIGN DYNAMIC TEST PROGRAM
Final technical rept.
AVIATION SAFETY ENGINEERING AND RESEARCH PHOENIX AZ
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The report presents the results of a series of dynamic tests conducted with four different concepts of experimental crew seats. The experimental seats were designed and constructed by four helicopter manufacturers. The seats were designed to withstand static load factors equivalent to those recommended in TRECOM Technical Report 63-4, Crew Seat Design Criteria for Army Aircraft, dated February 1963. The design load factors recommended in the above referenced report were as follows longitudinal-45G for 0.10 second lateral-45G for 0.10 second and vertical-25G for 0.10 second. Special kits for small arms ballistics protection were also designed and installed in the seats tested. These seats were designed exclusively using static load factors. No previous testing was conducted by any seat manufacturer prior to the conduct of these tests. The four seats were tested under four load conditions. Two of the conditions involved simultaneous half loads on the seats in two different seat positions, and two of the conditions involved full loads in two different seat positions. Only one of the four seats tested withstood the loads imposed for all four conditions. Three of the seats failed and were damaged beyond economical repair when each was subjected to the first full load test condition. The report also includes a detailed description of an acceleration device which was specially designed and fabricated for this series of tests.