In order to give some proof that the criteria used in the design of airframes and undercarriages provided adequate strength for the landing case dynamic tests of the landing shock absorber system, and for service purposes of the whole aircraft, were required. At first simple drop tests were carried out, the surface being inclined if fore and aft loadings were required as well as vertical ones. With increasing payload requirements the possibility of reducing undercarriage weight was investigated, and drop tests modified to approximate more closely to the actual case. The contribution of wing lift was allowed for, and the loads due to spin up of the wheels simulated by driving them electrically in the reverse direction before the drop. The technique of tests on the North American AJ‐1 is described.
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