Abstract
TRANSIENT response to explosive shock loading of aircraft structures must be evaluated with due regard for aerodynamic and structural resonance phenomena. An explosively generated shock front, after normal reflection from a rigid surface, will be at least doubled in amplitude; the exact factor depends on the incident shock amplitude and ambient atmospheric pressure. In addition, a transient load with a short rise time may precipitate a peak response twice that caused by a slowly rising (static) load of the same amplitude. Results of static load tests on aircraft are often extrapolated to give transient loading limits without obvious consideration of the points mentioned above. Exhaustive transient loading tests or detailed calculations are seldom carried out. This paper outlines finite element calculations made with NASTRAN on a model of an aircraft door. Good agreement was found with statically produced displacements of a fullscale sample of a landing gear door from an A-6 fighter bomber. Transient calculations were made, also with NASTRAN, and these showed that accepted transient load limits appear conservative.
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