Abstract
In order to achieve reasonably aero-engine landing shock data induction, first filter the shock data samples through ESD (Energy Spectrum Density) and SRS (Shock Response Spectrum), and then Actual SRS and Standard SRS were given on relevant standards and mathematical statistical methods. Casing shock of aeroengines were measured during landing, and Actual SRS and Standard SRS of two types of aero-engine installed in the same aircraft were obtained. The differences of shock characteristics on different directions in the same position were analyzed with the differences of shock characteristics of two types of aero-engine. The results show that the shock characteristics on different directions on the same position may vary greatly, and it is possible to reduce the risk of shock damage through changing installation direction of equipments or structures. Shock characteristics of two types of aero-engine may vary greatly, so that measured shock data of corresponding aero-engine should be selected as test condition on the shock test of airborne equipments or structures. The conclusions provide some guidance for shock absorption design of aero-engine and installation of airborne equipment.
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