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Abstract: Based
on the study of the mechanical behavior of helicopter structures,
including both experiment and FEM analysis, a simplified mechanical
model for helicopter crashworthiness design, which can be used to
predict the maximum impact force in the crash procedure and design some
energy-absorption components, is proposed. The dynamic response of a
helicopter with initial speed 10.2 m/s vertically impinged at the ground
is calculated. The ratio of the dissipated energy absorbed by the
landing gear to the total input energy and the kinetic energy decreasing
curve of the fuselage during impact process are obtained. The comparison
between the theoretical results and FEM results is reasonable agreement.
Key words: Helicopter Crashworthiness Theoretical model
CLC No: V275
O341
国家自然科学基金资助项目(10272011). Received 20020325, received in revised form
20020615
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