This paper describes a method for the determination of the ﬂexible modes of an air-breathing hypersonic vehicle. The method outlined here takes into account changes in vehicle mass and structural temperature over the duration of the vehicle’s trajectory. A simple sizing program is outlined to estimate the vehicle volume, mass, and planform requirements for a dual- cycle (rocket and scramjet) powered vehicle. It is shown that the varying mass eﬀects dominate the frequencies and mode-shapes over the structural heating eﬀects. We then discuss the eﬀects of the structural modes on the transmission zeros.
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