In the process of hypersonic flight in the dense atmosphere, the loading environment of the vehicle is extremely harsh. The air at the front end is severely compressed and fricts with the windward side, resulting in a sharp rise in the surface temperature of the aircraft. With the increase of the flight Mach number, the phenomenon of aerodynamic heating becomes more and more serious. Therefore, the influence of high temperature must be considered in the ground modal test of the aircraft structure. However, the measurement of vibration response signal in high temperature environment has become a big problem. This paper introduces a non-contact vibration signal test method, which is applied to the modal test of carbon fiber resin matrix composites in high temperature environment. The modal parameters of composite materials in different temperature environments are obtained successfully, and good results are achieved.
Access to the requested content is limited to institutions that have purchased or subscribe to SPIE eBooks.
You are receiving this notice because your organization may not have SPIE eBooks access.*
*Shibboleth/Open Athens users─please
sign in
to access your institution's subscriptions.
To obtain this item, you may purchase the complete book in print or electronic format on
SPIE.org.
INSTITUTIONAL Select your institution to access the SPIE Digital Library.
PERSONAL Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.