Evaluation of the aeroelastic stability of the Ariane 5/Hermes vehicle in the low frequency range is presented. Two prediction methods are described, one based on the quasi-steady theory, the other using the slender bodies formulation. The prediction methods allow a computation of the aerodynamic damping and the frequency variation of the low frequency structure eigenmodes. An application to the Hermes launch configuration for various Mach numbers is presented. The study was extended by subscale wind tunnel tests, on a mockup reproducing a few significant modes, in order to validate or update the calculation tools. Conclusions from the comparison between experimental and calculation results are given.
Prediction Methods of Launcher Aeroelastic Stability. Application to the Ariane 5/Hermes Vehicle. Comparison with Test Results
1989
13 pages
Report
No indication
English
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