Anti-Symmetric Mode Flutter of Winged Reentry Space Vehicle.

摘要

The reentry winged space vehicle 'HOPE' projects is proceeding. HOPE has a tip-fin wing which forms a non-planar wing. Anti-symmetric mode flutter experiments were conducted on a similar configuration model to HOPE by using the sting supporting system in which the rolling mode can be controlled in a transonic wind tunnel (NAL). Several flutter points have been obtained for a single model. The results of the experiments and those of the analysis by DPM (Doublet-Point Method) are compared. The comparison shows good agreement in the subsonic region. In the supersonic region, however, the experimental flutter speed rise considerably, making the analytical results conservative. It has a tendency to agree again as the Mach number increases.