A reentry space vehicle with nonplanar wings, which was planned to be developed in Japan, has a roll elastic freedom during launch. This is because of an attachment between the vehicle and the launch rocket. This study describes the flutter characteristics of a reentry space vehicle model in both launching and free-flight configurations. Results of wind tunnel tests and analyses reveal that the antisymmetric mode flutter becomes critical in both configurations and the existence of the roll elastic freedom further decreases the critical flutter speed. The result also shows that the analytical and experimental flutter speeds differ significantly in the supersonic region. Corrected analysis is conducted by using the measured local Mach number, and it is found that the interference between the blunt fuselage and nonplanar wings results in a discrepancy in the flutter speed.
Flutter characteristics of reentry space vehicle with nonplanar wing
Flatterschwingungen eines Raumflugzeugs mit unebenen Tragflächen
AIAA Journal (online) ; 44 , 10 ; 2267-2273
2006
7 Seiten, 17 Bilder, 2 Tabellen, 22 Quellen
Article (Journal)
English
Befestigung , Biegeschwingung , Drehschwingung , Finite-Elemente-Methode , Flatterschwingung , Fluid-Struktur-Wechselwirkung , kritische Geschwindigkeit , Mach-Zahl , Modalanalyse , Raumflugzeug , Rollen (Drehbewegung) , Schwingungsmode , Stabilitätsgrenze , Start , Theorie-Experiment-Vergleich , Überschallströmung , Weltraumrakete , Windkanalprüfung , Tragfläche (Aerodynamik) , Flügelprofil
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