The paper provides an analytical assessment of the flutter character of an unclassified National Aerospace Plane configuration known as the demonstrator. Linear subsonic, supersonic, and hypersonic analysis indicate that the vehicle is prone to body-freedom flutter resulting from the decrease in vibration frequency of the all-moveable wing at high flight dynamic pressures. As the wing-pivot frequency decreases, it couples with the vehicle short-period mode resulting in dynamic instability. A similar instability sometimes occurs when the pivot mode couples with the fuselage-bending mode. Also assessed, for supersonic flight conditions, are configuration variations that include relocation of the wing further aft on the lifting-body fuselage, and the addition of body flaps to the rear of the vehicle. These changes are destabilizing because they result in severe wing-pivot/fuselage-bending instabilities at dynamic pressures lower than the instabilities indicated for the original demonstrator. Finally, a two-point wing support and actuation system concept is proposed for the National Aerospace.
Aeroelastic character of a national aerospace plane demonstrator concept
Die aeroelastische Eigenschaften eines nationalen Raumflugzeuges dessen Konzept als Demonstrator bekannt ist
1993
8 Seiten, 11 Bilder, 9 Quellen
Conference paper
English
Luftfahrttechnik , Raumfahrttechnik , Raumflugzeug , Aerodynamik , elastische Eigenschaft , analytische Untersuchung , Betriebsverhalten , Überschallgeschwindigkeit , Hyperschallgeschwindigkeit , Tragflügel , Flugzeugrumpf , Schwingungssystem , dynamische Festigkeit , Biegefestigkeit , Prozessoptimierung , Druckverteilung , Schwingungsdämpfung
Mechanical concept of W-WING whirl flutter aeroelastic demonstrator
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