Aerospace vehicle yaw generating systems and associated methods

Details Aerospace vehicle yaw generating systems and associated methods Aerospace vehicle yaw generating systems and associated methods

B - Operations, Transporting

64

C

B64C 9/00 (2006.01) B64C 9/14 (2006.01) B64C 9/34 (2006.01)

Patent

CA 2603819

Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage (101) with a first portion (111) and a second portion (112) . The system can further include a movable control surface (142a, 142b) coupled to the fuselage and extending generally in a horizontal plane . The control surface can be movable to a deflected position in which the control surface can be positioned to create a flow pattern proximate to the fuselage when the aerospace vehicle is located in a flow field. The flow pattern can be positioned to create a pressure differential between the first portion (111) of the fuselage and the second portion (112) of the fuselage. The first and second portions can be located so that the pressure differential produces a yawing moment (Rmr) on the aerospace vehicle .

L'invention concerne des systèmes de génération de lacet pour véhicule aérospatial et des procédés associés. Un aspect de l'invention concerne un système de génération de lacet pour véhicule aérospatial comprenant un fuselage composé d'une première et d'une seconde partie. Ledit système peut également comprendre une surface de commande mobile couplée au fuselage et s'étendant généralement dans un plan horizontal. La surface de commande peut se déplacer vers une position déviée dans laquelle ladite surface de commande peut être positionnée afin de créer une configuration d'écoulement à proximité du fuselage lorsque le véhicule aérospatial est situé dans le champ d'écoulement. La configuration d'écoulement peut être positionnée afin de créer un différentiel de pression entre la première et la seconde partie du fuselage. Ces première et seconde parties peuvent être placées de sorte que le différentiel de pression produit un moment de lacet sur le véhicule aérospatial.

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