Methods and arrangements tailoring aerodynamic forces afforded by a payload to reduce flight loads and to assist flight control for the coupled system
Patent 5322248 Issued on June 21, 1994. Estimated Expiration Date: 
March 26, 2012. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.
March 26, 2012. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent References 3065937 3204892 3290681 3702688 Aerospace vehicle Detachable thrust vector mechanism for an aeronautical vehicle Earth-to-orbit vehicle providing a reusable orbital stage Segmented projectile with de-spun joint Launch vehicle with interstage propellant manifolding Integrated launch and emergency vehicle system InventorAssigneeApplicationNo. 857876 filed on 03/26/1992US Classes:244/3.15, Automatic guidance244/55, Arrangement244/63, LaunchingD12/320Space satellite or habitat (7)ExaminersPrimary: Huppert, Michael S.Assistant: Ansley, Virna Lissi Attorney, Agent or FirmInternational ClassesB64G 001/14F42B 010/00 F42B 015/01 AbstractAn arrangement for controlling the flight of a launch vehicle and a coupled payload, such a spaceplane, from launch to the separation of the payload from the vehicle. The launch vehicle is provided with controllable gimballed rocket engines and optionally with aerodynamic control surfaces, that are controlled by flight control systems. The payload having controlled flight surfaces has control systems that cooperate with those flight control systems carried by the launch vehicle to jointly control the coupled launch vehicle and coupled payload during coupled flight. The cooperating flight control systems provide open and closed loop control systems that react to winds measured prior to launch and atmospheric disturbances as indicated by on-board sensors during flight. The payload is mounted on the launch vehicle at a cant angle relative to the longitudinal axis of the launch vehicle to optimize its lift to the coupled launch vehicle and payload. Roll steering is also used to minimize the exposure of the vehicle's most critical plane to atmosphere disturbances and/or to maximize available control authority, in addition to pitch and yaw steering.Other References
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