Aileron/elevators and body flap for roll, pitch, and yaw control
Patent 5707029 Issued on January 13, 1998. Estimated Expiration Date: 
March 7, 2016. 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 7, 2016. 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 ReferencesInventorApplicationNo. 611514 filed on 03/07/1996US Classes:244/225, With dual purpose surface structure (e.g., elevons)244/88, Rudders universally mounted244/90RAilerons and other roll control devicesExaminersPrimary: Grant, WilliamAttorney, Agent or FirmForeign Patent References
International ClassB64C 009/06AbstractThe present invention discloses an aircraft control system having simultaneously controllable rear aileron/elevators and a retractable body flap for longitudinal stabilization. The aileron/elevators are airfoils comprising the complete horizontal tail plane. Control arms for the rear aileron/elevators are capable of pivotal movement about the longitudinal axis of the aircraft while the aileron/elevators are secured to the control arms by axles pivotal about the lateral axis of the airfoil, for directional control. With two degrees of rotational movement, the aileron/elevators are capable of maneuvering the aircraft in all three axes, providing a much simpler mechanism than the conventional control surfaces. Added safety is accomplished by removing lateral control from the wings. Weight savings and reduced drag also result from eliminating the vertical stabilizer and rudder and consolidating the controls for both ailerons and elevators of conventional aircraft. | |
