Aileron/elevators and body flap for roll, pitch, and yaw control

Details Aileron/elevators and body flap for roll, pitch, and yaw control Aileron/elevators and body flap for roll, pitch, and yaw control

1996-03-07

1998-01-13

Grant, William

Aeronautics and astronautics

Aircraft control

Pilot operated

244 88, 244 90R, B64C 906

Patent

active

057070296

ABSTRACT:
The 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.

REFERENCES:
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