초록 ▼

Tilting the stabilizer at an extreme angle to the fuselage, with leading edge down, and controlling and varying engine thrust comprise a method for all-axis control of a generally conventional aircraft in ultra deep stall. The method is effective in recovery from unstable and unusual flight attribut

Tilting the stabilizer at an extreme angle to the fuselage, with leading edge down, and controlling and varying engine thrust comprise a method for all-axis control of a generally conventional aircraft in ultra deep stall. The method is effective in recovery from unstable and unusual flight attributes and in landing emergencies; the aircraft may land in the ultra deep stall configuration or conventional flight may be resumed. So-called flying wing aircraft, where pitch control surfaces are incorporated with the trailing edge of the primary lift surface, are also controllable in ultra deep stall by the method of this invention.

대표청구항 ▼

A method for controlling the flight of a generally conventional airplane, said airplane having a fuselage with nose and tail, a fixed wing as the primary lifting surface, a rudder at the tail for yaw control, a power system for generating forward thrust substantially parallel to the longitudinal axi

A method for controlling the flight of a generally conventional airplane, said airplane having a fuselage with nose and tail, a fixed wing as the primary lifting surface, a rudder at the tail for yaw control, a power system for generating forward thrust substantially parallel to the longitudinal axis of said fuselage, and a generally planar fully tiltable, by rotation about a transverse horizontal axis, stabilizer surface at said tail for pitch control, comprising the steps of: tilting said stabilizer surface, leading edge downward relative to said longitudinal axis of said fuselage, until the angle of said primary lifting surface relative to the oncoming air flow is positively increased to approach stalling; further tilting said stabilizer surface with leading edge downward relative to said longitudinal axis of said fuselage, until the angle of said primary lifting surface relative to said oncoming air flow is further positively increased and stall of said primary lifting surface is induced; further tilting said stabilizer surface with leading edge downward at an extreme angle of approximately 65 to 90 degrees relative to said longitudinal axis of said fuselage, until the angle of said primary lifting surface relative to said oncoming air flow is positively increased such that substantial flow line separation occurs along said primary lifting surface causing deep stall of said primary lifting surface; varying said power system thrust whereby the attitude and flight path of said airplane is controlled during deep stall of said primary lifting surface.