Abstract: A method of effecting recovery of a high speed aircraft from a condition of incipient or developed spin involves, upon entry into the condition, deploying at least one parachute coupled only to the forebody of the aircraft forward of the center of gravity, and is particularly effective in recovering from a flat spin. After recovery, the chute or chutes can be collapsed, released or retracted. The chute is deployed in response to predetermined angle of attack and yaw rate of the aircraft, which may be accomplished automatically under the control of spin condition sensing means. The chute is highly effective because of its location, and hence may be relatively small, the size of the chute, when deployed being such as to have a negligible influence on the free falling rate of sink of the aircraft.

Abstract: An aerodynamic spin control device or apparatus is provided for high speed aircraft for effecting inherent aerodynamic spin resistance and/or automatic spin recovery for the aircraft. In one embodiment clam shell doors or like devices are pivotably mounted individually and symmetrically at their forward ends in the forebody area of the aircraft so as to be automatically deployable outwardly in response to spin created forces, whereby to change the fuselage yawing moment from pro-spin to anti-spin by changing the flow field over the fuselage forebody at high angles of attack, by effectively changing the geometric characteristics of the forebody. The doors, in their housed or undeployed positions, conform to the normal contour of the forebody of the aircraft and can be armed (i.e. unlocked) manually or automatically. When unlocked, the doors would extend until the centrifugal and aerodynamic forces acting on the doors are in balance.