Abstract: A method and apparatus for flying a folding fin from a stored folded position on a flight vehicle housing to a deployed erect position, using available aerodynamic or fluid forces to control the fin deployment. The fin is erected in several stages. First, a hinge spring bias or lifting wedge means, or combination of fin and body shape, raises the fin surface sufficiently to engage the high-speed fluid flow over the vehicle housing. Next, a motion sensor measures the fin erection angle. Finally, a feedback control system adjusts the fin control angle to increase or reduce the time rate of change of fin erection angle, as necessary. In this manner, the fin can be "flown" into its deployed position in a smooth and controlled manner whereupon it is locked into the deployed erect position on the vehicle housing.

Abstract: A deflated airbag is located on the outside of a missile or other vehicle beneath a folded, pivotally mounted airfoil member prior to launch, and a supply of pressurized gas is connected to the interior of the airbag via a suitable valve. After launch, or after lowering of a launch platform in the case of launch from an aircraft, an actuator such as an acceleration sensing device or timing device opens the valve, supplying gas to inflate the bag and simultaneously urge the airfoil into an extended, working position. After the airfoil is locked in its extended position, the airbag rapidly deflates and may be dropped off or retracted. Where more than one airfoil is to be deployed, separate airbags are located beneath each of the folded airfoils and a common gas supply is connected to all of the airbags.

Abstract: A lateral thrust assembly for missile maneuvering comprises an annular array of outwardly directed nozzles, each nozzle having a releasable plug normally blocking flow of propellant gases out of the nozzle. A plug release mechanism associated with each plug allows that plug to be released to open the respective nozzle. A combustion chamber containing propellant is connected to the inner ends of all the nozzles. The propellant is ignited when one or more selected plugs are released to allow opening of the associated nozzle or nozzles, controlling the direction of the lateral thrust applied to the vehicle.

Abstract: A lateral thruster for missiles is provided which comprises two or more individually rotatable thruster motors with integral nozzles. If the thrusters are located at or near the center of gravity of the missile, the missile can be maneuvered while it remains pointed at the target. Locating the thrusters forward or aft of the missile center of gravity enables steering forces as well as lateral translational and roll forces to be provided. The thruster motors need not be disposed in pairs. The use of integral nozzles obviates sealing problems and allows mountings that permit rapid rotation of the thruster motors to improve missile response time. The lateral thruster disclosed is effective at nearly all aerodynamic angles of attack, missile velocities, and altitudes. The thruster as a unit is enclosed by a shroud that blends into the missile body contour. Possible propellants for the thruster motors include solid propellants and compressed gases.