Integrated thrust vector aerodynamic control surface
AssigneeGeneral Dynamics Corporation
InventorInge Maudal
Life of this patent
Estimating the term…
Abstract
A missile is disclosed on which constant burning thrust reaction motors are provided integral with the tail panels of the missile to enhance the effect thereof, particularly during the boost phase of flight. The motors provide thrust along the chord of the tail panel and are moved about the axis of rotation of the tail panel by the servo motor associated therewith. The servo motors are activated by central missile control circuitry.
Claims6
A missile comprising:
- a cylindrical missile body;
- main propulsion means acting along the axis of the body to propel the missile;
- a plurality of tail panels pivotably mounted to and exteriorly of the body and pivotable about an axis normal to the cylindrical surface of the body, for aerodynamically controlling direction of the missile in flight;
- a servo motor associated with each tail panel for controlling the angular position of the tail panel relative to the missile body;
- control circuitry for activating the servo motors to control the flight of the missile;
- and
- a continuously burning reaction thrust motor integral with and mounted in each tail panel and rotatable therewith for providing thrust along the chord thereof enhancing the aerodynamic control of the missile, and for developing rotational forces on the body in the absence of aerodynamic forces.
In conjunction with an improved missile control system for controlling the flight of a missile about pitch, roll and yaw axes of the type having a plurality of tail panel surfaces externally mounted to control the guidance of the missile in flight, servo motor control means coupled to the tail panel surfaces to control the angular position thereof, and control circuitry for operating the servo motor means, the improvement comprising:
- a continuously burning thrust reaction motor mounted in each tail panel surface to provide a reaction force along the surface with a component of thrust generally transverse to the flight axis of the missile.
Dependencies are inferred from the claim text.