Jet tab control mechanism for thrust vector control
AssigneeGeneral Dynamics, Pomona Division
InventorThomas W. Bastian
Life of this patent
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Abstract
A missile jet tab actuator system for a thrust vector control coupled to aerodynamic controlled surfaces is disclosed. The device removes roll information present in commands to the aerodynamic surfaces. Only pitch and yaw information is thus supplied to the thrust vector control jet tabs. In this disclosure, the roll information is removed by a gear and slotted sleeve system. The resulting pitch and yaw output is used to drive the thrust vector control jet tabs. No separate set of independently powered actuators for such tabs is required.
Claims9
A thrust vector control system for a missile comprising:
- a cylindrical missile body;
- rocket propulsion means acting along the axis of the body to propel the missile;
- a plurality of fins pivotably mounted external to the body, each being pivotable about an axis normal to the cylindrical surface of the missile body for aerodynamically controlling direction of the missile in flight;
- a servo motor associated with each fin for controlling the angular position of the fin relative to the missile body;
- control circuitry for commanding the servo motors to control the pivoting of the fins;
- a plurality of thrust vector control jet tabs effective to provide pitch and yaw moments by deflecting rocket exhaust gas;
- a coupler effective to transmit fin servo motor commands to the thrust vector control jet tabs;
- and
- actuator means coupled to said coupler and the tabs and containing means to rotate the thrust vector control jet tabs in response to pitch or yaw servo motor commands.
A thrust vector control system for a missile comprising:
- a cylindrical missile body;
- rocket propulsion means acting along the axis of the body to propel the missile;
- a plurality of fins pivotably mounted external to the body, each being pivotable about an axis normal to the cylindrical surface of the missile body for aerodynamically controlling direction of the missile in flight;
- a servo motor associated with each fin for controlling the angular position of the fin relative to the missile body;
- control circuitry for commanding the servo motors to control the pivot angle of the fins;
- a plurality of thrust vector control jet tabs capable of providing thrust moments by deflecting rocket exhaust gas;
- drive means for said thrust vector control jet tabs including:
- a first pair of geared rings, each ring being rotatable in response to commands provided to one of said fins;
- a second pair of geared rings, each of said second rings being mated to one of said first pair of rings;
- first pin means protruding from the inner surface of each of said second pair of rings;
- a first hollow cylinder having guide slots cut in the outer surface thereof, each slot being engaged by one of said first pin means, said first cylinder being rotatable and axially movable within said second pair of rings in response to motion of said pin means, axial motion of said first cylinder being in response to pitch or yaw servo commands and rotation of said first cylinder being in response to roll servo commands;
- a second hollow cylinder concentric to and within said first cylinder and axially movable therewith;
- means for preventing rotation of said second cylinder;
- second pins means protruding from the inner surface of said second cylinder;
- and
- a rotatable thrust vector control tab shaft coaxial with second cylinder and connected to a thrust vector control tab, said tab shaft having a profiled slot in the surface thereof mated to the second pin means, whereby axial motion of said second cylinder causes the thrust vector control shaft to rotate.
Dependencies are inferred from the claim text.