Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1982-04-22
1986-04-01
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
23926535, F41G 700, F02K 140
Patent
active
045792992
ABSTRACT:
The thrust control system has two rotatable joints, a blast tube joint connected to the rocket motor blast tube with 360 degrees continuous-rotation about the motor axis in either direction, and a nozzle joint joined to the blast tube joint with a 90 degree movement in either direction to the motor. Each joint is actuated by an independent servoactuator that gives independent and concurrent turning. The thrust vector of the system in any direction is substantially equal to the total motor thrust. The resultant side force of the nozzle when vectored in any position passes through the motor axis whereby induced roll moment is not developed.
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Johnson Wendell O.
Lavery Joseph R.
Jordan Charles T.
Morton Thiokol Inc.
White Gerald K.
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