Abstract: A rocket thrust vector control system including jet tabs and aerodynamic control surfaces is disclosed. The control system removes roll information present in commands to the aerodynamic surfaces and provides only pitch and yaw information to the jet tabs for the thrust vector control. The roll information is removed by a geared summing mechanism. The resulting pitch and yaw output is used to drive the thrust vector control jet tabs. The same powered actuators are used for both the aerodynamic control surfaces and the jet tabs.

Abstract: A servo system wherein a servo motor is continuously controlled in response to a pulse width modulated digital command signal is disclosed. A servo motor having a variable output is controlled in response to a variable amplitude error signal. A pulse code converter converts a pulse code modulated digital command signal to provide a pulse width modulated digital command signal for controlling the variable output of the servo motor. The digital command signal is provided at a predetermined frame rate in response to a frame pulse signal. A feedback transducer and network senses the variable output of the servo motor and provides a variable amplitude feedback signal that is indicative of the variable output. A synchronous pulse forming network converts the variable amplitude feedback signal to a proportional pulse width modulated digital feedback signal. The digital feedback signal is provided at the predetermined frame rate and in synchronization with the digital command signal.

Abstract: This invention relates to a servocontrol system for a weapon such as a missile which is a shoulder-launched, infrared-homing, guided missile which provides frontline troops with effective air defense against low altitude enemy aircraft. The weapon, described herein for purposes of illustration, consists of a missile and launcher combination which can be readily transported and operated within the normal environments associated with ground forces in a combat area. To meet the size, weight, and performance requirements, the missile achieves passive homing guidance by using a space-stabilized, infrared-seeking-head control system to generate guidance signals for a single-channel, variable-incidence wing control system working in conjunction with a rolling airframe.