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A special subscale, pintle-mounted gas generator was developed by the Army Advanced Ballistic Missile Defense Agency. It was used to comparatively evaluate the thrust vector control systems which might be used in conjunction with pintle-controlled interceptor motors. The two thrust vector control systems which have been evaluated to date are: the Gimballed, Supersonic Splitline Thrust Vector Control System and the Techroll Movable Nozzle Thrust Vector Control System. These evaluations were carried out under simulated altitude conditions with the gas generator operating in a boost and a sustain mode as part of the duty cycle. This paper will discuss the design of this Thrust Vector Control Gas Generator, motor fabrication, its multiple ignition system, the thrust vector control systems, test objectives, test procedures, and test results.

The development of a motor combining a pintle-controlled nozzle with gimbaled supersonic splitline thrust vector control (TVC) was undertaken in an effort to exploit the increased performance flexibility of a rocket system which is offered by thrust magnitude and thrust vector control. That is, the ability to perform widely different duty cycles, maneuvers, or fly different trajectories. The major objective is to demonstrate the effectiveness of a controllable solid-propelled rocket motor which features variable thrust, attitude control, and high propulsion efficiency. To date, three half-duration motors have been static-fired, two at sea level and one which contained a thrust vector control system at simulated altitude. Although each of these preliminary tests experienced some difficulty, several of the major design objectives were successfully demonstrated.