Abstract: Provided in a compact system is a rapid response h-q-T sensor assembly, with associated processor and holding device, for measuring temperature, T, and heat flux, q, in a severe operating environment. From measured temperatures, T, and heat flux, q, a stagnation point recovery temperature, Tr, and a heat transfer coefficient, h, may be calculated using approximation algorithms loaded in the processor. The system approximates the ideal conditions in which Tr is derived from measuring a high temperature, i.e., a zero heat flux path to ground, i.e., q=0, r=∞ and a lower wall temperature measured along an infinite heat flux path, i.e, q=∞, r=0. Although ideal conditions are not able to be duplicated, appropriate positioning of heat flux indicators and temperature indicators in the surface of a thin film on the q-h-T sensor assembly, while allowing for very short duration sampling in a hostile environment, permits a viable approximation.

Abstract: An aerodynamic fin and stowable jet vane system preferably for rocket motor issile applications to control roll, pitch, and yaw, in either the aerodynamic or thrust flight control conditions, has a retractable and stowable aerodynamic vane integrated with a stowable thrust vector reaction steering system on a common support. The integrated aerodynamic fins and thrust vector control reduce the overall missile mainframe dimensions and are mounted on a single, space saving support.

Abstract: An integrated roll control and power supply system for a missile includes a pair of flywheel-motor-generator (FMG) units, a pair of power flow control (PFC) units coupled between the FMG units and a missile load, and a roll sensor coupled to the PFC units. The integrated system also includes a pair of resistance heaters and a pair of clutch-brake devices. The FMG units are axially aligned and displaced from one another. One FMG unit operates in a counterclockwise direction, while the other FMG unit operates in a clockwise direction. The two FMG units produce the bi-directional roll torque characteristic necessary to develop roll-dampening torques for the missile system roll control autopilot.

Abstract: A thrust vector control apparatus for selective deployment of a vane within n exhaust stream has the vane mounted on the periphery of an exhaust nozzle for pivotable movement between a retracted position without the stream and an inserted position within the stream. A pivotally mounted link assembly is used with an actuator to urge the vane into the stream. The link assembly becomes locked in place upon the full insertion of the vane. This locked position precludes unintended pivotal motion of the vane; however, rotational motion of the vane is still possible due to the pivotal connection of the link. A second actuator rotates the vane in the stream, thereby controlling the direction of the stream.