USA As Represented by Secretary of the Navy

Other

Arnold O Danielson

Robert B Dillinger

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, T , and a heat transfer coefficient, h, may be calculated using approximation algorithms loaded in the processor. The system approximates the ideal conditions in which T is derived from measuring a high temperature, i.e., a zero heat flux path to ground, i.e., q&equals;0, r&equals;&infin; and a lower wall temperature measured along an infinite heat flux path, i.e, q&equals;&infin;, r&equals;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. Using a pair of algorithms, the measured values of temperature, T, and heat flux, q, and calibrating a value of thermal resistance, data are processed in situ to yield derived values for the worst case heat transfer coefficient, h, and the stagnation recovery temperature, T .

Rapid response h-q-T sensor

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.

Integrated aerodynamic fin and stowable TVC vane system

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. The PFC units receive roll attitude, rate and acceleration input signals from the roll sensor and, in response to such signals, are operable at three different levels of roll damping to dissipate power flow from the FMG units to supply electrical components of the missile and to operate resistance heaters and clutch/brake devices to develop appropriately balanced roll torques in the missile airframe.

Integrated roll control and power supply system and method

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.

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Inyokern, CA, United States of America

Arnold O Danielson