Thiokol Corporation

Utah State University

Alliant Techsystems Inc.

Morton Thiokol Inc.

Steven R Wassom

Morgan E Davidson

Lawrence C Faupell

Thomas K Highsmith

Robert B Smalley, Jr

Michael D Blair

Girard H Rapp

Joel Dever

Joseph J Kliger

William D Starrett

A method and apparatus for determining the longitudinal position of a tapered displaceable element positioned between two substantially orthogonally laterally opposing displacement sensors. A change in the longitudinal position of the displaceable element causes the sensors to each measure their distance to the displaceable element which relates directly to the local thickness and thus the longitudinal position of the displaceable element. The system factors out errors in measured lateral proximity position of the displaceable element since an erroneous proximity to one sensor is equal and opposite to an erroneous proximity to the other.

Optics positioning sensor system

A system for determining the longitudinal position of a displaceable element positioned between two substantially orthogonally laterally opposing displacement sensors measures a distance from each displacement sensor to the displaceable element. The displaceable element has a tapered thickness along its length. A change in the longitudinal position of the displaceable element causes the proximity sensors to each detect their distance to the displaceable element, which distances then correspond directly to the local thickness and thus the longitudinal position of the displaceable element. The system calculates the position of the displaceable element. The system can easily factor out errors in measured lateral proximity position of the displaceable element, since an erroneous proximity to one sensor is equal and opposite to an erroneous proximity to the other.

Proximity-leveraging, transverse displacement sensor apparatus and method

A method and device for producing a controlled combustion by placing a combustion chamber in communication with a feed chamber that contains a solid propellant/body, introducing at least a portion of the body into the combustion chamber, isolating the combustion chamber from the feed chamber, and igniting the solid propellant in the combustion chamber while the combustion chamber is isolated from the feed chamber.

Digital solid rocket motor and gas generator

A system for providing pitch, yaw, and roll control during the flight of a rocket-propelled vehicle combines a vectorable nozzle with jet vanes. The vectorable nozzle provides yaw and pitch control, while the jet vanes provide roll control. Anti-rotation pins extend from the vehicle housing into longitudinal slots within the vectorable nozzle to allow vectoring movements and prevent rotation of the nozzle. The jet vanes are rotatably mounted on shafts within the nozzle exit cone to receive and guide combustion products passing through the nozzle. The jet vanes may be jettisoned after an initial high-angle-of-attack maneuver is completed and the vehicle gains speed, after which roll control is provided by aerodynamic fins. The jet vanes may also be formed of material which erodes after the initial maneuver, thereby reducing the loss of thrust caused by the jet vanes.

Vectorable nozzle having jet vanes

A control system for use in missiles and other projectiles which provides pitch, yaw and roll control. The control system includes two opposing pairs of flaps configured in the aft end of the missile case. Each flap is attached for rotation about its leading edge. Prior to actuation, the flaps conform to the exterior surface of the missile. Upon actuation, the flaps extend into the airstream to induce aerodynamic forces. The axis of rotation of each flap is positioned at an oblique angle to the radial plane of the missile.

Finless aerodynamic control system

A tactical pulsed missile with a movable nozzle for thrust vector control and movable aerofins to provide greater maneuverability and flexibility. The first pulse is fired at launch and the later pulses are fired as needed whereby steerage may be provided by thrust vector control during the firing of the pulses. When none of the pulses are firing, steerage may be provided by the movable aerofins. The missile is provided with separate small electromechanical actuators for each of the aerofins and each of the movable nozzle axes which are preferably placed closely adjacent the respective aerofins and nozzle so that the weight and space of various linkages may be eliminated. The motors are provided with a source of high voltage so that their size may be reduced whereby they burn up when the high voltage is applied for a short period of time but not before their task has been achieved. The fin span is reduced to less than about four inches to enable the packaging of a greater number of such tactical missiles in the payload bay of an airplane. A flexible bearing may be provided between the nozzle and nozzle housing. An elastomeric material may be provided between and bonded to the nozzle and nozzle housing to prevent the ingestion of exhaust and debris into the space therebetween.

Growing community of inventors

Smithfield, UT, United States of America

Steven R Wassom