Other

General Dynamics Ordnance and Tactical Systems, Inc.

Versatron, Inc.

General Dynamics Ordinance and Tactical Systems, Inc.

Richard W Schroeder

Allan Alfred Voigt

John Mark Speicher

Che-Ram S Voigt

Michael C May

Craig Perry

A dog repellent system for including in the original construction of, or to be added to an existing vehicle that lacks a protective barrier for operators and passengers, such as bicycles, motorcycles, and the like.

Dog repellent system for cyclists

The present invention provides an apparatus and methods directed to a selectively engageable shaft locking device. In one embodiment, a shaft lock device is presented which enables the testing of the shaft and shaft drive device without engaging the drive mechanism into a fully operational state. Another embodiment provides the ability to return the shaft lock device to a storage state after full engagement. The present invention also provides for methods of testing a selective shaft lock device according to the disclosures contained herein.

Systems and methods for a selectively engageable shaft lock and drive device priority

A fin retention and deployment mechanism that has the advantage of providing for the deployment of aerodynamic control surfaces on command without the need for an additional actuation device or control circuitry separate from the actuator that controls the angle of the fins during flight. The actuator that is already required for operation of the control surfaces after deployment initiates the deployment of the fins, as well. A latch mechanism comprises a retaining member and a lath, which engages the retaining member enabling a biasing mechanism to force the fins from a stowed position to a fully deployed position.

Fin retention and deployment mechanism

A fin cover release and deployment system designed for high G forces of gun-launched missiles. In one embodiment, a pyrotechnic actuator drives actuator arms to first release and eject the fin slot covers, followed by deployment of the fins radially outward to the steering position. Following complete ejection of the covers, the fins are driven outwardly by cam surfaces along the latch arms, followed by a spring and wedge mechanism installed interiorly of the fin steering shaft to lock the fins in the fully deployed state. In another embodiment, a motor and rotating threaded shaft replace the pyrotechnic actuator.

Cover ejection and fin deployment system for a gun-launched projectile

An actuator system for controlling the external fins on a gun-launched projectile to control the flight path of the projectile. These actuator systems include an electric motor having a rotor and output shaft which is driven between travel limits that are less than 180 apart (less than 90 in either direction from a central rest position). Coupling from the motor shaft to the control shaft for the external fins is via a coupling between an eccentric ball on the motor shaft and an eccentric receptacle member on the fin shaft. As the angle of the motor shaft varies, the eccentric ball slides in a slot in the fin coupling member, causing the fin shaft angle to vary correspondingly. In another embodiment, the eccentric ball for controlling the fin shaft angle is mounted on a link arm that is coupled to the motor shaft, thereby permitting the motor to be mounted off the projectile axis and thus accommodating a shortened space in the projectile required for the actuator system and associated power supply.

Gun-launched rolling projectile actuator

In a missile thrust vector control (TVC) system, two yoke plates are used which surround a pair of pivotably-mounted rocket nozzles. The rocket nozzles pass through corresponding elongated slots disposed on each yoke plate, the elongate slots engaging said rocket nozzles and operating to actuate the movement of the rocket nozzles in accordance with command signals issued by the missile autopilot. The actuator yoke plates are mounted for movement in orthogonal directions, and for rotation in unison. The orthogonal movement of the yoke plates effects corresponding movement of the rocket nozzles in the yaw and pitch directions. Simultaneous rotation of the yoke plates produces a relative twisting of the pivotably-mounted rocket nozzles causing thrust angles to deviate from the missile central axis in opposite directions but equal degree, thereby imparting a roll moment to the missile. In this fashion, any combination of movements of the missile during flight is made possible.

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Healdsburg, CA, United States of America

Richard W Schroeder