Raytheon Company

Erik A Fjerstad

George Darryl Budy

Derek L Budisalich

John D Willems, Jr

David J Reyes

Thomas A Black

Robert W Von Mayr

Robert W Vonmayr

By removing the aerodynamic fin forces from the fin lock mechanism, achieved by actuating the fin control system to apply a controlled force that counters the aerodynamic forces acting on the control fins, the system can reduce the transmission of aerodynamic forces onto the fin lock mechanism, which makes the fin lock mechanism easier to unlock with less force. Accordingly, a method for unlocking a fin lock mechanism that releasably holds one or more missile control fins in a locked position, where the control fins are prevented from rotating, includes the steps of (i) applying an alternating positive and negative rotational force to a control fin; (ii) monitoring the position of the control fin during the applying step; and (iii) while the position of the control fin does not exceed a predetermined value, repeating the applying step for a predetermined number of times or for a predetermined period.

Fin buzz system and method for assisting in unlocking a missile fin lock mechanism

A component separation system for separating a load from an external structure according to various aspects of the present invention comprises a sleeve slidingly engaged with the external structure. The sleeve includes an opening and an interior. A locking mechanism, such as a ball or latch, is movably disposed through the sleeve opening between a locked position engaging the external structure and an unlocked position not engaging the external structure. A mover slidingly disposed within the hollow interior of the sleeve controls the movement of the locking mechanism through the opening. Energy excess beyond that required for unlocking the mechanism may provide a thrust to forcibly eject the load from the external structure.

Methods and apparatus for integrated locked thruster mechanism

A mechanical deployment and actuation system may comprise a rotation module, a pinion module, a rack module, and a bevel module. The rotation module may be configured to couple to a housing and rotate about the principal axis of the rotation module relative to the housing. The pinion module may be configured to couple to the rotation module and selectively rotate about the principal axis of the pinion module relative to the rotation module. The rack module may be configured to dynamically couple to the pinion module and translate along the principal axis of the rack module in response to rotation of the pinion module. The bevel module may be configured to couple to the rotation module and selectively rotate the rotation module, wherein rotation of the rotation module rotates about the principal axis of the rotation module, the rack module, and the pinion module.

System and method for deployment and actuation

The disclosed system, device and method for providing a low aspect rack and pinion assembly includes a rack engaged with a ball screw and a pinion. The rack is generally responsive to the rotation of the ball screw and the pinion is generally responsive to the movement of the rack. The separating forces generated by the engagement of the rack and pinion are suitably reacted by one or more stabilizer bearings engaged with the structure of the rack and pinion to prevent the rack and pinion from disengaging while maintaining a low aspect profile.

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Tucson, AZ, United States of America

Erik A Fjerstad