Raytheon Company

Jeffrey P Sowers

Matthew B Castor

Christopher P Owan

Charles M De Lair

Derek L Budisalich

John Fawcett Roden Bugge

Matthew P Francis

A control actuation system for an air-breathing rocket motor propelled guided missile positions the drive motors and input gears in an inlet fairing extending aft of the air inlet towards the tail of the missile. The output gears are positioned coincident with and mechanically coupled to their respective tail fins spaced around the circumference of the missile. At least one of the tail fins is offset in a circumferential direction of the missile from its corresponding input gear and the inlet fairing. At least one ring gear is positioned around the exhaust tube to rotate in the circumferential direction of the missile. The ring gear comprises input and output teeth that engage the input and output gears, respectively, to actuate the tail fin.

Ring gear control actuation system for air-breathing rocket motors

The disclosed system, device and method for deploying a sub-module from a carrier vehicle generally includes: a sub-module projectile () housed within a carrier vehicle; a rolling diaphragm () sealed between a first pressure chamber volume () and a second sub-module containment volume (e.g., substantially formed on the opposing side of rolling diaphragmrelative to pressure chamber); and a release mechanism (), wherein the sub-module projectile () is secured until releasable deployment from the carrier vehicle. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve ejection, deployment and/or dispersal of a variety of sub-modules from a variety of carrier modules. Exemplary embodiments of the present invention generally provide for the ejection and dispersal of kinetic energy rod warheads from a kill-vehicle.

Lightweight deployment system and method

Growing community of inventors

Orlando, FL, United States of America

Jeffrey P Sowers