Raytheon Company

Huck International, Inc.

Robert D Travis

Andrew B Facciano

Daniel D Reimann

Charles M Hoke

Michael S Alkema

James A Ebel

Dale O Widmer

Jeffrey R Richards

Jeffery R Richards

Mike J Saxton

Sandie Y Worley

Dana McWilliams

Justin Powell

A frangible detent pin comprising a base a pin head and an elastic member. The base is configured to be secured within a bore. The pin head and the base are interconnected through a frangible connection. The elastic member is configured to bias the pin head away from the base. The frangible detent pin has a rigid stage in which the pin head is rigidly positioned relative to the base and a spring-loaded stage in which the pin head is moveable relative to the base under a compression load between pin head and the base. The frangible detent pin is configured to transition from the rigid stage to the spring-loaded stage in response to the compression load exceeding a predetermined threshold sufficient to cause the frangible connection to fail.

Frangible detent pin

A deployment system, such as for deploying wings, includes a pair of hub assemblies that transmit linear motion provided by an actuator into a combination of rotational and axial motion. The actuator works on both hub assemblies, rotating (for each wing) a slew ring that is coupled to a lift bar that acts as a follower, following a pair of cam slots, to allow the wings to follow their desired course. In one embodiment the wings move axially away from a fuselage at the beginning of the deployment movement, followed by a primarily rotational movement, with the wings pulling in toward the fuselage at the end of the deployment process. The actuator includes a pair of threaded shafts (threaded in opposite directions) that rotate along with a pinion gear, driven by a motor, to translate a pair of retractor links that are coupled to the slew rings.

Single-actuator rotational deployment mechanism for multiple objects

An internally coupleable joint is disclosed. The joint can include a first component and a second component configured to mate with one another in an end-to-end relationship. An axially extending protrusion of the first component can interface with a corresponding recess of the second component. In addition, the first component and the second component can each have an internal coupling feature extending at least partially about an inner circumference of the respective component. The joint can also include a securing member having external coupling features configured to engage the internal coupling features of the first and second components to prevent separation of the first and second components.

Internally coupleable joint

A missile or other flight vehicle has a stage separation mechanism for separating a downstream stage from an upstream portion of the missile. The mechanism includes one or more holes in fluid communication with a cavity between the upstream and downstream portions of the missile. The holes are located downstream of one or more shocks produced by one or more local variations in the outer surface shape of the missile. The one or more local variations in outer surface shapes produce the one or more shocks as the missile is flown at supersonic speeds. These shock(s) produce downstream pressure rises, and these pressure increases are communicated to the cavity by the hole(s). The increased pressure in the cavity provides a mechanism for separating the downstream stage from the upstream portion of the missile, after release of a mechanical coupling between the upstream portion and downstream stage.

Stage separation mechanism and method

A frangible valve is disclosed. The frangible valve can include an outer portion operable to form a pressure boundary for a pressure vessel. The frangible valve can also include an inner portion integrally formed with the outer portion and having a central region and a separation region about a perimeter of the central region proximate the outer portion. The separation region can have a thickness less than a thickness of the central region and can be configured to break at a predetermined fluid pressure inside the pressure vessel to vent pressure from the pressure vessel.

Frangible valve

A toroid pressure vessel includes a toroid body having an inner shell and an outer shell. The toroid body includes a toroid outer perimeter. The outer shell extends along the toroid outer perimeter. A planar exterior face extends along at least a portion of the outer shell and the toroid outer perimeter. A support belt circumscribes the toroid outer perimeter and is coupled along the planar exterior face. The support belt braces and supports the pressure vessel along the toroid outer perimeter against bulging force (and hoop stress) generated by pressurized fluids within the vessel. The support belt facilitates the use of thinner pressure vessel shells and thereby decreases the weight of the pressure vessel while providing a support to the outer shell that substantially prevents deformation of the planar exterior face.

Belted toroid pressure vessel and method for making the same

Projectiles that include a propulsion system and a launch motor which are located on opposing sides of a payload and a method of directing a projectile toward a target are generally described herein. Placing the propulsion system and the launch motor on opposing sides of the payload may provide many potential advantages when designing the projectile. These design advantages may make it easier to create a projectile that includes more propellant and/or payload while still permitting the projectile to be stored within existing containers having a fixed size.

Projectile that includes propulsion system and launch motor on opposing sides of payload and method

Some embodiments pertain to a projectile and method that includes a flight vehicle and a propulsion system attached to the flight vehicle. The propulsion system includes a plurality of motors that propel the projectile. A guidance system is connected to the propulsion system. The guidance system ignites an appropriate number of the motors to adjust the speed of the projectile based on the location of the projectile relative to a desired destination for the flight vehicle. In some embodiments, the flight vehicle is a kinetic warhead. The projectile may be an interceptor that includes a first propulsion stage, a second propulsion stage and a third propulsion stage that includes the third propulsion system. The number of booster motors that will be ignited by the guidance system depends on the speed that the projectile needs to be adjusted to in order to maneuver the projectile to a desired location.

Projectile and method that include speed adjusting guidance and propulsion systems

A gripping washer includes a washer body having first and second rigid support surfaces. A fastener hole extends between the first and second rigid support surfaces. An inner washer perimeter extends around the fastener hole. One or more elastomeric gripping tabs are coupled with the inner washer perimeter. The one or more elastomeric gripping tabs extend inwardly into the fastener hole from the inner washer perimeter. The elastomeric gripping tabs are pliable relative to the first and second rigid support surfaces of the washer body and deform and grip the washer with a fastener passed through the fastener hole. By gripping a fastener with the elastomeric gripping tabs the gripping washer is anchored to the fastener and substantially prevents decoupling of the gripping washer from the fastener prior to installation (e.g., fastening with a work piece). Gripping of the fastener with the gripping washer thereby minimizes foreign object debris.

Gripping washer having one or more deformable gripping tabs and method for reducing foreign object debris

A deployable raceway harness assembly for use with a multi-stage rocket includes a first cable bundle configured to extend across a second stage of a multi-stage rocket from a guidance unit to a first stage of the rocket. The deployable raceway harness assembly includes a deployable raceway cover configured for detachable coupling with the multi-stage rocket. The deployable raceway cover extends over at least the first cable bundle and a second cable bundle. The first cable bundle is fastened to the deployable raceway cover. The second cable bundle is configured to extend from the guidance unit to the second stage and is shorter than the first cable bundle. An in-flight deployment mechanism is configured to detach the deployable raceway cover and the first cable bundle extending across the second stage from the multi-stage rocket in-flight leaving the second cable bundle extending to the second stage in place.

Multi-stage rocket, deployable raceway harness assembly and methods for controlling stages thereof

In an embodiment of methods and apparatus for a control surface restraint and release system comprises a restraint apparatus detachably coupled to the control surface, a guidance rail slidably engaging the restraint apparatus, and a stopping mechanism coupled to the guidance rail and configured to stop a movement of the restraint apparatus.

Methods and apparatus for a control surface restraint and release system

A separation device for separating parts along a seam includes a frangible structure and a pressure tube assembly within the frangible structure. The pressure tube assembly includes a pressure tube which contains an explosive detonation assembly/cord that can be initiated to expand the pressure tube, and break the frangible structure with a shock force. The pressure tube assembly also includes a explosive manifold that is recessed in the frangible structure, not protruding from an outer surface of the frangible structure. The explosive manifold receives the ends of the pressure tube, and includes a detonator for detonating the explosive detonation assembly/cord. The explosive manifold has circular-cross-section fittings for accepting a circular ends of the pressure tube. By not having any part of the pressure tube assembly protrude from the frangible structure, improved performance may be achieved. Having circular fittings also improves the seal between the pressure tube and the explosive manifold.

Expanding tube separation device

Methods and apparatus for an actuator system according to various aspects of the present invention include a housing; a sleeve having a deformable portion; and a mover for applying force to the sleeve. The sleeve, which is sealed to the housing, is configured to reside and move within the housing. The mover applies a force against a portion of the sleeve, causing the deformable portion to deform and move.

Growing community of inventors

Tucson, AZ, United States of America

Robert D Travis