The Boeing Company

Mcdonnell Douglas Corporation

Theboeing Company

Thaddeus M Jakubowski, Jr

John K Foster

Cory Gordon Keller

Ryan Binkholder

James Vincent Eveker

Aaron Ross Cowin

Norman F Robinson

Daniel S Rymarz

Gregory M Sisti

Todd J Palmer

Samuel Jerome Huhman

Cameron D Brown

Richard Raymond Kreutzman, Jr

Gary T Johnson

Nelson O Weber

Daniel DiDomenico

Keith A Coleman

Herman R Kietzman, Jr

Mike Heller

Jess W Lockhart

Daryl D Carpenter

David Michael Paruleski

Steven Michael Schoen

A propulsionless munition configured to be launched from a hypersonic aerial includes a munition body that is free of any propulsion system for producing thrust. The munition body includes a forward section including a radome assembly and an aft section including a control system. The radome assembly includes a nose radome and a frangible radome cover disposed over the nose radome for shielding the nose radome from high temperatures resulting from aerodynamic heating at hypersonic speeds. The frangible radome cover is detachable from the nose radome upon detection by the control system of a predetermined threshold comprising at least one of a predetermined speed, a predetermined altitude, and a predetermined temperature.

Propulsionless hypersonic dual role munition

A system and method for ejecting a store from an aircraft include a stowage tube configured to retain the store. The stowage tube includes an open rear end. A door panel is coupled to the stowage tube. An actuator driven linkage is coupled to the door panel. The actuator driven linkage is configured to rotate the door panel about a pivot axis at a forward edge opposite from an aft end between a closed position associated with a stowed position of the system and an open position associated with a deployed position of the system. The stowage tube is configured to rearwardly eject the store out of the open rear end when the system is in the deployed position.

Systems and methods for ejecting a store from an aircraft

A hinge assembly of a system for operating a door of an aircraft includes a bracket secured to a structure of the aircraft. The bracket includes a first forward joint and a first aft joint separated by a first distance along a first line. A forward link is coupled to the first forward joint. An aft link is longer than the forward link, and is coupled to the first aft joint. A door coupler is secured to a door. The door coupler includes a second forward joint and a second aft joint separated by a second distance that is less than the first distance. The second distance is along a second line that is parallel to the first line in a stowed position. The forward link is further coupled to the second forward joint, and the aft link is further coupled to the second aft joint.

Systems and methods for operating a door of an aircraft

Container retention and release apparatus are disclosed. An example container retention and release apparatus includes a swaybrace to engage an exterior surface of a container. A latch is to attach to an internal receptacle of the container to retain the container. The latch is movable between a latched position to retain the container and an unlatched position to release the container. A drive is to move the latch between the latched position and the unlatched position.

Container retention and release apparatus for use with aircraft

A cover for an empty rail missile launcher that can be used in flight. The cover is shaped to reflect radar signals transmitted by a radar transmitter away from the radar transmitter to reduce detectibility by radar. The cover may also be coated with radar absorbent material to reduce detectibility by radar. Hangers are used to mount the cover to the rail missile launcher. The cover is provided with a grounding mechanism to dissipate precipitation static. A restraint mechanism is provided to prevent the cover from inadvertently sliding off the rail missile launcher.

Aircraft missile launcher cover

A store ejector is adapted for in-flight adjustment of the pitch attitude imparted to a store by a pair of ejector pistons. The pitch attitude of the store is adjustable to correspond to a flight condition of the aircraft at time of store release. The aircraft has a flight computer that provides store release pitch data corresponding to the aircraft flight conditions. The store ejector includes an orificing assembly that varies the flow of pressurized gas to the ejector pistons by translating a mandrel within a bore formed in the orificing assembly. Orifices within the bore are adjusted to apportion the flow of pressurized gas to the ejector pistons in accordance with an optimum orifice setting corresponding to the desired pitch attitude of the store for the given flight condition.

System and method for in-flight adjustment of store ejector gas flow orificing

A store ejection system that can be 'blind-loaded' without the need to have physical access to the ejector rack. This invention provides the ability to carry certain unique weapon shapes that can not be carried on current ejector racks due to the lack of access to the rack once the weapon is raised into position.

Store ejector rack

Store ejector rack systems and methods having an improved fluid actuator assembly for sequencing the opening of the hooks from which the store is suspended and the pressurization of thrusters which force the store away from the aircraft are disclosed. In one embodiment, an actuator assembly includes a staged valve assembly including a primary valve for controlling the flow of high pressure fluid from an accumulator to the thrusters, and a slave piston independently movable with respect to the primary valve for actuating the hook release mechanism.

Aircraft store ejector rack systems and methods

A pneumatically operated stores ejector rack for an aircraft having an adjustable flow restricting device for variably apportioning the flow of pressurized gas from a manifold to the store ejection thrusters. The flow restricting device includes at least one adjustable valve assembly, having a valve and a valve body, for varying the pressure of gas supplied to the thruster. It also includes a feed conduit connecting the manifold and the valve, and a collar threadably engageable with the manifold and the feed conduit for urging the valve into contact valve body. Also disclosed is a method for apportioning the flow of pressurized gas between a pair of thrusters in a stores ejection rack which includes the flow restricting device.

Variable flow restricting devices

There is provided a store ejection system and method that use a pressurized non-pyrotechnic gas as the source of energy and transfer mechanism for jettisoning a store, such as from an aircraft. The ejection system includes an on-board pressure vessel for holding the pressurized gas with a releasable valve configured to hermetically seal the pressure vessel. The pressure vessel is releasably connected to system and the releasable valve is configured to be released after the pressure vessel is connected thereto so that the releasable seal hermetically seals the pressure vessel before the pressure vessel is connected to the pressure regulator. The ejection system also includes at least one actuation system and at least one pneumatically-driven jettison mechanism for releasably retaining the store.

Store ejection system with disposable pressure vessel and associated method of operation

There is provided a store ejection system and method for mounting and ejecting a jettisonable store. The system uses a pressurized non-pyrotechnic fluid from a fluid source as the source of energy and the transfer mechanism. An actuation system includes an accumulator for receiving and storing the fluid from the pressure source, a poppet valve for controlling a flow of the fluid from the accumulator, and a controller for actuating the poppet valve to an open position in response to a control signal to jettison the store. A pneumatically-driven jettison mechanism for releasably retaining the store is fluidly connected to the poppet valve such that actuating the poppet valve to the open position releases the pressurized fluid in the accumulator to flow to the jettison mechanism, thereby actuating the jettison mechanism to jettison the store. An isolation valve, which is configured to selectively provide gas to the accumulator, can be operatively coupled to an adjustable member of the actuation system or the jettison mechanism so that the isolation valve can be closed when the poppet valve is actuated to the open position, thereby preventing further flow of the fluid from the fluid source.

Store ejection system with integral isolation valve and associated ejection method

A device for locating a person has a housing with an interior and an opening into the interior. The device also has a locator balloon stored the housing interior which is deployable from the housing through the housing opening when the device is actuated. The balloon is stored in a nesting arrangement with a portion of the housing with the balloon being collapsed around the housing portion and substantially conforming therewith. The balloon is deployed in a manner such that the balloon passes over the housing portion as the balloon expands out of through the housing opening and inflates with the housing attached to the balloon. The device also has a source of gas that is lighter than air positioned within an interior of balloon. The gas source is released to expand and inflate the balloon when the device is actuated.

Man overboard locator device

A stores ejection system for retaining stores on the underside of an aircraft and forcibly jettisoning the stores away from the aircraft is disclosed. The ejection system includes a plurality of ejector mechanisms for releasably holding and jettisoning the stores away from the aircraft, a plurality of storage devices for storing pressurized gas to actuate the ejector mechanisms, and a central control system for maintaining the pressure of the gas, and actuating the release of the gas. The central control system monitors the pressure of the storage devices and heats only those storage devices that have a pressure below the operating pressure.

Method and apparatus for providing pneumatic energy to an ejector

Snap rings positioned in grooves on shaft members and the like for retaining component members on the shaft members. Retention members, such as retaining rings with counterbores, are positioned over the snap rings and prevent the snap rings from expanding outwardly and being released from the grooves. The retention members are installed such that axial loads force the retention members against the snap rings. The snap rings are preferably spiral snap rings.

Snap ring retention system

There is provided a store ejection system and method that use a pressurized non-pyrotechnic gas as the source of energy and transfer mechanism for jettisoning a store from an aircraft. The ejection system includes an on-board pressure vessel for holding the pressurized gas, a releasable seal configured to hermetically seal the pressure vessel, and a pressure regulator fluidly connected to the releasable seal and configured to control a flow of the gas from the pressure vessel when the releasable seal is configured in an open position. The pressure vessel is releasably connected to the pressure regulator and the releasable seal is configured to be released after the pressure vessel is connected to the pressure regulator so that the releasable seal hermetically seals the pressure vessel before the pressure vessel is connected to the pressure regulator. The ejection system also includes at least one actuation system and at least one pneumatically-driven jettison mechanism for releasably retaining the store.

Growing community of inventors

Saint Charles, MO, United States of America

Thaddeus M Jakubowski, Jr