The Boeing Company

Mcdonnell Douglas Corporation

Other

John K Foster

Thaddeus M Jakubowski, Jr

Ryan Binkholder

Cory Gordon Keller

Cameron D Brown

Daniel S Rymarz

Gary T Johnson

Thaddeus M Jakubowski

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

A cooking pot support assembly includes a support rack that has a grapple portion and a support portion. The grapple portion is positionable to engage a front edge of a sink having the support portion angling downwardly into the sink. The support portion has a cooking pot positioned thereon to support the cooking pot at an angle. In this way the support portion assists with pouring liquid from the cooking pot into the sink. A support is rotatably coupled to the support rack. The support is positionable in a deployed position to extend into the sink. The support includes a stop portion extending upwardly from the support rack to inhibit the cooking pot from sliding along the support rack into the sink.

Cooking pot support assembly

A store ejector rack including a first hook member and a second hook member, a split sleeve guide member, and a pair of split sleeve members, including a first split sleeve member and a second split sleeve member, operatively coupled to the split sleeve guide member. The first split sleeve member is coupled to the first hook member and the second split sleeve member is coupled to the second hook member. A valve control assembly is operatively coupled to the split sleeve guide member, wherein actuation of the split sleeve guide member causes actuation of the first hook member, the second hook member, and the valve control assembly.

Store ejection system and method of discharging a store from a vehicle

A multiple advanced missile and bomb ejector rack carriage system employs a carriage mountable to an air to ground (AG) bomb release unit (BRU) on an aircraft pylon. A single MIL-STD-1760 electrical interface is integral to the carriage and has a first power connection and first signal connection. Onboard carriage avionics are supported within the carriage and connected to the MIL-STD-1760 electrical interface. The onboard carriage avionics are adapted to receive communications from an aircraft central computer through the first power connection and first signal connection and provide store specific communications independent of specific original aircraft wiring to at least one ejector and store.

Multiple missile and bomb carriage system

An insect trapping device traps, kills and facilitates disposal of an insect. The device includes a handle which is hollow defining a conduit extending between a first end and a second end. A fan coupled to the handle in the conduit such that the fan provides suction into the first end of the handle. A cup is coupled to the first end of the handle for directing an insect into the first end of the handle. A receptacle is coupled to the second end of the handle and vented end such that the fan urges air flow out through the receptacle wherein the receptacle receives and holds the insect sucked through the first end of the handle.

Insect trapping device

In one embodiment there is provided a radar signature and induced aerodynamic drag minimizing, externally mountable, internally configurable pod structure optimized for internal placement of one or more deployable stores through configuration and optimal kinematic operation of a pod door assembly. The pod structure has an externally mountable pod housing, a predetermined pod housing cross-sectional configuration optimized to provide a configurable interior volume accommodating multiple different store configurations, and a predetermined pod housing configuration having a cross-sectional configuration optimized to minimize a radar signature and an induced aerodynamic drag. The pod structure further has a pod door assembly integral with the pod housing and having a plurality of pod doors and one or more seal door mechanism assemblies. The pod structure is optimized in kinematic operational combination of the pod doors and seal door mechanism assemblies controlling ejection launch envelopes.

Configurable pod structure and store stowage and deployment system and method

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 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 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

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

St. Peters, MO, United States of America

John K Foster