Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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. 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 forward link is further coupled to the second forward joint, and the aft link is further coupled to the second aft joint.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: There is provided a store ejection system, store, and method for mounting a jettisonable store on an aircraft. The system uses a pressurized non-pyrotechnic fluid from a pressure vessel integral to the store and sealed by a releasable seal as the source of energy and the transfer mechanism. An actuation system includes an accumulator for receiving and storing the fluid from the pressure vessel, a dump valve for controlling a flow of the fluid from the accumulator, and a controller for actuating the dump valve to an open position in response to a control signal to jettison the store. The seal is configured to hermetically seal the pressure vessel before the actuation system is connected to the pressure vessel, and the actuation system is configured to be fluidly connected to the pressure vessel upon release of the releasable seal.

Abstract: An automatic and sequencing pneumatic actuation assembly is provided for use in an ejection system capable of unlocking and forcibly ejecting stores from racks mounted on an aircraft or similar weapon carrier. The actuation assembly including a primary valve and release ram for reciprocating movement along a common longitudinal axis between closed and open positions. A solenoid control valve initiates movement of the primary valve by creating a pressure imbalance across the primary valve. Pressurized gas is caused to vent to an environment having a pressure lower than the pressurized gas, allowing the primary valve to move the release ram into engagement with a mechanism capable of unlocking the hooks before moving ejector pistons to forcibly eject the unlocked stores. A bias member is provided for automatically returning the primary valve to the closed position after the stores have been released.

Abstract: An adaptor for releasably attaching a store to a rack on the underside of an aircraft. The rack has at least one hook connected to the rack and pivotable between a closed position for retaining the store on the rack and an open position for installation of the store on the rack and release of the store from the aircraft. The adaptor has a generally continuous lower surface shaped to conform to the outer surface of the store, an upper surface, and a surrounding wall connecting the upper and lower surfaces. The upper surface has a post extending downwardly from the rack for stabilizing the store against longitudinal and lateral movement of the store relative to the rack due to air loads during flight. The surrounding wall has a least one recess formed therein for receiving the hook. The adaptor is shaped so that upon release of the store, aerodynamic drag resulting from the presence of the adaptor on the store is minimized.

Abstract: The stores ejection system and method of the present invention provide automatic pre-load device, such as a pneumatically-operated pre-load piston, to pre-load a store ejection ram into contact with a bomb or other store prior to store ejection. Mechanical shock to the store during ejection is thereby minimized. The ejection system automatically retracts following store ejection to minimize ejection system aerodynamic drag during flight.

Abstract: An actuator assembly that has a constant net pressure area telescoping piston. The actuator assembly has a cylindrical housing; nesting, telescoping pistons; a central plug; an outer cap; and a vent. The cylindrical housing has an interior surface and a base that terminates at an open end. The nesting, telescoping pistons are located in the housing and can extend past the housing open end. The telescoping pistons have an outer piston slidably sealed against the housing and an inner piston that is slidably sealed against the outer piston. The outer piston has a first end proximal to the housing base, and a second end distal to the housing base. The inner piston has an open end proximal to the housing base, and a closed end distal to the housing base. The central plug extends from the base and into the telescoping pistons. The central plug is in pressurized communication with the inner piston and is engagable with a pressurized fluid source. The outer cap has a first and a second member.

Abstract: The stores ejection system of the present invention includes a single release hook and swaybraced ejection rams for releasably mounting and forcibly ejecting miniature munitions and other miniature stores on an aircraft. The pneumatically-driven stores ejection system can accommodate miniature stores having bail lugs sized to reduce store aerodynamic drag and radar signature and to improve store delivery accuracy.

Abstract: A variable flow-restricting and apportioning device for an aircraft ejector rack system having a pair of fluid-actuated thrusters includes a pair of rotatable feed conduits for supplying pressurized fluid to the thrusters. Each feed conduit has an exit flow passage at its exit end which is eccentric relative to the longitudinal axis about which the conduit is rotatable, and the exit end of each feed conduit slidably fits into a female receptacle in a receiver in fluid communication with one of the thrusters. Each receptacle includes a mating face therein which has a receiver port for supplying fluid to the respective thruster. The receiver port is eccentric relative to the rotational axis of the feed conduit. Rotating each feed conduit relative to the respective receiver causes varying degree of overlap between the eccentric exit flow passages and the eccentric receiver ports, thereby defining variable-size flow orifices at each receiver.