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: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.