# US 12,110,108 B2 · Systems and methods for ejecting a store from an aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,110,108 B2 - Document ID: US12110108B2 - Status: Granted - Kind: B2 - Application number: 17/654,251 - Filed: 2022-03-10 - Published: 2023-01-05 - Granted: 2024-10-08 - Earliest claimed: 2021-06-30 - Assignees: The Boeing Company - Applicants: The Boeing Company - Inventors: John K. Foster; Ryan Binkholder; Thaddeus Jakubowski, Jr. - Web page: https://patentgrep.com/patent/US12110108B2 ## CPC - B64D 1/04: the articles being explosive, e.g. bombs - B64D 1/06: Bomb releasing; Bomb doors - B64C 30/00: Supersonic type aircraft - B64D 7/08: Arrangement of rocket launchers - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - B64C: AEROPLANES; HELICOPTERS ## 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. ## Claims ### Claim 1 A system for ejecting a store from an aircraft, the system comprising: a stowage tube configured to retain the store, wherein the stowage tube includes an open rear end; a door panel coupled to the stowage tube, wherein the stowage tube is mounted on the door panel; an actuator driven linkage coupled to the door panel, wherein 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, and wherein the stowage tube is configured to rearwardly eject the store out of the open rear end when the system is in the deployed position; and an ejector valve in fluid communication with a chamber having a piston, wherein the ejector valve comprises a poppet valve. ### Claim 2 (depends on 1) The system of claim 1, further comprising an ejector valve in fluid communication with a chamber having a piston, wherein the piston is configured to engage the store, and wherein the ejector valve provides pressurized fluid to move the piston to eject the store when the system is in the deployed position. ### Claim 3 (depends on 2) The system of claim 2, wherein the piston is configured to travel over a stroke of at least twenty four inches. ### Claim 4 (depends on 2) The system of claim 2, wherein the ejector valve comprises a regulating orifice sized to controllably regulate flow of the pressurized fluid to cause an applied force to the piston to increase with stroke, wherein the piston is configured to impart an end-of-stroke velocity to the store. ### Claim 5 A system for ejecting a store from an aircraft, the system comprising: a stowage tube configured to retain the store, wherein the stowage tube includes an open rear end; a door panel coupled to the stowage tube; an actuator driven linkage coupled to the door panel, wherein 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, and wherein the stowage tube is configured to rearwardly eject the store out of the open rear end when the system is in the deployed position, an ejector valve in fluid communication with a chamber having a piston, wherein the piston is configured to engage the store, and wherein the ejector valve provides pressurized fluid to move the piston to eject the store when the system is in the deployed position, wherein the ejector valve comprises: a poppet valve; and a regulating orifice sized to controllably regulate flow of the pressurized fluid to cause an applied force to the piston to increase with stroke, wherein the piston is configured to impart an end-of-stroke velocity to the store. ### Claim 6 (depends on 5) The system of claim 5, wherein a lower surface of the door panel is flush with an outer mold line of the aircraft when the system is in the stowed position. ### Claim 7 (depends on 5) The system of claim 5, wherein the aircraft is a hypersonic aircraft. ### Claim 8 (depends on 5) The system of claim 5, wherein the store is a munition. ### Claim 9 (depends on 5) The system of claim 5, further comprising a latch configured to retain the door panel in the closed position. ### Claim 10 (depends on 5) The system of claim 5, wherein the actuator driven linkage comprises an actuator operably coupled to a lower link arm and an upper link arm. ### Claim 11 (depends on 5) The system of claim 5, wherein the pivot axis is defined by a hinge proximate to the forward edge of the door panel. ### Claim 12 (depends on 5) The system of claim 5, wherein the pivot axis is perpendicular to a longitudinal axis of the aircraft. ### Claim 13 A method for ejecting a store from an aircraft, the method comprising: retaining a store within a stowage tube having an open rear end, wherein the stowage tube is mounted on a door panel; rotating the door panel, by an actuator driven linkage coupled to 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; engaging the store with a piston disposed within a chamber that is in communication with an ejector valve having a poppet valve; and rearwardly ejecting the store out of the open rear end when the system is in the deployed position. ### Claim 14 (depends on 13) The method of claim 13, further comprising providing, by the ejector valve, pressurized fluid to move the piston to eject the store when the system is in the deployed position. ### Claim 15 (depends on 13) The method of claim 13, wherein a lower surface of the door panel is flush with an outer mold line of the aircraft when the system is in the stowed position. ### Claim 16 (depends on 13) The method of claim 13, further comprising retaining, by a latch, the door panel in the closed position. ### Claim 17 (depends on 13) The method of claim 13, wherein the pivot axis is perpendicular to a longitudinal axis of the aircraft. ### Claim 18 An aircraft comprising: a system for ejecting a store, the system comprising: a stowage tube configured to retain the store, wherein the stowage tube includes an open rear end; a door panel coupled to the stowage tube, wherein the stowage tube is mounted on the door panel; an actuator driven linkage coupled to the door panel, wherein 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, wherein the pivot axis is perpendicular to a longitudinal axis of the aircraft, and wherein the stowage tube is configured to rearwardly eject the store out of the open rear end when the system is in the deployed position; and an ejector valve in fluid communication with a chamber having a piston, wherein the piston is configured to engage the store, and wherein the ejector valve provides pressurized fluid to move the piston to eject the store when the system is in the deployed position, and wherein the ejector valve comprises a poppet valve. ### Claim 19 (depends on 18) The aircraft of claim 18, wherein a lower surface of the door panel is flush with an outer mold line of the aircraft when the system is in the stowed position. ### Claim 20 (depends on 18) The aircraft of claim 18, wherein the aircraft is a hypersonic aircraft.