Systems and methods for ejecting a store from an aircraft

Patent metadata

Field	Value
Publication number	US-12110108-B2
Application number	US-202217654251-A
Country	US
Kind code	B2
Filing date	Mar 10, 2022
Priority date	Jun 30, 2021
Publication date	Oct 8, 2024
Grant date	Oct 8, 2024

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.

First claim

What is claimed is:

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.

2. 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.

3. The system of claim 2 , wherein the piston is configured to travel over a stroke of at least twenty four inches.

4. 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.

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.

6. 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.

7. The system of claim 5 , wherein the aircraft is a hypersonic aircraft.

8. The system of claim 5 , wherein the store is a munition.

9. The system of claim 5 , further comprising a latch configured to retain the door panel in the closed position.

10. 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.

11. The system of claim 5 , wherein the pivot axis is defined by a hinge proximate to the forward edge of the door panel.

12. The system of claim 5 , wherein the pivot axis is perpendicular to a longitudinal axis of the aircraft.

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.

14. 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.

15. 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.

16. The method of claim 13 , further comprising retaining, by a latch, the door panel in the closed position.

17. The method of claim 13 , wherein the pivot axis is perpendicular to a longitudinal axis of the aircraft.

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.

19. 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.

20. The aircraft of claim 18 , wherein the aircraft is a hypersonic aircraft.

Assignees

• Boeing Co

Inventors

• Foster John K
• Binkholder Ryan
• Jakubowski Jr Thaddeus

Classifications

• B64C30/00

  Supersonic type aircraft · CPC title

• B64D7/08

  Arrangement of rocket launchers · CPC title

• B64D1/04 Primary

  the articles being explosive, e.g. bombs · CPC title

• B64D1/06 Primary

  Bomb releasing; Bomb doors · CPC title