Variable thrust catapult

Patent metadata

Field	Value
Publication number	US-11242153-B2
Application number	US-201916667772-A
Country	US
Kind code	B2
Filing date	Oct 29, 2019
Priority date	Oct 29, 2019
Publication date	Feb 8, 2022
Grant date	Feb 8, 2022

Abstract

A rocket catapult assembly for an ejection seat may comprise a motor assembly including a proximal end and a distal end, an outlet tube coupled to the distal end, and a valve coupled to the outlet tube. The valve may be configured to vary an operating pressure based on an occupant's weight. The valve may be in a closed configuration, on open configuration, or a partially open configuration during ejection of the ejection seat.

First claim

What is claimed is:

1. A rocket catapult assembly for use in an ejection seat system of an aircraft, comprising:
a motor assembly comprising a motor outer tube and a mortar inner casing extending from a proximal end and a distal end, the mortar inner casing defining a chamber;
an outlet tube coupled to the distal end, the outlet tube in fluid communication with the chamber; and
a valve coupled to the outlet tube, the valve configured to vary an operating pressure of a pressurized fluid during operation of the rocket catapult assembly;
wherein the proximal end of the rocket catapult assembly is configured to be coupled to the aircraft.

2. The rocket catapult assembly of claim 1 , wherein the valve comprises a solenoid valve.

3. The rocket catapult assembly of claim 2 , wherein the solenoid valve is in communication with a controller, wherein the solenoid valve is configured to be in a closed position in response to a command by the controller when a load of a load cell exceeds a threshold load.

4. The rocket catapult assembly of claim 1 , wherein the valve comprises a modulated bleed valve.

5. The rocket catapult assembly of claim 4 , wherein the modulated bleed valve is in communication with a controller, wherein the modulated bleed valve is configured to vary between an open configuration and a closed configuration to maintain a desired pressure in response to a command by the controller of the desired pressure based on a measured load of a load cell.

6. The rocket catapult assembly of claim 1 , wherein the valve comprises a relief valve.

7. The rocket catapult assembly of claim 6 , wherein the relief valve is configured to at least partially open in response to a pressure in the outlet tube exceeding a pressure threshold.

8. An aircraft ejection system comprising:
an ejection seat, comprising:
a seat pan;
a seat back coupled to the seat pan; and
a rocket catapult assembly coupled to the seat back, the rocket catapult assembly comprising:
a motor assembly comprising a motor outer tube and a mortar inner casing extending from a proximal end and a distal end, the mortar inner casing defining a chamber;
an outlet tube coupled to the distal end, the outlet tube in fluid communication with the chamber; and
a valve coupled to the outlet tube, the valve configured to vary an operating pressure of a pressurized fluid during operation of the rocket catapult assembly;

wherein the proximal end of the rocket catapult assembly is configured to be coupled to an aircraft.

9. The aircraft ejection system of claim 8 , further comprising a display switch, wherein the display switch is configured to create an electrical connection and open the valve from a closed configuration to an open configuration, and wherein the valve is a solenoid valve.

10. The aircraft ejection system of claim 8 , further comprising a display switch, wherein the display switch is configured to create an electrical connection and close the valve from a closed configuration to an open configuration, and wherein the valve is a solenoid valve.

11. The aircraft ejection system of claim 8 , further comprising a load cell coupled to the seat pan.

12. The aircraft ejection system of claim 11 , further comprising a controller in electrical communication with the load cell and the valve.

13. The aircraft ejection system of claim 12 , wherein the valve is a solenoid valve, and wherein the solenoid valve is configured to be in a closed position in response to a command by the controller when a load of the load cell exceeds a threshold load.

14. The aircraft ejection system of claim 12 , wherein the valve is a modulated bleed valve, and wherein the modulated bleed valve is in communication with the controller, wherein the modulated bleed valve is configured to vary between an open configuration and a closed configuration to maintain a desired pressure in response to a command by the controller of the desired pressure based on a measured load of the load cell.

15. The aircraft ejection system of claim 8 , wherein the valve is a relief valve.

16. The aircraft ejection system of claim 15 , wherein the relief valve is configured to at least partially open in response to a pressure in the outlet tube exceeding a pressure threshold.

17. A method of controlling an operating pressure of a rocket catapult assembly for an ejection seat of an aircraft, the method comprising:
compressing a load cell disposed in a seat pan of the ejection seat; and
opening or closing a valve in response to compressing the load cell, wherein the valve is coupled to, and in fluid communication with, an outlet tube, the outlet tube coupled to a distal end of a motor assembly of the rocket catapult assembly;
wherein a proximal end of the rocket catapult assembly is configured to be coupled to the aircraft.

18. The method of claim 17 , wherein the valve is a solenoid valve, and wherein the step of opening or closing the solenoid valve further comprises opening the solenoid valve when a load measured by the load cell exceeds a load threshold.

19. The method of claim 17 , wherein the valve is a solenoid valve, and wherein prior to the step of opening or closing the solenoid valve, the method further comprises completing an electrical connection in response to compressing the load cell.

20. The method of claim 17 , wherein the valve is a modulated bleed valve.

Assignees

• Goodrich Corp

Inventors

• Whelan Patrick
• Salois Matthew D
• Benjamin Jeff
• Mueller Kevin J

Classifications

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• B64D25/10 Primary

  Ejector seats · CPC title