Variable thrust catapult

Patent metadata

Field	Value
Publication number	US-11300078-B2
Application number	US-202016747420-A
Country	US
Kind code	B2
Filing date	Jan 20, 2020
Priority date	Jan 20, 2020
Publication date	Apr 12, 2022
Grant date	Apr 12, 2022

Abstract

A rocket catapult assembly for an ejection seat may comprise a drive motor, a metering tube, a first cartridge, and a second cartridge. The metering tube may include an outer wall having a gas pervious section and a gas impervious section. The drive motor may be configured to translate the metering tube and align the gas pervious section or gas impervious section with a first cartridge and a second cartridge to produce a desired thrust of the rocket catapult assembly.

First claim

What is claimed is:

1. A rocket catapult assembly for use in an ejection seat system of an aircraft, comprising:
a drive motor including a drive shaft;
a metering tube coupled to the drive shaft, the metering tube including an outer wall having a gas pervious section and a gas impervious section;
a first cartridge disposed radially outward of the metering tube;
a second cartridge disposed axially adjacent to the first cartridge; and
a separation disk disposed between the first cartridge and the second cartridge.

2. The rocket catapult assembly of claim 1 , further comprising a mortar inner case defining a chamber, wherein the drive motor is configured to translate the drive shaft and the metering tube along an axis defined by a centerline of the mortar inner case.

3. The rocket catapult assembly of claim 2 , wherein the gas pervious section is disposed adjacent to the first cartridge and the gas impervious section is disposed adjacent to the second cartridge in a first configuration, and wherein the gas pervious section is disposed adjacent to the first cartridge and the second cartridge in a second configuration.

4. The rocket catapult assembly of claim 3 , wherein the first configuration corresponds to a first thrust of the rocket catapult assembly, wherein the second configuration corresponds to a second thrust of the rocket catapult assembly, and wherein the second thrust is greater than the first thrust.

5. The rocket catapult assembly of claim 3 , wherein the first cartridge is in fluid communication with the chamber in the first configuration, and wherein the second cartridge is fluidly isolated from the chamber in the first configuration.

6. The rocket catapult assembly of claim 1 , further comprising an igniter coupled to the first cartridge.

7. The rocket catapult assembly of claim 1 , wherein the first cartridge and the second cartridge are annular in shape.

8. An aircraft ejection seat system 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 mortar assembly comprising a mortar outer casing and a mortar inner casing extending from a proximal end to a distal end, the mortar inner casing defining a chamber;
a drive motor including a drive shaft;
a metering tube coupled to the drive shaft; the metering tube including an outer wall having a gas pervious section and a gas impervious section, wherein the metering tube is configured to alter a thrust of the rocket catapult assembly based on an axial alignment of the metering tube.

9. The aircraft ejection seat system of claim 8 , further comprising:
a first cartridge disposed radially outward of the metering tube;
a second cartridge disposed axially adjacent to the first cartridge; and
a separation disk disposed between the first cartridge and the second cartridge.

10. The aircraft ejection seat system of claim 9 , further comprising a display switch configured to be in a first position and a second position, wherein the display switch is configured to create a first electrical connection and align the gas pervious section with the first cartridge and the gas impervious section with the second cartridge in response to being in the first position, wherein the display switch is configured to create a second electrical connection and align the gas pervious section with the first cartridge and the second cartridge in response to being in the second position.

11. The aircraft ejection seat system of claim 9 , further comprising a load cell coupled to the seat pan.

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

13. The aircraft ejection seat system of claim 12 , wherein the controller is configured to align the gas pervious section with the first cartridge only when a weight below a first threshold weight is measured by the load cell.

14. The aircraft ejection seat system of claim 13 , wherein the controller is configured to align the gas pervious section with the first cartridge and the second cartridge when the weight is measured by the load cell as being above a second threshold weight, wherein the second threshold weight is greater than the first threshold weight.

15. The aircraft ejection seat system of claim 9 , further comprising a third cartridge disposed axially adjacent to the second cartridge.

16. The aircraft ejection seat system of claim 9 , further comprising a breech, the drive motor coupled to the breech.

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;
aligning a gas pervious section of an outer wall of a metering tube with a first cartridge, the first cartridge disposed radially outward from the metering tube; and
aligning a gas impervious section of the outer wall of the metering tube with a second cartridge in response to the load cell measuring a weight below a first weight threshold.

18. The method of claim 17 , further comprising aligning the gas pervious section with the first cartridge and the second cartridge in response to the weight being above the first weight threshold.

19. The method of claim 18 , further comprising aligning the gas impervious section with a third cartridge in response to the weight being above the first weight threshold and below a second weight threshold.

20. The method of claim 19 , further comprising aligning the gas pervious section with the first cartridge, the second cartridge, and the third cartridge in response to the weight being above the second weight threshold.

Assignees

• Ami Ind Inc

Inventors

• Benjamin Jeff
• Salois Matthew D

Classifications

• F02K9/80 Primary

  characterised by thrust or thrust vector control (burning control of solid propellants F02K9/26; feeding control of liquid or gaseous propellants F02K9/56; re-ignitable, restartable or intermittently operated rocket-engine plants F02K9/94) · CPC title

• B64D25/10

  Ejector seats · CPC title

• F02K9/36 Primary

  Propellant charge supports · CPC title

• F02K9/62

  Combustion or thrust chambers · CPC title