Symmetric roll divergence

Patent metadata

Field	Value
Publication number	US-11465762-B2
Application number	US-202016983622-A
Country	US
Kind code	B2
Filing date	Aug 3, 2020
Priority date	Aug 3, 2020
Publication date	Oct 11, 2022
Grant date	Oct 11, 2022

Abstract

An ejection seat for an aircraft is disclosed. In various embodiments, the ejection seat includes a base, a divergence rocket attached to the base, and a compensation rocket attached to the base.

First claim

What is claimed is:

1. An ejection seat for an aircraft, comprising:
a base of the ejection seat;
a main ejection rocket attached to and oriented perpendicular to the base of the ejection seat, the orientation of the main ejection rocket being parallel with a yaw axis of the ejection seat;
a divergence rocket attached to and oriented perpendicular to the base of the ejection seat, the divergence rocket being disposed on a first side of the main ejection rocket along a pitch axis of the ejection seat;
a compensation rocket attached to and oriented perpendicular to the base of the ejection seat, the compensation rocket being disposed on a second side of the main ejection rocket opposite the divergence rocket along the pitch axis;
a roll sensor mounted to the ejection seat and configured to produce an output; and
a processor operatively coupled to the roll sensor, the processor configured to fire the main ejection rocket, the divergence rocket, and the compensation rocket based on the output of the roll sensor.

2. The ejection seat of claim 1 , wherein the ejection seat defines the roll axis, the yaw axis and the pitch axis, each of which is pair-wise perpendicular, and wherein firing the divergence rocket causes the base of the ejection seat to roll in a first roll direction about the roll axis.

3. The ejection seat of claim 2 , wherein firing the compensation rocket causes the base of the ejection seat to roll in a second roll direction about the roll axis that is opposite the first roll direction.

4. The ejection seat of claim 1 , wherein a divergence force that is generated by the divergence rocket is perpendicular to the roll axis.

5. The ejection seat of claim 4 , wherein a compensation force that is generated by the compensation rocket is perpendicular to the roll axis.

6. The ejection seat of claim 1 , wherein the processor is configured to fire each of the main ejection rocket, the divergence rocket, and the compensation rocket at at least one of a preset time and a time that is computed on the fly.

7. The ejection seat of claim 6 , wherein the sensor produces an output corresponding to at least one of a roll direction, a roll rate, and a roll position of the ejection seat around a roll axis, and wherein the processor is configured to first time fire at least one of the main ejection rocket, the divergence rocket, and the compensation rocket at a time that is computed on the fly is based on the output of the sensor.

8. The ejection seat of claim 7 , wherein the processor is configured to fire the ejection rocket at an initial time, the divergence rocket at a first preset time, and the compensation rocket at a second preset time, the second preset time being after than the first preset time.

9. The ejection seat of claim 8 , wherein the first preset time follows an initial time at which a main ejection rocket is fired.

10. The ejection seat of claim 9 , wherein the second preset time follows the initial time at which the main ejection rocket is fired.

11. The ejection seat of claim 1 , further comprising
at least one of an additional divergence rocket and additional compensation rocket, the at least one additional divergence rocket being oriented parallel to the base of the ejection seat in a third direction that is perpendicular to the orientation of the divergence rocket, and the at least one additional compensation rocket being oriented parallel to the base of the ejection seat in a fourth direction that is opposite the third direction.

12. The ejection seat of claim 11 , wherein the divergence rocket, the compensation rocket, the at least one of an additional divergence rocket and an additional compensation rocket comprise a plurality of divergence and compensation rockets, and wherein a strength of at least one of the plurality of divergence and compensation rockets are different from each other.

13. A method of controlling a trajectory of an ejection seat having a main ejection rocket, a divergence rocket and a compensation rocket, comprising:
firing the main ejection rocket at an initial time, the main ejection rocket being oriented parallel with a yaw axis of the ejection seat;
firing the divergence rocket at a first time to rotate the ejection seat in a first roll direction, the divergence rocket being oriented along a pitch axis of the ejection seat;
firing the compensation rocket at a second time to rotate the ejection set in a second roll direction that is opposite to the first direction, the compensation rocket being oriented along the pitch axis, the second time being later than the first time; and
sensing at least one of a roll direction, a roll rate, and a roll position of the ejection seat around a roll axis,
wherein firing at least one of the main ejection rocket, divergence rocket, and the compensation rocket is based on the sensing at least one of the roll direction, the roll rate, and the roll position of the ejection seat around the roll axis.

14. The method of claim 13 , wherein the ejection seat defines the roll axis, the yaw axis and the pitch axis, each of which is pair-wise perpendicular, and wherein firing the divergence rocket causes the base of the ejection seat to roll in a first roll direction at a first roll rate about the roll axis.

15. The method of claim 14 , wherein firing the compensation rocket causes the base of the ejection seat to roll in a second roll direction at a second roll rate about the roll axis that is opposite the first roll direction, and wherein firing the compensation rocket brings the second roll rate to zero.

16. The method of claim 15 , wherein a divergence force that is generated by the divergence rocket is perpendicular to the roll axis.

17. The method of claim 16 , wherein a compensation force that is generated by the compensation rocket is perpendicular to the roll axis.

18. The method of claim 13 , wherein the processor is configured to fire each of the main ejection rocket, the divergence rocket, and the compensation rocket at at least one of a preset time and a time that is computed on the fly.

19. The method of claim 18 , wherein the first time is a first preset time following the initial time at which a main ejection rocket is fired.

20. The method of claim 19 , wherein the second time is a second preset time following the initial time at which the main ejection rocket is fired.

Assignees

• Ami Ind Inc

Inventors

• Holstine Steve
• Carson Kassidy L
• Stribrny Casey Andrew
• Bharucha Nicholas K

Classifications

• B64D25/04

  Seat modifications · CPC title

• B64D25/10 Primary

  Ejector seats · CPC title

• B64D25/08

  Ejecting or escaping means · CPC title