Systems and methods for preventing the stowage of ejection seat arm catcher members

Patent metadata

Field	Value
Publication number	US-11148809-B2
Application number	US-201916687381-A
Country	US
Kind code	B2
Filing date	Nov 18, 2019
Priority date	Nov 18, 2019
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

The present disclosure provides an arm catcher system for an aircraft ejection seat. The arm catcher system may comprise a first support member configured to rotate in a first direction to be deployed in response to an ejection event and a first persistent locking mechanism coupled to the first support member, wherein the first persistent locking mechanism is configured to allow the support member to rotate in the first direction and configured to prevent the first support member from rotating in a second direction opposite the first direction.

First claim

What is claimed is:

1. An arm catcher system for an aircraft ejection seat, the arm catcher system comprising:
a first support member configured to rotate in a first direction to be deployed in response to an ejection event;
a first persistent locking mechanism coupled to the first support member, wherein the first persistent locking mechanism is configured to allow the first support member to rotate in the first direction and configured to prevent the first support member from rotating in a second direction, the second direction being opposite the first direction; and
a second support member positioned below the first support member, wherein the first support member and the second support member are on a common side of the aircraft election seat.

2. The arm catcher system of claim 1 , further comprising a second persistent locking mechanism coupled to the second support member.

3. The arm catcher system of claim 2 , further comprising a third support member and a third persistent locking mechanism coupled to the third support member, the third support member positioned on an opposite side of the aircraft ejection seat as the first support member.

4. The arm catcher system of claim 3 , further comprising a fourth support member and a fourth persistent locking mechanism coupled to the fourth support member, the fourth support member positioned below the third support member.

5. The arm catcher system of claim 1 , wherein the first persistent locking mechanism comprises a sprag clutch.

6. The arm catcher system of claim 1 , wherein the first persistent locking mechanism comprises a planetary ratchet and pawl device.

7. The arm catcher system of claim 1 , wherein the first persistent locking mechanism comprises a ratchet and pawl device.

8. The arm catcher system of claim 5 , wherein the sprag clutch comprises an inner race, an outer race, and a plurality of sprags disposed radially between the inner race and the outer race, wherein the first support member is coupled to the outer race and the inner race is coupled to a seat frame.

9. The arm catcher system of claim 6 , wherein the planetary ratchet and pawl device comprises a gear, a pawl support, a pawl, and a biasing member,
wherein the gear and the pawl support are mounted to a central pivot axis,
wherein the biasing member is disposed between the pawl support and the pawl,
wherein the gear is coupled to the first support member and the central pivot axis is mounted to a seat frame.

10. The arm catcher system of claim 7 , wherein the ratchet and pawl device comprises a gear, a support, and a pawl,
wherein the gear is mounted to a pivot axis of the support,
wherein the pawl is mounted to a second pivot axis of the support,
wherein the gear is coupled to the first support member and the support is mounted to a seat frame.

11. An aircraft ejection seat comprising:
a seat frame; and
an arm catcher system associated with the seat frame, the arm catcher system comprising:
a first support member configured to rotate in a first direction to be deployed in response to an ejection event;
a first persistent locking mechanism coupled to the first support member, wherein the first persistent locking mechanism is configured to allow the first support member to rotate in the first direction and configured to prevent the first support member from rotating in a second direction, the second direction being opposite the first direction, the first persistent locking mechanism coupled to the seat frame; and
a second support member positioned below the first support member, wherein the first support member and the second support member are on a common side of the aircraft ejection seat.

12. The aircraft ejection seat of claim 11 , further comprising a second persistent locking mechanism coupled to the second support member.

13. The aircraft ejection seat of claim 11 , wherein the first persistent locking mechanism comprises a sprag clutch.

14. The aircraft ejection seat of claim 11 , wherein the first persistent locking mechanism comprises a planetary ratchet and pawl device.

15. The aircraft ejection seat of claim 11 , wherein the first persistent locking mechanism comprises a ratchet and pawl device.

16. The aircraft ejection seat of claim 13 , wherein the sprag clutch comprises an inner race, an outer race, and a plurality of sprags disposed radially between the inner race and the outer race, wherein the first support member is coupled to the outer race and the inner race is coupled to a seat frame.

17. The aircraft ejection seat of claim 14 , wherein the planetary ratchet and pawl device comprises a gear, a pawl support, a pawl, and a biasing member,
wherein the gear and the pawl support are mounted to a central pivot axis,
wherein the biasing member is disposed between the pawl support and the pawl,
wherein the gear is coupled to the first support member and the central pivot axis is mounted to a seat frame.

18. The aircraft ejection seat of claim 15 , wherein the ratchet and pawl device comprises a gear, a support, and a pawl,
wherein the gear is mounted to a pivot axis of the support,
wherein the pawl is mounted to a second pivot axis of the support,
wherein the gear is coupled to the first support member and the support is mounted to a seat frame.

19. A method for manufacturing an aircraft ejection seat, the method comprising:
coupling a first support member of a first arm catcher system to the aircraft ejection seat, the first support member configured to rotate in a first direction in response to an ejection event;
coupling a first persistent locking mechanism to the first support member and to the aircraft ejection seat, the first persistent locking mechanism configured to allow the first support member to rotate in the first direction and configured to prevent the first support member from rotating in a second direction, the second direction being opposite the first direction; and
coupling a second support member of the first arm catcher system to the aircraft ejection seat, wherein the first support member and the second support member are on a common side of the aircraft ejection seat and with the second support arm being positioned below the first support arm.

20. The method of claim 19 , wherein the first persistent locking mechanism comprises a sprag clutch.

Assignees

• Goodrich Corp

Inventors

• Shook Ryan

Classifications

• B64D25/10 Primary

  Ejector seats · CPC title

• B64D11/0644

  Adjustable arm rests · CPC title

• B64D11/0616 Primary

  with ejection means · CPC title

• B64D11/0689

  specially adapted for pilots · CPC title

• B64D25/04

  Seat modifications · CPC title