EMERGENCY MANUAL PARACHUTE OPERATION SYSTEM

• US 20200130852A1
• Filed: 10/29/2018
• Published: 04/30/2020
• Est. Priority Date: 10/29/2018
• Status: Abandoned Application

• Current Assignee: AMI Industries, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: AMI Industries, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: MARUTZKY, KYLER, BROWNSBERGER, TIMOTHY, BENJAMIN, JEFF
• Application Number:
  US16/173,957
• Publication Number:
  US 20200130852A1
• Time in Patent Office: Days
• CPC Class Codes: B64D 11/0616 with ejection means
• CPC Class Codes: B64D 17/62 Deployment
• CPC Class Codes: B64D 17/725 by explosive means
• CPC Class Codes: B64D 17/74 Sequential deployment of a plurality of canopies
• CPC Class Codes: B64D 25/10 Ejector seats
• CPC Class Codes: F15B 15/19 Pyrotechnical actuators
• CPC Class Codes: F15B 20/002 Electrical failure

Abstract

A chute-deployment-seat-release system for an ejection seat may be configured to deploy a parachute from the ejection seat and release an occupant restraint of the ejection seat. The chute-deployment-seat-release system may comprise an auto-deployment assembly, including a first power supply, and a manual deployment assembly, including a second power supply and a handle. The first power supply may be configured to activate in response to expulsion of the ejection seat from an aircraft. The second power supply may be configured to activate in response to an actuation of the handle.

Claims

1. A chute-deployment-seat-release system for deploying a parachute from an ejection seat and releasing an occupant restraint of the ejection seat, the chute-deployment-seat-release system comprising:

a sequencer including a first logic circuit and a second logic circuit;

a first power supply electrically coupled to the first logic circuit, wherein the first power supply is configured to activate in response to expulsion of the ejection seat;

a second power supply electrically coupled to the second logic circuit; and

a handle operationally coupled to the second power supply, wherein the second power supply is configured to activate in response to an actuation of the handle.

2. The chute-deployment-seat-release system of claim 1, further comprising:

a parachute mortar;

a first electrical conduit coupled to the parachute mortar, wherein the first logic circuit and the second logic circuit are electrically coupled to the first electrical conduit;

a restraint release thruster; and

a second electrical conduit coupled to the restraint release thruster, wherein the first logic circuit and the second logic circuit are electrically coupled to the second electrical conduit.

3. The chute-deployment-seat-release system of claim 2, wherein the second logic circuit is configured to fire the restraint release thruster a predetermined time delay after firing the parachute mortar.

4. The chute-deployment-seat-release system of claim 1, further comprising a cable configured to activate the second power supply, wherein the handle is configured to translate the cable.

5. The chute-deployment-seat-release system of claim 4, wherein the second power supply comprises an activation pin, wherein the second power supply is configured to activate in response to a translation of the activation pin, and wherein the cable is configured to translate the activation pin in response to the actuation of the handle.

6. The chute-deployment-seat-release system of claim 5, further comprising a cable crank operationally coupled to the cable, wherein the cable crank is configured to rotate about a pivot joint and translate the cable in response to the actuation of the handle.

7. The chute-deployment-seat-release system of claim 1, wherein the second power supply comprises a thermal battery.

8. An ejection seat configured to be expelled from an aircraft, the ejection seat comprising:

a parachute;

an occupant restraint; and

a chute-deployment-seat-release system configured to deploy the parachute and release the occupant restraint, the chute-deployment-seat-release system comprising;

an auto-deployment assembly including a first power supply, wherein the first power supply is configured to activate in response to expulsion of the ejection seat from the aircraft; and

a manual deployment assembly including a second power supply and a handle, wherein the second power supply is configured to activate in response to an actuation of the handle.

9. The ejection seat of claim 8, wherein the chute-deployment-seat-release system further comprises a sequencer, the sequencer including a first logic circuit and a second logic circuit, and wherein the first logic circuit is electrically coupled to the first power supply and the second logic circuit is electrically coupled to the second power supply.

10. The ejection seat of claim 9, wherein the chute-deployment-seat-release system further comprises:

a parachute mortar electrically coupled to the first logic circuit and the second logic circuit; and

a restraint release thruster electrically coupled to the first logic circuit and the second logic circuit.

11. The ejection seat of claim 10, wherein the second logic circuit is configured to fire the restraint release thruster a predetermined time delay after firing the parachute mortar.

12. The ejection seat of claim 8, wherein the manual deployment assembly further comprises a cable configured to activate the second power supply, wherein the handle is configured to translate the cable.

13. The ejection seat of claim 12, wherein the second power supply comprises an activation pin, and wherein the second power supply is configured to activate in response to a translation of the activation pin, and wherein the cable is configured to translate the activation pin in response to the actuation of the handle.

14. The ejection seat of claim 8, wherein the second power supply comprises a thermal battery.

15. A chute-deployment-seat-release system configured to deploy a parachute and release an occupant restraint of an ejection seat, the chute-deployment-seat-release system comprising:

an auto-deployment assembly including a first power supply, wherein the first power supply is configured to activate in response to expulsion of the ejection seat from an aircraft; and

a manual deployment assembly including a second power supply and a handle, wherein the second power supply is configured to activate in response to an actuation of the handle.

16. The chute-deployment-seat-release system of claim 15, further comprising a sequencer, the sequencer including a first logic circuit and a second logic circuit, wherein the first logic circuit is electrically coupled to the first power supply and the second logic circuit is electrically coupled to the second power supply.

17. The chute-deployment-seat-release system of claim 16, further comprising:

a parachute mortar electrically coupled to the first logic circuit and the second logic circuit; and

a restraint release thruster electrically coupled to the first logic circuit and the second logic circuit.

18. The chute-deployment-seat-release system of claim 17, wherein the second logic circuit is configured to fire the restraint release thruster a predetermined time delay after firing the parachute mortar.

19. The chute-deployment-seat-release system of claim 15, wherein the manual deployment assembly further comprises a cable configured to activate the second power supply, and wherein the handle is configured to translate the cable.

20. The chute-deployment-seat-release system of claim 19, wherein the second power supply comprises an activation pin, and wherein the second power supply is configured to activate in response to a translation of the activation pin, and wherein the cable is configured to translate the activation pin in response to the actuation of the handle.