Rocket-based inverted parachute deployment system

Patent metadata

Field	Value
Publication number	US-10106264-B1
Application number	US-201615249079-A
Country	US
Kind code	B1
Filing date	Aug 26, 2016
Priority date	Aug 26, 2016
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

A system to deploy a parachute is disclosed. In various embodiments, a plurality of rockets are attached to a perimeter of the parachute. Each of the rockets is configured to fly initially in a first direction substantially in a direction of deployment of the parachute and to fly subsequently along a trajectory that includes a component that is substantially perpendicular to the direction of deployment and extends radially from a center of the parachute.

First claim

What is claimed is:

1. A system to deploy a parachute, comprising:
a plurality of rockets attached to a perimeter of the parachute,
wherein each of the rockets is configured to fly initially in a first direction substantially in a direction of deployment of the parachute and to fly subsequently along a trajectory that includes a component that is substantially perpendicular to the direction of deployment and extends radially from a center of the parachute.

2. The system of claim 1 , wherein the trajectory includes a second component substantially opposite the direction of deployment.

3. The system of claim 1 , wherein the plurality of rockets initially deploy the parachute in an inverted position.

4. The system of claim 1 , wherein a rocket of the plurality of rockets flies in a parabolic trajectory away from a center of the parachute.

5. The system of claim 1 , wherein a rocket of the plurality of rockets is tethered to the parachute with multiple tethers comprising a tether than pulls the rocket in a direction substantially opposite the direction of deployment.

6. The system of claim 1 , wherein a nozzle of a rocket of the plurality of rockets is shaped to cause the rocket to turn after it is deployed.

7. The system of claim 1 , wherein a nozzle of a rocket of the plurality of rockets is angled away from the rest of the rocket.

8. The system of claim 1 , wherein a nozzle of a rocket of the plurality of rockets changes in shape after the rocket is deployed.

9. The system of claim 1 , wherein a nozzle of a rocket of the plurality of rockets becomes progressively angled away from the rest of the rocket after the rocket is deployed.

10. The system of claim 1 , wherein a fin of a rocket of the plurality of rockets is shaped to cause the rocket to turn after it is deployed.

11. The system of claim 1 , wherein a fin of a rocket of the plurality of rockets changes in shape after the rocket is deployed.

12. The system of claim 1 , wherein a nozzle or a fin of a rocket of the plurality of rockets comprises a bimetallic material or a material that changes shape under heat.

13. The system of claim 1 , wherein a fin of a rocket of the plurality of rockets is attached to a nozzle of the rocket.

14. The system of claim 1 , wherein a fin or a nozzle of a rocket of the plurality of rockets changes in shape after the rocket is deployed based on an intensity or duration of heat released from the nozzle.

15. The system of claim 1 , wherein a nozzle of a rocket of the plurality of rockets is controlled by a pilot, a computer, or a servomotor after deployment of the rocket.

16. The system of claim 1 , wherein a size, a number, a fuel type, or a fuel amount of the plurality of rockets is determined based on a trajectory of the rocket determined to optimally deploy the parachute.

17. The system of claim 1 , wherein a combustion chamber type of a rocket of the plurality of rockets is determined based on a trajectory of the rocket determined to optimally deploy the parachute.

18. The system of claim 1 , wherein the plurality of rockets are able to be deployed at once or in stages.

19. The system of claim 1 , wherein the plurality of rockets are able to be deployed at once or in stages based on a pilot indication, an environmental condition, or an aircraft condition.

Assignees

• Kitty Hawk Corp

Inventors

• Robertson Cameron
• Reichert Todd
• Vander Lind Damon

Classifications

• F42B10/02 Primary

  Stabilising arrangements · CPC title

• B64D17/725

  by explosive means · CPC title

• F42B12/68

  Line-carrying missiles, e.g. for life-saving (harpoons F42B30/14 {, mine-clearing snakes F41H11/14}) · CPC title

• B64D17/80 Primary

  in association with aircraft, e.g. for braking thereof · CPC title

• B64D17/62 Primary

  Deployment · CPC title