Rocket landing systems

Patent metadata

Field	Value
Publication number	US-12168531-B2
Application number	US-202318353521-A
Country	US
Kind code	B2
Filing date	Jul 17, 2023
Priority date	Apr 27, 2015
Publication date	Dec 17, 2024
Grant date	Dec 17, 2024

Abstract

A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea.

First claim

The invention claimed is:

1. A method of stabilizing a landing rocket, comprising:
landing the rocket between a first stabilization element and a second stabilization element, wherein the first stabilization element is coupled to a first lateral support element and coupled to a second lateral support element spaced apart from the first lateral support element, and wherein the second stabilization element is coupled to the first lateral support element and coupled to the second lateral support element; and
moving the first stabilization element toward the second stabilization element.

2. The method of claim 1 wherein the first stabilization element is a first stabilizing cable and the second stabilization element is a second stabilizing cable.

3. The method of claim 1 wherein the first stabilization element is coupled to the first lateral support element by a first clutch system and coupled to the second lateral support element by a second clutch system, and wherein the second stabilization element is coupled to the first lateral support element by a third clutch system and coupled to the second lateral support element by a fourth clutch system.

4. The method of claim 1 , wherein:
the first and second stabilization elements are movable independently of one another;
the first stabilization element includes a first engagement fitting that is movable along a length of the first stabilization element; and
the second stabilization element includes a second engagement fitting that is movable along a length of the second stabilization element.

5. The method of claim 1 , further comprising:
landing the rocket between a third stabilization element and a fourth stabilization element, wherein the third stabilization element is coupled to a third lateral support element and coupled to a fourth lateral support element spaced apart from the third lateral support element, and wherein the fourth stabilization element is coupled to the third lateral support element and coupled to the fourth lateral support element; and
moving the third stabilization element toward the fourth stabilization element.

6. The method of claim 5 wherein the first and second stabilization elements extend perpendicular to the third and fourth stabilization elements and the first and second lateral support elements extend perpendicular to the third and fourth lateral support elements.

7. The method of claim 1 wherein landing the rocket includes landing the rocket on landing gear of the rocket under control of an engine of the rocket.

8. The method of claim 7 , wherein the first and second stabilization elements contact the rocket as the rocket lands.

9. The method of claim 1 wherein movement of the first stabilization element toward the second stabilization element is initiated when a portion of the rocket is between the first and second stabilization elements.

10. The method of claim 1 , further comprising:
landing the rocket between a third stabilization element and a fourth stabilization element, wherein the third stabilization element is coupled to a third lateral support element and coupled to a fourth lateral support element spaced apart from the third lateral support element, and wherein the fourth stabilization element is coupled to the third lateral support element and coupled to the fourth lateral support element; and
moving the third stabilization element toward the fourth stabilization element;
wherein the third and fourth stabilization elements are above the first and second stabilization elements and the third and fourth lateral support elements are above the first and second lateral support elements.

11. The method of claim 10 wherein movement of the first stabilization element toward the second stabilization element is initiated after movement of the third stabilization element toward the fourth stabilization element is initiated.

12. The method of claim 10 wherein movement of the third stabilization element toward the fourth stabilization element is initiated when the rocket clears a safety plane of the third and fourth stabilization elements and movement of the first stabilization element toward the second stabilization element is initiated when the rocket clears a safety plane of the first and second stabilization elements.

13. The method of claim 10 , further comprising:
landing the rocket between a fifth stabilization element and a sixth stabilization element, wherein the fifth stabilization element is coupled to a fifth lateral support element and coupled to a sixth lateral support element spaced apart from the fifth lateral support element, and wherein the sixth stabilization element is coupled to the fifth lateral support element and coupled to the sixth lateral support element; and
moving the fifth stabilization element toward the sixth stabilization element.

14. The method of claim 13 wherein the first and second stabilization elements extend perpendicular to the fifth and sixth stabilization elements and the first and second lateral support elements extend perpendicular to the fifth and sixth lateral support elements.

Assignees

• Knudsen N Eric
• Knudsen Matthew Niels
• Knudsen Andrew Niels
• Knudsen Jacob Niels

Inventors

• Knudsen N Eric
• Knudsen Matthew Niels
• Knudsen Andrew Niels
• Knudsen Jacob Niels

Classifications

• B64G5/00 Primary

  Ground equipment for vehicles, e.g. starting towers, fuelling arrangements (B64G3/00 takes precedence) · CPC title

• B64G1/625

  Landing devices; Undercarriages · CPC title

• B64G2005/005

  Systems for launching spacecraft from a platform at sea · CPC title

• B64G1/62 Primary

  Systems for re-entry into the earth's atmosphere; Retarding or landing devices · CPC title