Spring-assisted deployment of a pivotable rocket motor

Patent metadata

Field	Value
Publication number	US-10094646-B2
Application number	US-201514685585-A
Country	US
Kind code	B2
Filing date	Apr 13, 2015
Priority date	Apr 13, 2015
Publication date	Oct 9, 2018
Grant date	Oct 9, 2018

Abstract

A rocket comprises at least one propulsion unit including a pivotable rocket motor, a spring-assisted one-time deployment mechanism, and a release mechanism. The pivotable rocket motor is pivotable between a stowed position and a deployed position. The spring-assisted one-time deployment mechanism moves the rocket motor from the stowed position to the deployed position when the deployment mechanism is released by the release mechanism. Outer geometry of the rocket is changed as the rocket motor is moved to the deployed position.

First claim

The invention claimed is:

1. A rocket comprising at least one propulsion unit including:
a pivotable motor mount;
a rocket motor coupled to the pivotable motor mount, so that the entire rocket motor is pivotable on the motor mount between a stowed position and a deployed position, wherein an outer geometry of the rocket is changed as the rocket motor is moved to the deployed position;
a spring-assisted one-time deployment mechanism for moving the rocket motor from the stowed position to the deployed position when the deployment mechanism is released; and
a release mechanism for releasing the deployment mechanism.

2. The rocket of claim 1 , wherein outer diameter of the rocket is increased as the rocket motor is moved to the deployed position.

3. The rocket of claim 1 , wherein the rocket motor includes at least a nozzle and combustion chamber.

4. The rocket of claim 1 , wherein the at least one propulsion unit includes a plurality of propulsion units arranged in a tractor configuration.

5. The rocket of claim 1 , wherein the deployment mechanism includes a spring that stores mechanical energy when the rocket motor is in the stowed position; and wherein the release mechanism includes a frangible nut that, until broken, holds the spring in an energy storage state and the rocket motor in the stowed position and that, when broken, allows the spring to urge the rocket motor towards the deployed position.

6. The rocket of claim 1 , wherein the release mechanism is non-explosive.

7. The rocket of claim 1 , further comprising a frame having a load ring; wherein the pivotable rocket motor includes an axle pivot that extends through the load ring and terminates in the motor mount.

8. The rocket of claim 7 , wherein the axle pivot extends radially outward from the frame.

9. The rocket of claim 7 , wherein the deployment mechanism is mounted to the load ring of the frame.

10. The rocket of claim 7 , wherein the motor mount includes a spherical hard stop to correctly align a thrust line of the rocket motor in the deployed position.

11. The rocket of claim 7 , wherein the axle pivot forms a hinge line, and wherein the rocket motor has a thrust line that is off center from the hinge line, whereby thrust from the rocket motor holds the rocket motor in the deployed position.

12. The rocket of claim 7 , wherein an arm extends radially from the axle pivot; and wherein the deployment mechanism applies spring force to the arm.

13. The rocket of claim 7 , wherein the rocket motor is rotatable by at least twenty degrees from the stowed position to the deployed position.

14. A launch system comprising:
an aircraft defining an envelope space; and
the rocket of claim 1 , wherein the rocket motor in the stowed position is disposed within the envelope space.

15. A rocket stage comprising:
a frame; and
a plurality of propulsion units, each propulsion unit including:
a rocket motor mounted to the frame by an axle pivot, the rocket motor being pivotable between a stowed position and a deployed position; and
a spring-loaded housing and frangible nut for locking the axle pivot with the rocket motor in the stowed position, the spring-loaded housing causing the axle pivot to rotate the rocket motor to the deployed position when the frangible nut is broken
wherein outer geometry of the rocket is changed as the rocket motor is moved from the stowed position to the deployed position.

16. The rocket stage of claim 15 , wherein each rocket motor includes at least a nozzle and combustion chamber.

17. The rocket stage of claim 15 , wherein each propulsion unit includes a motor mount at an end of the axle pivot, the rocket motor mounted to the motor mount.

18. The rocket stage of claim 17 , wherein the motor mount includes a spherical hard stop to correctly align a thrust line of the rocket motor in the deployed position.

19. The rocket stage of claim 15 , wherein the axle pivot forms a hinge line, and wherein the rocket motor has a thrust line that is off center from the hinge line.

20. A method comprising:
carrying a rocket aboard an aircraft, the rocket having a rocket motor coupled to a pivotable motor mount, so that the entire rocket motor is pivotable on the motor mount to a stowed position to fit within an envelope space of the aircraft; and
releasing the rocket at a deployment altitude, wherein a spring-assisted mechanism aboard the rocket causes the entire rocket motor to pivot on the motor mount to a deployed position.

Assignees

• Boeing Co

Inventors

• Albright Justin G
• Kutzmann Aaron J

Classifications

• F42B15/36 Primary

  Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means · CPC title

• F02K9/976

  Deployable nozzles · CPC title

• F42B15/10

  Missiles having a trajectory only in the air · CPC title

• F05D2260/311

  of the frangible or shear type · CPC title

• B64G1/645

  Separators · CPC title