Propulsion system with single initiator for multiple rocket motors

Patent metadata

Field	Value
Publication number	US-11852104-B2
Application number	US-202117466245-A
Country	US
Kind code	B2
Filing date	Sep 3, 2021
Priority date	Sep 3, 2021
Publication date	Dec 26, 2023
Grant date	Dec 26, 2023

Abstract

A propulsion system includes multiple solid rocket motors that are activated by a single initiator. The rocket motors act in parallel, providing thrust in a single direction. The initiator activates an ignition charge that is in or operatively coupled to a plenum that transports hot gasses from the ignition charge to the rockets to be ignited. The plenum may be an annular plenum, which may be located in an annular manifold. The plenum may be an unchoked plenum, allowing flow of hot gasses without choking. The plenum may be lined with an insulator material. A cover may be used to cover the plenum, and also to receive the rocket motors. The rocket motors may be solid-fuel rocket motors. The individual rocket motors may have separate ignition booster charges coupled to the plenum, which are ignited by the ignition charge and which in turn ignite the propellant grains.

First claim

What is claimed is:

1. A propulsion system comprising:
a manifold; and
an initiator operatively coupled to the manifold;
wherein the manifold has a plenum therein to which multiple rocket motors are couplable via separate mounts for each of the multiple rocket motors, to provide ignition to the multiple rocket motors',
wherein the plenum is an annular plenum with an ignition charge connected to the initiator therein, wherein the ignition charge is aligned with only one rocket motor of the multiple rocket motors, wherein the ignition charge is in a part but not all of the plenum;
wherein ignition of the initiator fills the plenum with hot gasses, wherein when the hot gasses have fully filled the plenum, the hot gasses enter the separate mounts to ignite separate ignition booster charges in each mount to provide ignition to each of the multiple rocket motors attached to the separate mounts.

2. The propulsion system of claim 1 , wherein the manifold is an annular manifold.

3. The propulsion system of claim 1 , wherein the initiator is coupled to an outer surface of the manifold.

4. The propulsion system of claim 1 , further comprising a cover on the manifold.

5. The propulsion system of claim 4 , wherein the cover has the mounts for receiving the rocket motors.

6. The propulsion system of claim 4 , wherein the mounts have chambers therein, with the ignition boosters in the chambers.

7. The propulsion system of claim 1 , wherein the manifold is made of metal.

8. The propulsion system of claim 1 , wherein the manifold is made of steel.

9. The propulsion system of claim 1 , further comprising an insulator on an inner surface of the plenum.

10. The propulsion system of claim 9 , wherein the insulator is a silicone material.

11. The propulsion system of claim 1 , further comprising the rocket motors, operatively coupled to the plenum.

12. The propulsion system of claim 11 , wherein the rocket motors are circumferentially spaced around the manifold.

13. The propulsion system of claim 11 , wherein the rocket motors are an even number of rocket motors.

14. The propulsion system of claim 13 , wherein the rocket motors includes pairs of rocket motors diametrically opposed to one another.

15. The propulsion system of claim 11 , wherein the rocket motors are threadedly coupled to mounts on a cover on the manifold.

16. A flight vehicle comprising:
a fuselage; and
a propulsion system coupled to the fuselage, the propulsion system including:
a manifold; and
an initiator operatively coupled to the manifold;
wherein the manifold has a plenum therein to which multiple rocket motors are couplable via separate mounts for each of the multiple rocket motors, to provide ignition to the multiple rocket motors;

wherein the plenum is an annular plenum with an ignition charge connected to the initiator therein, wherein the ignition charge is aligned with only one rocket motor of the multiple rocket motors, wherein the ignition charge is in a part but not all of the plenum;
wherein ignition of the initiator fills the plenum with hot gasses, wherein when the hot gasses have fully filled the plenum, the hot gasses enter the separate mounts to ignite separate ignition booster charges in each mount to provide ignition to each of the multiple rocket motors attached to the separate mounts.

Assignees

• Raytheon Co

Inventors

• Pinello-Benavides Jacob
• Meschberger John
• Moore Stephen
• Little Iii Edward

Classifications

• F02K9/95 Primary

  characterised by starting or ignition means or arrangements (safety devices F02K9/38) · CPC title

• F02K9/32

  Constructional parts; Details not otherwise provided for · CPC title

• F02K9/763

  with solid propellant · CPC title

• F02K9/78

  with an air-breathing jet-propulsion plant (with a ram-jet engine F02K7/18) · CPC title

• F02K9/343

  Joints, connections, seals therefor · CPC title