Rocket motor with combustion product deflector

Patent metadata

Field	Value
Publication number	US-10690443-B1
Application number	US-201916249304-A
Country	US
Kind code	B1
Filing date	Jan 16, 2019
Priority date	Jan 16, 2019
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

A missile includes a rocket motor that has a flow deflector in an expansion region of the rocket motor's nozzle. The flow deflector diverts flow of combustion products away from a safe region that is aft of the missile. The safe region protects an operator of a launcher used to fire the missile, such as a shoulder-fired launcher, from harm caused by the combustion products. The flow deflector may be small enough such that it does not significantly adversely affect the performance of the rocket motor. The presence of the flow diverter may allow for the rocket motor to be started sooner in the flight of the missile, or at a distance closer to the operator, while still keeping the operator safe. The flow deflector and supporting structure, such as struts, may be additively manufactured with at least an aft part of the nozzle, as a continuous single-piece part.

First claim

What is claimed is:

1. A rocket motor comprising:
a fuel element;
a converge-diverge nozzle through which combustion products from the burning of the fuel element pass; and
a flow deflector along a centerline of an expansion region of the nozzle;
wherein the flow deflector deflects away from the centerline combustion products from the burning of the fuel;
wherein the flow deflector is attached to an inner wall of a diverge portion of the nozzle via struts, with the diverge portion defining the expansion region; and
wherein an upstream end of the flow deflector is in the diverge portion of the nozzle.

2. The rocket motor of claim 1 , wherein the flow deflector is conical.

3. The rocket motor of claim 1 , wherein the flow deflector has a wedge shape.

4. The rocket motor of claim 1 , wherein the flow deflector has a maximum extent of at least 3.2 mm (0.125 inches).

5. The rocket motor of claim 1 , wherein the flow deflector, the struts, and at least part of the diverge portion are a single unitary additively-manufactured part.

6. The rocket motor of claim 1 , as part of a missile, wherein the missile also includes:
a payload; and
a booster that provides initial thrust to the missile, prior to operation of the rocket motor.

7. The missile of claim 6 , in combination with a tubular launcher that launches the missile, wherein the launcher contains and directs force from the booster to provide thrust to the missile.

8. The combination of claim 7 , wherein the launcher is a shoulder-fired launcher.

9. The rocket motor of claim 1 , wherein the upstream end of the flow deflector is a rounded nose.

10. The rocket motor of claim 1 , wherein the upstream end of the flow deflector is a flat nose.

11. The rocket motor of claim 1 , wherein the flow deflector is at a downstream end of the diverge portion of the nozzle.

12. The rocket motor of claim 1 , wherein the flow deflector extends straight across a diameter of the rocket motor.

13. A method of firing a rocket-propelled missile, the method comprising:
launching the missile from a launcher operated by an operator; and
propelling the missile using a rocket motor of the missile;
wherein the propelling includes deflecting combustion products using a flow deflector in an expansion region of a nozzle of the rocket motor, wherein an upstream end of the flow deflector is in a diverge portion of the nozzle, thereby creating a safe region behind the missile, when the operator of the launcher is in the safe region.

14. The method of claim 13 , wherein the launching includes the operator supporting the launcher on a shoulder of the operator.

15. The method of claim 13 , wherein the creating the safe region includes creating a conical safe region, with the conical safe region having an axis coincident with a central axis of the expansion region.

16. The method of claim 13 , wherein the creating the safe region includes creating a wedge-shape safe region.

17. The method of claim 13 , wherein the deflecting includes deflecting the combustion products using a bow shock produced by the deflector.

18. The method of claim 13 , wherein the creating the safe region includes creating a region having an extent of at least 30 cm perpendicular to a flight path of the missile at a distance of 6 meters behind the missile.

19. The method of claim 13 , wherein the propelling is initiated with the missile at least a 6 meters away from the launcher.

Assignees

• Raytheon Co

Inventors

• Summers Matt H
• Villarreal James Kendall
• Smallwood David A
• Dryer Richard
• Hitner John M

Classifications

• F42B15/10

  Missiles having a trajectory only in the air · CPC title

• F42B10/665

  characterised by using a nozzle provided with at least a deflector mounted within the nozzle · CPC title

• F41F3/0455 Primary

  Bazookas · CPC title

• F41F3/0413 Primary

  Means for exhaust gas disposal, e.g. exhaust deflectors, gas evacuation systems · CPC title