Variable burn-rate solid rocket motor ignition method

Patent metadata

Field	Value
Publication number	US-11530669-B2
Application number	US-202017017741-A
Country	US
Kind code	B2
Filing date	Sep 11, 2020
Priority date	Sep 11, 2020
Publication date	Dec 20, 2022
Grant date	Dec 20, 2022

Abstract

A solid rocket motor uses at least one thermally conductive wire or at least one pair of electrically conductive wires to increase a burn surface area of a propellant grain and thus a thrust of the rocket motor. The rocket motor includes a pulse chamber containing a burnable propellant grain, a propellant inhibited center bore bonded to surfaces of the burnable propellant grain, and at least one conductive wire coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore. The conductive wire is configured for passive or active activation to ignite the propellant inhibited center bore that subsequently burns in the variable regions. The thermally conductive wire is formed of a refractory metal or refractory alloy material that enables the entire length of the wire to be heated simultaneously or nearly simultaneously when the wire is passively activated.

First claim

What is claimed is:

1. A rocket motor comprising:
a pulse chamber containing a burnable propellant grain;
a propellant inhibited center bore bonded to surfaces of the burnable propellant grain; and
at least one conductive wire coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore, the at least one conductive wire being configured for passive or active activation to ignite and ablate the propellant inhibited center bore that subsequently burns in the variable regions, wherein the at least one conductive wire is interposed between the propellant inhibited center bore and the propellant grain to increase a burn surface area of the burnable propellant grain via ablation of the propellant inhibited center bore;
wherein the propellant inhibited center bore includes an electrically-activated propellant that undergoes an electro-chemical burning reaction when electrically activated, and that inhibits combustion when not electrically activated.

2. The rocket motor according to claim 1 , wherein the at least one conductive wire is thermally conductive and passively activated by a burn front of the burnable propellant grain that directly impinges the at least one conductive wire.

3. The rocket motor according to claim 2 , wherein an entire length of the at least one conductive wire is heated simultaneously or nearly simultaneously when the at least one conductive wire is passively activated.

4. The rocket motor according to claim 1 , wherein the at least one conductive wire includes a pair of electrically conductive wires that are actively activated by an external power source arranged in the rocket motor.

5. The rocket motor according to claim 1 , wherein the at least one conductive wire extends along a length of the propellant inhibited center bore that is less than an entire length of the propellant inhibited center bore.

6. The rocket motor according to claim 1 , wherein the at least one conductive wire is formed of a refractory metal or refractory alloy material.

7. The rocket motor according to claim 1 , wherein the at least one conductive wire includes a plurality of wires arranged along the propellant inhibited center bore.

8. The rocket motor according to claim 7 , wherein the plurality of wires are arranged symmetrically about the propellant inhibited center bore.

9. The rocket motor according to claim 1 , wherein the at least one conductive wire is arranged proximate a burn surface of the burnable propellant grain.

10. The rocket motor according to claim 1 , wherein the at least one conductive wire is spaced from a burn surface of the burnable propellant grain.

11. The rocket motor according to claim 1 , wherein the at least one conductive wire includes a plurality of spaced wire segments arranged along the propellant inhibited center bore.

12. The rocket motor according to claim 1 , wherein the burnable propellant grain is an end-burning propellant grain.

13. The rocket motor according to claim 1 , wherein the rocket motor is a multi-pulse rocket motor including a second burnable propellant that is burned during a second pulse of the multi-pulse rocket motor, wherein the at least one conductive wire includes at least one second conductive wire that is coupled to the second burnable propellant.

14. The rocket motor according to claim 13 , wherein the multi-pulse rocket motor includes a third burnable propellant that is burned during a third pulse of the multi-pulse rocket motor, wherein the at least one conductive wire includes at least one third conductive wire that is coupled to the third burnable propellant.

15. A rocket motor comprising:
a pulse chamber containing a burnable propellant grain;
a propellant inhibited center bore bonded to surfaces of the burnable propellant grain;
at least one pair of electrically conductive wires coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore; and
a power supply coupled to the at least one pair of electrically conductive wires for electrically activating the at least one pair of electrically conductive wires thereby generating an electro-chemical burning reaction to ignite and ablate the propellant inhibited center bore that subsequently burns in the variable regions, wherein the at least one conductive wire is interposed between the propellant inhibited center bore and the propellant grain to increase a burn surface area of the burnable propellant grain via ablation of the propellant inhibited center bore;
wherein the propellant inhibited center bore includes an electrically-activated propellant that undergoes the electro-chemical burning reaction when electrically activated, and that inhibits combustion when not electrically activated.

16. The rocket motor according to claim 15 , wherein the rocket motor is a multi-pulse rocket motor including a second burnable propellant that is burned during a second pulse of the multi-pulse rocket motor, wherein at least one second pair of electrically conductive wires is arranged in a second pulse chamber.

17. A method of increasing a burn surface area of a propellant grain in a rocket motor, the method comprising:
selecting a length, number, refractory metal material, and arrangement of at least one conductive wire to increase a burn surface area in a rocket motor;
coupling the at least one conductive wire to a burnable propellant grain by arranging the at least one conductive wire in variable regions along a propellant inhibited center bore of the burnable propellant grain in a pulse chamber;
igniting the burnable propellant grain;
activating the at least one conductive wire; and
igniting and ablating the propellant inhibited center bore via activation of the at least one conductive wire, wherein the at least one conductive wire is interposed between the propellant inhibited center bore and the propellant grain to increase a burn surface area of the burnable propellant grain via ablation of the propellant inhibited center bore, wherein the propellant inhibited center bore includes an electrically-activated propellant that undergoes an electro-chemical burning reaction when electrically activated to subsequently burn in the variable regions, and that inhibits combustion when not electrically activated.

18. The method according to claim 17 further comprising passively activating at least one thermally conductive wire using a burn front of the burnable propellant grain that directly impinges the at least one thermally conductive wire; and
heating simultaneously or nearly simultaneously an entire length of the at least one thermally conductive wire when the at least one thermally conductive wire is activated.

19. The method according to claim 17 further comprising actively activating at least one pair of electrically activated conductive wires via a power supply arranged in the rocket motor.

20. The method according to claim 17 further comprising:
coupling at least one second conductive wire to a second burnable propellant grain that is burned during a second pulse of the rocket motor;
igniting the second burnable propellant grain; and
activating the at least one second conductive wire.

Assignees

• Raytheon Co

Inventors

• Koehler Frederick B
• Meisner Mark J
• Vollin Jeff L

Classifications

• F42B15/10

  Missiles having a trajectory only in the air · CPC title

• 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

• F02K9/28

  having two or more propellant charges with the propulsion gases exhausting through a common nozzle · CPC title

• F42B10/38

  Range-increasing arrangements (F42B10/34, F42B14/06 {and F42B15/105} take precedence) · CPC title