Thermally initiated variable venting system for rocket motor

Patent metadata

Field	Value
Publication number	US-10830181-B2
Application number	US-201816136125-A
Country	US
Kind code	B2
Filing date	Sep 19, 2018
Priority date	Sep 19, 2018
Publication date	Nov 10, 2020
Grant date	Nov 10, 2020

Abstract

A thermally initiated variable venting system may comprise a first linear shape charge (LSC) coupled to a first sensor and a second LSC coupled to a second sensor. An upper apex of the second LSC may be disposed within a lower apex of the first LSC. The output of the system may vary depending on whether the event is fast cook-off (FCO) or slow cook-off (SCO).

First claim

What is claimed is:

1. A thermally initiated variable venting system for a rocket motor case, comprising:
a first linear shape charge (LSC) coupled to a first sensor; and
a second LSC coupled to a second sensor;
wherein the first LSC radially overlaps the second LSC;
the first sensor is configured to activate to ignite the first LSC in response to at least a portion of the first sensor reaching a first temperature;
the second sensor is configured to activate to ignite the second LSC in response to at least a portion of the second sensor reaching a second temperature;
the thermally initiated variable venting system configured to project a molten jet towards the rocket motor case in response to at least one of the first LSC being ignited by the first sensor and the second LSC being ignited by the second sensor.

2. The thermally initiated variable venting system of claim 1 , wherein the molten jet is greater in response to the first LSC being ignited by the first sensor.

3. The thermally initiated variable venting system of claim 2 , wherein the molten jet is configured to cut a slot through a motor case in response to the first LSC being ignited by the first sensor.

4. The thermally initiated variable venting system of claim 2 , wherein the molten jet is configured to cut a trench into a motor case in response to the second LSC being ignited by the second sensor.

5. The thermally initiated variable venting system of claim 2 , wherein at least one of a velocity, a pressure, and a temperature of the molten jet is greater in response to the first LSC being ignited by the first sensor than in response to the second LSC being ignited by the second sensor.

6. The thermally initiated variable venting system of claim 1 , wherein the molten jet is generated by a detonation wave that travels in a direction perpendicular to the molten jet.

7. The thermally initiated variable venting system of claim 1 , wherein the first temperature is less than the second temperature.

8. The thermally initiated variable venting system of claim 1 , wherein the first sensor comprises a slow cook off (SCO) sensor and the second sensor comprises a fast cook off (FCO) sensor.

9. The thermally initiated variable venting system of claim 1 , wherein the first LSC comprises:
a sheath defining a main charge cavity; and
an explosive charge material contained in the main charge cavity.

10. The thermally initiated variable venting system of claim 9 , wherein the sheath comprises a hollowed chevron-shaped cross-section that defines the main charge cavity, the chevron-shaped cross-section defining an upper apex and a lower apex, and an upper apex of the second LSC is disposed in the lower apex of the first LSC.

11. A rocket motor, comprising:
a rocket motor case;
a cover coupled to the rocket motor case and extending longitudinally along an outer surface of the rocket motor case;
a channel disposed in the cover, an opening of the channel facing the rocket motor case;
a first linear shape charge (LSC) coupled to a first sensor, at least a portion of the first LSC disposed in the channel; and
a second LSC coupled to a second sensor, at least a portion of the second LSC disposed in the channel;
wherein the second LSC is disposed between the first LSC and the rocket motor case;
the first sensor is configured to activate to ignite the first LSC in response to at least a portion of the first sensor reaching a first temperature;
the second sensor is configured to activate to ignite the second LSC in response to at least a portion of the second sensor reaching a second temperature;
wherein a molten jet is projected from the opening in the channel in response to at least one of the first LSC being ignited by the first sensor and the second LSC being ignited by the second sensor.

12. The rocket motor of claim 11 , wherein the molten jet is configured to cut a slot through a motor case in response to the first LSC being ignited by the first sensor.

13. The rocket motor of claim 11 , wherein the molten jet is configured to cut a trench into a motor case in response to the second LSC being ignited by the second sensor.

14. The rocket motor of claim 11 , wherein at least one of a velocity, a pressure, and a temperature of the molten jet is greater in response to the first LSC being ignited by the first sensor than in response to the second LSC being ignited by the second sensor.

15. The rocket motor of claim 11 , wherein the first temperature is less than the second temperature.

16. The rocket motor of claim 11 , wherein the first sensor comprises a slow cook off (SCO) sensor and the second sensor comprises a fast cook off (FCO) sensor.

17. The rocket motor of claim 11 , wherein the first LSC comprises:
a sheath defining a main charge cavity; and
an explosive charge material contained in the main charge cavity.

18. The rocket motor of claim 17 , wherein the sheath comprises a hollowed chevron-shaped cross-section that defines the main charge cavity, the chevron-shaped cross-section defining an upper apex and a lower apex, and an upper apex of the second LSC is disposed in the lower apex of the first LSC.

19. A method for manufacturing a thermally initiated variable venting system, comprising:
disposing a first linear shape charge (LSC) into a channel of a cover;
disposing a second LSC into the channel;
coupling a second sensor to the second LSC configured to activate to ignite the second LSC in response to at least a portion of the second sensor reaching a second temperature; and
coupling the cover to a rocket motor case, wherein an opening in the channel faces the rocket motor case, the second LSC disposed between the first LSC and the rocket motor case, such that a molten jet is projected from the opening towards the rocket motor case in response to at least one of the first LSC being ignited by the first sensor and the second LSC being ignited by the second sensor.

20. The method of claim 19 , further comprising disposing an upper apex of the second LSC within a lower apex of the first LSC.

Assignees

• Goodrich Corp

Inventors

• Interiano Luis G

Classifications

• F02K9/38 Primary

  Safety devices, e.g. to prevent accidental ignition · CPC title

• F02K9/26

  Burning control {(F02K9/10, F02K9/34, F02K9/86, F02K9/92 and F02K9/94 take precedence)} · CPC title

• F42B39/14

  Explosion or fire protection arrangements on packages or ammunition (F42B39/20 {and F42B39/24} take precedence; {wall or panel structure of fireproof safes or storage containers E05G1/024}) · CPC title

• F02K9/95

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

• F02K9/08

  using solid propellants (F02K9/72 takes precedence; using semi-solid or pulverulent propellants F02K9/70) · CPC title