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US 8,191,351 B2Granted
Insensitive rocket motor
AssigneeRaytheon Company
InventorsRichard D. Loehr, Gerald M. Turner, Jeremy C. Danforth
Life of this patent
Estimating the term…
Abstract
There is disclosed a solid fuel rocket motor including a center-perforated solid fuel grain. The solid fuel grain may be adapted to burn outwardly from a center surface facing the center perforation when ignited by a primary igniter during a normal mode of operation. The solid fuel grain may be further adapted to burn longitudinally from an end face when ignited by a secondary igniter during a safety mode of operation.
Claims22
A solid fuel rocket motor, comprising:
- a solid fuel grain;
- a primary igniter;
- and
- a secondary igniter embedded in an end surface of the solid fuel grain;
- wherein the solid fuel grain adapted to 1) burn outwardly from a center surface facing a center perforation when ignited by the primary igniter, and 2) burn longitudinally from the end face when ignited by the secondary igniter;
- wherein the secondary igniter ignites the end face of the solid fuel grain when the temperature of the secondary igniter exceeds a predetermined ignition temperature;
- wherein the rocket motor further comprises an inhibitor layer to inhibit ignition of the center surface of the solid fuel grain when the grain is ignited by the secondary igniter;
- wherein the solid fuel rocket motor produces a first level of thrust when ignited by the primary igniter;
- and
- wherein the solid fuel rocket motor produces a second level of thrust substantially lower than the first level of thrust when ignited by the secondary igniter.
7 more elements
A solid fuel rocket motor, comprising:
- a solid fuel grain having an end surface, and a center surface facing a center perforation;
- an inhibitor layer coating at least a portion of the center surface;
- a primary igniter disposed to ignite the center surface;
- a secondary igniter embedded in the end surface, and disposed to ignite the end surface;
- a case having a longitudinal axis terminating in a fore end and an aft end, the case at least partially enclosing the solid fuel grain, the primary igniter, and the secondary igniter;
- and
- a nozzle coupled to the aft end of the case proximate to the end surface of the solid fuel grain, the nozzle to exhaust combustion gases produced by combustion of the solid fuel grain;
- wherein the secondary igniter is adapted to ignite in response to externally applied heat;
- and
- wherein the secondary igniter has a first ignition temperature lower than a spontaneous ignition temperature of the solid fuel grain.
7 more elements
A solid fuel rocket motor, comprising:
- a solid fuel grain having an end surface, and a center surface facing a center perforation;
- an inhibitor layer coating at least a portion of the center surface;
- a primary igniter disposed to ignite the center surface;
- a secondary igniter disposed to ignite the end surface;
- a case having a longitudinal axis terminating in a fore end and an aft end, the case at least partially enclosing the solid fuel grain, the primary igniter, and the secondary igniter;
- and
- a nozzle coupled to the aft end of the case proximate to the end surface of the solid fuel grain, the nozzle to exhaust combustion gases produced by combustion of the solid fuel grain;
- wherein the secondary igniter is adapted to ignite in response to externally applied heat;
- wherein the secondary igniter has a first ignition temperature lower than a spontaneous ignition temperature of the solid fuel grain;
- and
- wherein the nozzle abuts the secondary igniter, but leaves a portion of the secondary igniter uncovered.
8 more elements
Dependencies are inferred from the claim text.