Integral variable performance propellant grain
AssigneeGoodrich Corporation
InventorsPaul Parinas, Brian Wilson
Life of this patent
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Abstract
A solid propellant rocket motor may comprise a core-burning propellant grain extending along a longitudinal axis of the solid propellant rocket motor between an exhaust end of the solid propellant rocket motor and a forward end of the solid propellant rocket motor, a first burn inhibitor layer surrounding the core-burning propellant grain, an end-burning propellant grain surrounding the first burn inhibitor layer, a second burn inhibitor layer surrounding the end-burning propellant grain, and an aperture at least partially defined by the first burn inhibitor layer. The end-burning propellant grain is ignited by the core-burning propellant grain via the aperture.
Claims20
A solid propellant rocket motor, comprising:
- a core-burning propellant grain extending along a longitudinal axis of the solid propellant rocket motor between an exhaust end of the solid propellant rocket motor and a forward end of the solid propellant rocket motor;
- a first burn inhibitor layer surrounding the core-burning propellant grain;
- an end-burning propellant grain surrounding the first burn inhibitor layer;
- a second burn inhibitor layer surrounding the end-burning propellant grain;
- and
- an aperture at least partially defined by the first burn inhibitor layer;
- wherein the end-burning propellant grain is ignited by the core-burning propellant grain via the aperture.
A method for manufacturing a solid propellant rocket motor, comprising:
- disposing a core-burning propellant grain in a first chamber at least partially defined by a first burn inhibitor layer;
- disposing an end-burning propellant grain in a second chamber at least partially defined by a second burn inhibitor layer;
- and
- disposing the first chamber to be in fluid communication with the second chamber via an aperture;
- the solid propellant rocket motor configured such that the end-burning propellant grain is ignited by the core-burning propellant grain via the aperture.
A solid propellant rocket motor, comprising:
- a first burn inhibitor layer defining a first chamber;
- a core-burning propellant grain disposed in the first chamber;
- a second burn inhibitor layer defining a second chamber;
- an end-burning propellant grain disposed in the second chamber;
- and
- an aperture, whereby the first chamber is in fluid communication with the second chamber;
- wherein the end-burning propellant grain is ignited by the core-burning propellant grain via the aperture.
Dependencies are inferred from the claim text.