Multi-pulse rocket propulsion motor
AssigneeExquadrum, Inc.
InventorKevin E. Mahaffy
Life of this patent
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Abstract
A multi-pulse rocket propulsion motor for use with vehicles, such as space vehicles like satellites, rockets, and the like. The propulsion motor is a modular system that is capable of providing a plurality of discrete, controllable propulsion pulses. The propulsion motor can be used for primary propulsion of the vehicle and/or as a maneuvering thruster of the vehicle. The propulsion motor includes a plurality of propellant housings each containing a combustible propellant grain, a discharge plenum defining a plenum volume in communication with the discharge of each propellant housing, and a nozzle downstream from and in fluid communication with the plenum volume.
Claims23
A rocket propulsion motor, comprising:
- a plurality of propellant housings each containing a combustible propellant;
- each propellant housing having a first end, a second end, and a discharge orifice at the first end through which combustion gas resulting from combustion of the combustible propellant is discharged, each one of the discharge orifices having a discharge axis along which combustion gas is discharged, the discharge axes of the discharge orifices are parallel to a longitudinal axis of each propellant housing;
- a discharge plenum defining a plenum volume, each one of the discharge orifices is placed in communication with the plenum volume of the discharge plenum whereby each propellant housing discharges combustion gas into the plenum volume;
- a nozzle downstream from and in fluid communication with the plenum volume and through which combustion gas from the plenum volume is exhausted, the nozzle having a nozzle axis;
- each discharge axis is parallel to the nozzle axis of the nozzle;
- wherein each discharge orifice has a rupturable gas seal associated therewith that prevents communication between combustion gas in the plenum volume and the combustible propellant in the associated propellant housing until the gas seal is ruptured.
A propulsion motor for a space vehicle, comprising:
- at least three propellant housings each containing solid propellant grain;
- each propellant housing having a first end, a second end, an ignition initiator that is configured to ignite the solid propellant grain, and a discharge orifice at the first end through which combustion gas resulting from combustion of the solid propellant is discharged, each one of the discharge orifices having a discharge axis along which combustion gas is discharged, the discharge axes of the discharge orifices are parallel to a longitudinal axis of each propellant housing;
- a single discharge plenum defining a plenum volume, each one of the discharge orifices is placed in communication with the plenum volume whereby each propellant housing discharges combustion gas into the plenum volume;
- each discharge orifice having a seal that temporarily prevents communication between combustion gas in the plenum volume and the solid propellant grain in the associated propellant housing;
- a nozzle connected to the discharge plenum and receiving combustion gas from the plenum volume, the nozzle having a nozzle axis, a converging section along the nozzle axis leading to a throat, and a diverging section along the nozzle axis and extending from the throat, and combustion gas from the plenum volume flows through the nozzle to generate thrust;
- and
- each discharge axis is parallel to the nozzle axis of the nozzle.
Dependencies are inferred from the claim text.