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US 8,584,443 B1Granted
Method and system for controlling solid propellant thrust
AssigneeDigital Solid State Propulsion, LLC
InventorRussell W. Carlson
Life of this patent
Estimating the term…
Abstract
The present invention relates to a solid rocket motor control system that uses state of the art electrically ignited, extinguishable and throttleable propellants. In embodiments, the control system is implemented by a software algorithm embedded in missile flight controllers and contains all control system elements and control compensation that performs thrust control for many defense and space rocket motor applications, for example.
Claims12
A method comprising:
- receiving a thrust command;
- controlling electrical power provided to a solid propellant to cause the solid propellant to output a thrust corresponding to the thrust command;
- monitoring a chamber pressure corresponding to the thrust output;
- and
- adjusting the electrical power in accordance with the monitored chamber pressure.
2 more elements
A system comprising:
- a thrust command input;
- a control loop that adjusts electrical power provided to a solid propellant to cause the solid propellant to output a thrust corresponding to the thrust command;
- and
- a pressure transducer that monitors a chamber pressure corresponding to the thrust output;
- wherein the control loop is adapted to adjust the electrical power in accordance with the monitored chamber pressure.
2 more elements
A rocket motor comprising:
- a solid propellant;
- a thrust command input;
- a controller programmed to adjusts electrical power provided to the solid propellant to cause the solid propellant to output a thrust corresponding to the thrust command;
- and
- a pressure transducer that monitors a chamber pressure corresponding to the thrust output;
- wherein the controller is programmed to adjust the electrical power in accordance with the monitored chamber pressure.
3 more elements
Dependencies are inferred from the claim text.