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The thrust of a rocket motor can be varied while maintaining efficiency over a range of pressure ratios using a design that allows for changing the relative position of a plug and a combustion chamber exit. The plug or the chamber exit may be attached to an adaptive control system for position modi

The thrust of a rocket motor can be varied while maintaining efficiency over a range of pressure ratios using a design that allows for changing the relative position of a plug and a combustion chamber exit. The plug or the chamber exit may be attached to an adaptive control system for position modification. The plug may be positioned in a plug nozzle configuration or in an expansion-deflection (ED) configuration. In either configuration, the elongated downstream portion of the plug allows for efficiency over a wide range of pressure ratios, while ability to change plug position with respect to the chamber exit allows adjustment of rocket thrust.

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We claim: 1. A rocket motor with a combustion chamber configured such that a propellant will flow out of the combustion chamber in a downstream direction, said rocket motor comprising: an exit formed at a downstream end of said rocket motor wherein the exit forms a rectangular opening; a plug with

We claim: 1. A rocket motor with a combustion chamber configured such that a propellant will flow out of the combustion chamber in a downstream direction, said rocket motor comprising: an exit formed at a downstream end of said rocket motor wherein the exit forms a rectangular opening; a plug with an elongated downstream portion; a position control apparatus that modifies a relative position of the plug and the exit, said position control apparatus interacting with an electromagnetic suspension mechanism, a flexible disk diaphragm, or a flexible mesh to control a position of said plug. 2. The rocket motor of claim 1 wherein said elongated downstream portion converges to form a spike. 3. The rocket motor of claim 1 wherein said elongated downstream portion is truncated. 4. The rocket motor of claim 1 wherein the propellant is in a solid state prior to combustion. 5. The rocket motor of claim 1 wherein said plug is positioned within said exit in an expansion-deflection (ED) nozzle configuration. 6. The rocket motor of claim 1, wherein said position control apparatus comprises a rod that extends from an upstream portion of said rocket motor. 7. A rocket motor with a combustion chamber configured such that a propellant will flow out of the combustion chamber in a downstream direction, said rocket motor comprising: an exit formed at a downstream end of said rocket motor; a plug with an elongated downstream portion, wherein said plug is positioned within said exit in an expansion-deflection (ED) nozzle configuration; a tapered rod upstream of said plug; and a position control apparatus that modifies a relative position of the plug and the exit, said position control apparatus interacting with an electromagnetic suspension mechanism, a flexible disk diaphragm, an electronic control mechanism, or a flexible mesh to control a position of said plug. 8. A rocket motor with a combustion chamber configured such that a propellant will flow out of the combustion chamber in a downstream direction, said rocket motor comprising: an exit formed at a downstream end of said rocket motor; a plug with an elongated downstream portion, wherein said plug is positioned within said exit in an expansion-deflection (ED) nozzle configuration; a notched rod upstream of said plug; and a position control apparatus that modifies a relative position of the plug and the exit, said position control apparatus interacting with an electromagnetic suspension mechanism, a flexible disk diaphragm, an electronic control mechanism, or a flexible mesh to control a position of said plug. 9. An apparatus for controlling thrust of a rocket motor with a combustion chamber configured such that a propellant will flow out of the combustion chamber in a downstream direction, said apparatus comprising: a plug means that is positioned within an exit in an expansion-deflection (ED) nozzle configuration; a tapered rod means upstream of said plug means; an elongated downstream portion of said plug means, said elongated downstream portion forming a nozzle for imparting thrust to said rocket motor a position modification means for axially modifying the relative position of said plug and the exit through which the propellant passes as it departs the combustion chamber, said position modification means interacting with an electromagnetic suspension mechanism, a flexible disk diaphragm, an electronic control mechanism, or a flexible mesh to control a position of said plug. 10. The apparatus for controlling thrust of a rocket motor of claim 9 wherein the propellant is in a solid state prior to combustion. 11. An apparatus for controlling thrust of a rocket motor with a combustion chamber configured such that a propellant will flow out of the combustion chamber in a downstream direction, said apparatus comprising: a plug means that is positioned within an exit in an expansion-deflection (ED) nozzle configuration; a notched rod means upstream of said plug means; an elongated downstream portion of said plug means, said elongated downstream portion forming a nozzle for imparting thrust to said rocket motor; a position modification means for axially modifying the relative position of said plug and the exit through which the propellant passes as it departs the combustion chamber, said position modification means interacting with an electromagnetic suspension mechanism, a flexible disk diaphragm, an electronic control mechanism, or a flexible mesh to control a position of said plug. 12. A rocket motor with a combustion chamber configured such that a propellant will flow out of the combustion chamber in a downstream direction, said rocket motor comprising: an exit formed at a downstream end of said rocket motor wherein said exit is formed as a separate piece that is attached to a surrounding housing; a plug with an elongated downstream portion; a position control apparatus that modifies a relative position of the plug and the exit, said position control apparatus interacting with an electromagnetic suspension mechanism, a flexible disk diaphragm, or a flexible mesh to control a position of said plug. 13. A rocket motor with a combustion chamber configured such that a propellant will flow out of the combustion chamber in a downstream direction, said rocket motor comprising: an exit formed at a downstream end of said rocket motor; a plug with an elongated downstream portion; a position control apparatus that modifies a relative position of the plug and the exit, said position control apparatus interacting with an electromagnetic suspension mechanism, a flexible disk diaphragm, an electronic control mechanism, or a flexible mesh to control a position of said plug; wherein said position control apparatus includes computerized controls that modify said relative position to adapt to ambient pressures to provide a predictable rocket speed. 14. The rocket motor of claim 13, wherein said position control apparatus includes computerized controls that modify said relative position to account for erosion of said plug and said exit. 15. A rocket motor with a combustion chamber configured such that a propellant will flow out of the combustion chamber in a downstream direction, said rocket motor comprising: an exit formed at a downstream end of said rocket motor; a plug with an elongated downstream portion; a position control apparatus that modifies a relative position of the plug and the exit, said position control apparatus interacting with an electromagnetic suspension mechanism, a flexible disk diaphragm, an electronic control mechanism, or a flexible mesh to control a position of said plug; wherein said position control apparatus includes computerized controls that modify said relative position to cause said rocket motor to smolder.