초록 ▼

An invention is provided for a dual mode hybrid electric thruster propulsion system. The dual mode hybrid electric thruster provides low thrust using ion/plasma exhaust only, and high thrust by mixing a neutral molecular gas with the ion/plasma exhaust. The dual mode hybrid electric thruster include

An invention is provided for a dual mode hybrid electric thruster propulsion system. The dual mode hybrid electric thruster provides low thrust using ion/plasma exhaust only, and high thrust by mixing a neutral molecular gas with the ion/plasma exhaust. The dual mode hybrid electric thruster includes a main propellant duct defining a main propellant intake. Coupled to the main propellant duct is an accelerating element, which includes an ionization chamber and an exhaust output. In addition, a momentum exchange zone is located at the exhaust output of the accelerating element. The momentum exchange zone includes a secondary propellant duct defining a secondary propellant intake, which provides a secondary propellant into the momentum exchange zone. In high-thrust mode, the momentum exchange zone exchanges momentum between high velocity ions from the accelerating element with atoms of the secondary propellant.

대표청구항 ▼

What is claimed is: 1. A propulsion system comprising: a main propellant duct defining a main propellant intake for providing a main propellant; an accelerating element coupled to the main propellant duct, the accelerating element having an ionization chamber for ionizing the main propellant and an

What is claimed is: 1. A propulsion system comprising: a main propellant duct defining a main propellant intake for providing a main propellant; an accelerating element coupled to the main propellant duct, the accelerating element having an ionization chamber for ionizing the main propellant and an exhaust output for high velocity ions of the main propellant from the accelerating element; and a momentum exchange zone located at the exhaust output of the accelerating element, the momentum exchange zone having a secondary propellant duct defining a secondary propellant intake, wherein the secondary propellant duct provides a secondary propellant into the momentum exchange zone where momentum is exchanged from the high velocity ions from the accelerating element to atoms of the secondary propellant. 2. A propulsion system as recited in claim 1, wherein the accelerating element includes a heating element and an ion-optics system to accelerate ions. 3. A propulsion system as recited in claim 1, wherein the accelerating element includes magnetic windings which produce a magnetic field to accelerate ions. 4. A propulsion system as recited in claim 1, wherein the momentum exchange zone exchanges momentum between high velocity ions from the accelerating element with atoms of the secondary propellant. 5. A propulsion system as recited in claim 1, further comprising a throttle coupled to the secondary duct, the throttle capable of adjusting a flow rate of the secondary propellant into the momentum exchange zone. 6. A propulsion system as recited in claim 1, wherein the secondary propellant is a neutral gas. 7. A propulsion system as recited in claim 6, wherein the neutral gas is xenon. 8. A method for providing propulsion comprising the operations of: providing a main propellant to an accelerating element having an ionization chamber and an exhaust output; ionizing the main propellant and accelerating the ions through the exhaust output of the accelerating element; and providing a secondary propellant into a momentum exchange zone located at the exhaust output of the accelerating element, wherein momentum is exchanged from high velocity ions from the accelerating element to atoms of the secondary propellant. 9. A method as recited in claim 8, wherein the accelerating element heats the main propellant and accelerates ions through an ion-optics system. 10. A method as recited in claim 8, wherein the accelerating element produces a magnetic field to accelerate ions into the momentum exchange zone. 11. A method as recited in claim 8, further comprising the operation of adjusting a flow rate of the secondary propellant into the momentum exchange zone to adjust thrust. 12. A method as recited in claim 8, wherein the secondary propellant is a neutral gas. 13. A method as recited in claim 12, wherein the neutral gas is xenon. 14. A propulsion system comprising: means for providing a main propellant to an accelerating element having an ionization chamber and an exhaust output; means for ionizing the main propellant and accelerating the ions through the exhaust output of the accelerating element; and means for providing a secondary propellant into a momentum exchange zone located at the exhaust output of the accelerating element, wherein momentum is exchanged from high velocity ions from the accelerating element to atoms of the secondary propellant. 15. A propulsion system as recited in claim 14, wherein the accelerating element includes a means for heating the main propellant and an ion-optics means for accelerating ions. 16. A propulsion system as recited in claim 14, wherein the accelerating element includes a means for producing a magnetic field to accelerate ions into the momentum exchange zone. 17. A propulsion system as recited in claim 14, further comprising a means for adjusting a flow rate of the secondary propellant into the momentum exchange zone to adjust thrust. 18. A propulsion system as recited in claim 14, wherein the secondary propellant is a neutral gas. 19. A propulsion system as recited in claim 18, wherein the neutral gas is xenon. 20. A propulsion system as recited in claim 18, wherein the neutral gas is argon.