Method and apparatus to produce high specific impulse and moderate thrust from a fusion-powered rocket engine

Patent metadata

Field	Value
Publication number	US-9822769-B2
Application number	US-201314400204-A
Country	US
Kind code	B2
Filing date	May 10, 2013
Priority date	May 10, 2012
Publication date	Nov 21, 2017
Grant date	Nov 21, 2017

Abstract

A system and method for producing and controlling high thrust and desirable specific impulse from a continuous fusion reaction is disclosed. The resultant relatively small rocket engine will have lower cost to develop, test, and operate that the prior art, allowing spacecraft missions throughout the planetary system and beyond. The rocket engine method and system includes a reactor chamber and a heating system for heating a stable plasma to produce fusion reactions in the stable plasma. Magnets produce a magnetic field that confines the stable plasma. A fuel injection system and a propellant injection system are included. The propellant injection system injects cold propellant into a gas box at one end of the reactor chamber, where the propellant is ionized into a plasma. The propellant and fusion products are directed out of the reactor chamber through a magnetic nozzle and are detached from the magnetic field lines producing thrust.

First claim

The invention claimed is:

1. A system comprising a rocket engine employing nuclear fusion with thrust augmentation, the system comprising
a reactor chamber for containing a stable plasma comprising a fusion fuel;
a heating system for heating said plasma and increasing an ion energy of said plasma to at least 5 kiloelectronvolts for producing power from fusion reactions in said stable plasma;
a plurality of magnets coaxial to said reactor chamber, the plurality of magnets producing a magnetic field to confine the stable plasma and promote rapid loss of fusion products into a scrape off layer;
a fuel injection system for injecting additional quantities of said fusion fuel to sustain the power output of said fusion reaction;
a gas box at one end of said scrape off layer for ionizing a cold propellant gas into a cold propellant plasma for introduction into said scrape off layer to augment the mass of said scrape off layer, wherein said cold propellant plasma is introduced into the reactor chamber and heated in the reactor chamber by fusion reaction products to form a warm propellant plasma;
a propellant injection system for injecting said cold propellant gas into said gas box;
a magnetic nozzle, attached to the end of the reactor chamber distal from said gas box, for directing said warm propellant plasma in said scrape off layer out of said reactor chamber as expelled propellant to create thrust.

2. The system of claim 1 wherein said fusion fuel comprises deuterium and helium-3.

3. The system of claim 1 wherein said plurality of magnets in conjunction with said plasma produces a magnetic field in a field-reversed configuration.

4. The system of claim 3 wherein the magnets are superconducting magnetic coils.

5. The system of claim 4 wherein the magnets are permanent magnets.

6. The system of claim 3 wherein the fuel injection system is a neutral beam.

7. The system of claim 6 wherein the propellant is deuterium.

8. The system of claim 6 wherein the propellant is hydrogen.

9. The system of claim 6 further comprising at least one energy conversion system.

10. The system of claim 9 wherein the heating system employs radio frequency odd-parity rotating magnetic fields produced by radio frequency magnetic coils.

11. The system of claim 10 further comprising a shield for attenuating and deflecting radiation produced from fusion.

12. The system of claim 11 wherein said reactor chamber is a vacuum vessel which is transparent to radio frequencies.

13. The system of claim 1 , wherein the stable plasma has a plasma radius of approximately 25 centimeters.

14. The system of claim 1 , wherein ions in the stable plasma have an ion gyroradii of about one tenth of a plasma radius of the stable plasma.

15. The system of claim 1 , further comprising a charge exchange chamber that neutralizes the expelled propellant to form a neutral stream, and causing the neutral stream to separate from said magnetic field.

16. A method for augmenting the thrust a fusion powered rocket engine that includes a reactor chamber for containing a stable plasma comprising a fusion fuel, a plurality of magnets coaxial to the chamber, a heating system, a fuel injection system, a propellant injection system coupled to a gas box at one end of the reactor chamber, and a magnetic nozzle at the end of the chamber distal to the gas box, the method comprising:
injecting, by the fuel injection system, the fusion fuel into the reactor chamber;
heating, by the heating system, the plasma such that the fuel is ionized and heated such that a sustained nuclear fusion reaction occurs in the plasma producing power;
forming, by the magnets, a magnetic field to confine the plasma and promote rapid loss of fusion products into a scrape-off-layer;
injecting, by the propellant injection system, a cold propellant gas into the gas box;
ionizing the cold propellant gas in the gas box to form an ionized cold propellant plasma;
injecting the ionized cold propellant into the reactor chamber and converting said cold ionized propellant plasma into a warm propellant plasma to increase the mass of the scrape-off-layer, wherein the warm propellant plasma is heated by the fusion products as it flows through the scrape-off-layer;
expelling the warm propellant plasma and fusion products from the reactor chamber through the magnetic nozzle to create thrust.

17. The method according to claim 16 wherein said fusion fuel comprises deuterium and helium-3.

18. The method according to claim 16 , where in a field-reversed magnetic field configuration is produced by the plurality of magnets in conjunction with the plasma.

19. The method according to claim 18 , wherein plurality of magnets are superconducting magnetic coils.

20. The method according to claim 19 , wherein the plurality of magnets are permanent magnets.

21. The method according to claim 18 , wherein the fusion fuel is injected by a neutral beam.

22. The method according to claim 21 , wherein the injected propellant is deuterium.

23. The method according to claim 21 , wherein the injected propellant is hydrogen.

24. The method according to claim 21 , further comprising converting energy from the fusion products into electricity.

25. The method according to claim 24 , wherein the heating is accomplished by radio frequency odd-parity rotating magnetic fields produced by radio frequency magnetic coils.

26. The method according to claim 25 , wherein converting the energy is accomplished by capturing electro-magnetic radiation in the radio frequency spectrum using radio frequency magnetic coils.

27. The method according to claim 26 , further comprising attenuating and deflecting radiation produced from the fusion reaction with a shielding material.

28. The method according to claim 27 , wherein heating by radio frequencies is enabled by the use of a vacuum vessel for the reactor chamber, which is transparent to such frequencies.

29. The method of claim 16 , wherein the stable plasma has a plasma radius of approximately 25 centimeters.

30. The method of claim 16 , wherein ions in the stable plasma have an ion gyroradii of about one tenth of a plasma radius of the stable plasma.

31. The method of claim 16 , wherein the warm propellant plasma and fusion products are expelled propellant, the method further comprising forming a neutral stream by neutralizing the expelled propellant and detaching the expelled propellant from said magnetic field.

Assignees

• Princeton Satellite Systems Inc
• Univ Princeton
• Princeton Satellite Systems

Inventors

• Cohen Samuel A
• Pajer Gary A
• Paluszek Michael A
• Razin Yosef S

Classifications

• B64G1/408

  Nuclear spacecraft propulsion · CPC title

• F03H1/0093 Primary

  Electro-thermal plasma thrusters, i.e. thrusters heating the particles in a plasma (resistojets per se B64G1/415) · CPC title

• Y02E30/122

  Cross-Sectional Technologies · mapped topic

• F02K9/08

  using solid propellants (F02K9/72 takes precedence; using semi-solid or pulverulent propellants F02K9/70) · CPC title

• G21B1/052

  reversed field configuration · CPC title