Optical Energy Transfer and Conversion System

• US 20150256033A1
• Filed: 05/27/2015
• Published: 09/10/2015
• Est. Priority Date: 11/23/2010
• Status: Active Grant

• Current Assignee: Stone Aerospace, Inc.
• Original Assignee: Piedra - Sombra Corporation, Inc.
• Inventors: Stone, William C., Hogan, Bartholomew P.
• Granted Patent: US 10,261,263 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 33/00 Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
• CPC Class Codes: E21B 41/0085 Adaptations of electric power generating means for use in boreholes
• CPC Class Codes: E21B 47/135 using light waves, e.g. infrared or ultraviolet waves
• CPC Class Codes: G02B 6/3604 Rotary joints allowing relative rotational movement between opposing fibre or fibre bundle ends
• CPC Class Codes: G02B 6/4268 Cooling of semiconductor devices H01L23/24; of electric apparatus H05K7/20; of instruments G12B15/00
• CPC Class Codes: G02B 6/4296 coupling with sources of high radiant energy, e.g. high power lasers, high temperature light sources
• CPC Class Codes: G02B 6/4415 Cables for special applications G02B6/4429, G02B6/4439, G02B6/4479 take precedence
• CPC Class Codes: G02B 6/4436 Heat resistant
• CPC Class Codes: G02B 6/4458 Coiled, e.g. extensible helix
• CPC Class Codes: H02J 50/30 using light, e.g. lasers
• CPC Class Codes: H02J 50/90 involving detection or optimisation of position, e.g. alignment
• CPC Class Codes: H10N 10/13 characterised by the heat-exchanging means at the junction

Abstract

An optical power transfer system for launching a spacecraft into low Earth orbit comprising a ground-based laser power generation station and a launch vehicle optically connected thereto. The generation station is capable of generating high optical power in the range of kilowatts to tens of megawatts and transferring the optical power generated to a launch vehicle to generate thrust. The generation station comprises a high power source, a chilling station, a laser, optical fiber, and at least one coupler. The launch vehicle comprises an actively cooled fiber spooler mounted thereon with a length of fiber for transmission of high optical energy circumscribing at least part thereof. The launch vehicle also contains a working fluid and fluid reservoir, a thruster assembly, an air intake and a storage chamber. In alternative embodiments, the launch vehicle may contain a beam switch assembly, multiple fiber spoolers and multiple thruster assemblies wherein at least one thruster assembly is gimbaled.

Claims

1. An optical power transfer system for launching a spacecraft into low Earth orbit comprising:

a ground-based laser power generation station; and

a launch vehicle optically connected to said ground-based laser power generation station.

2. The system of claim 1 wherein said ground-based laser power generation station further comprises:

a high power source;

a chilling station;

a laser connected to said high power source and said chilling station; and

an optical fiber connected to said laser at a first end and to said launch vehicle at a second end.

3. The system of claim 2 wherein said ground-based laser power generation station further comprises at least one coupler connected to said optical fiber, said at least one coupler positioned inline between said laser and said launch vehicle.

4. The system of claim 3 wherein said ground-based laser power generation station is capable of generating high optical power is in the range of kilowatts to tens of megawatts.

5. The system of claim 1 wherein said launch vehicle further comprises:

an actively cooled fiber spooler mounted on said launch vehicle;

a length of fiber for transmission of high optical energy, said length of fiber circumscribing at least part of said actively cooled fiber spooler and wherein said optical energy received by said launch vehicle is converted to another form of energy usable by said launch vehicle;

a thruster assembly optically connected to said actively cooled fiber spooler;

an air intake in fluid communication with said actively cooled fiber spooler and with said thruster assembly; and

a storage chamber in fluid communication with said actively cooled fiber spooler and with said thruster assembly.

6. The system of claim 5 wherein said thruster assembly further comprises:

a laser injection interface;

a plurality of beam forming optics optically connected to said laser injection interface;

a reaction chamber optically connected to said plurality of beam forming optics;

a refractory target contained within said reaction chamber; and

a nozzle connected to and extending distally from said reaction chamber, said nozzle directing thrust generated away from said launch vehicle.

7. The system of claim 6 further comprising an inline coupler optically connected to a second length of fiber, said inline coupler positioned between said actively cooled fiber spooler and said thruster assembly.

8. The system of claim 7 further comprising a working fluid.

9. The system of claim 8 wherein said working fluid is stored in said storage chamber.

10. The system of claim 6 wherein said refractory target is a plasma core impinged by a focused beam.

11. The system of claim 6 wherein said refractory target is a plurality of heat exchangers impinged by an expanded beam.

12. The system of claim 4 wherein said ground-based laser power generation station further comprises a drum spooler.

13. The system of claim 12 wherein said drum spooler is servo-controlled.

14. The system of claim 13 wherein said drum spooler is actively cooled.

15. A method of launching a spacecraft into low Earth orbit using an optical power transfer system, said method comprising the steps of:

generating optical power at a base station;

transmitting said optical power to a launch vehicle via an actively cooled fiber spooler on said launch vehicle, said transmitting step performed using an optical fiber;

converting said optical power received by said launch vehicle to another form of energy usable by said launch vehicle;

optically focusing said optical power into a reaction chamber to impinge on a refractory target;

regeneratively feeding a working fluid to a heat exchanger contained within said actively cooled fiber spooler;

pre-heating of said working fluid within said heat exchanger;

injecting said working fluid into said reaction chamber;

heating and expanding said working fluid within said reaction chamber; and

channeling the exhaust through a rocket nozzle to produce thrust.

16. The method of launching a spacecraft into low Earth orbit, as recited in claim 15, wherein said refractory target is a plasma core impinged by a focused beam.

17. The method of launching a spacecraft into low Earth orbit, as recited in claim 15, wherein said refractory target is a plurality of heat exchangers impinged by an expanded beam.

18. The method of launching a spacecraft into low Earth orbit, as recited in claim 15, wherein during initial flight of said launch vehicle, said working fluid for said injecting step is comprised of atmospheric air.

19. The method of launching a spacecraft into low Earth orbit, as recited in claim 18, wherein at approximately 20-30 kilometers of altitude of said launch vehicle, said working fluid for said injecting step is comprised of a mixture of atmospheric air and water or other fuel.

20. The method of launching a spacecraft into low Earth orbit, as recited in claim 18, wherein at exo-atmospheric flight of said launch vehicle, said working fluid for said injecting step is comprised solely of water.

21. The method of launching a spacecraft into low Earth orbit, as recited in claim 15, wherein said optical power is in the range of kilowatts to tens of megawatts.

22. A method of recovery of optical fiber expended during launch of a spacecraft, said method comprising the steps of:

affixing a first high energy connector to a drum spooler, said first high energy connector optically connected to a spacecraft;

launching of said spacecraft;

releasing an optical fiber connected at one end to said spacecraft from said spacecraft during launch of said spacecraft said optical fiber adapted for transmission of high optical energy sufficient to launch said spacecraft;

engaging said optical fiber expended from said spacecraft to said drum spooler following said launching step; and

collecting said optical fiber for processing, cleaning and rewinding for future use.

23. The method of recovery of optical fiber, as recited in claim 22, wherein said collecting step is performed by the rotation of said drum spooler.

24. The method of claim 23 wherein said drum spooler is servo-controlled.

25. The method of claim 24 wherein said drum spooler is actively cooled.

26. An optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit comprising:

a high power laser source;

a launch vehicle;

at least one actively cooled fiber spooler mounted on said launch vehicle and optically connected to said high power laser source;

a first optical fiber connected at one end to said high power laser source and at the other end to said at least one actively cooled fiber spooler, said at least one actively cooled fiber spooler having a length of said first optical fiber circumscribing at least part thereof;

a fiber guide extending distally from said at least one actively cooled fiber spooler, said fiber guide radially enclosing a portion of said first optical fiber;

a beam switch assembly optically connected to said at least one actively cooled fiber spooler; and

a plurality of thruster assemblies optically connected to said beam switch assembly.

27. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 26, further comprising an inline optical coupler optically connected at one end to said at least one actively cooled fiber spooler and optically connected to said beam switch assembly at the opposite end.

28. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 27, wherein said beam switch assembly further comprises:

at least one coupler optically connected to said at least one actively cooled fiber spooler;

at least one beam forming optics for transmission of high optical energy transmitted from said at least one coupler;

a rotary mirror centrally positioned to receive said high optical energy, said rotary mirror being angled to reflect said high optical energy received;

a plurality of fixed mirrors arrayed radially about said rotary mirror, said plurality of fixed mirrors angled toward said rotary mirror;

a rotary shaft connected to said rotary mirror; and

a servo motor for actuating said rotary shaft to rotate said rotary mirror.

29. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 28, wherein said at least one coupler is optically connected to said plurality of thruster assemblies.

30. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 29, wherein said plurality of thruster assemblies further comprises:

a laser injection interface optically connected to said beam switch assembly;

a plurality of beam forming optics optically connected to said laser injection interface;

a reaction chamber optically connected to said plurality of beam forming optics;

a refractory target contained within said reaction chamber; and

a nozzle connected to and extending distally from said reaction chamber, said nozzle directing thrust generated away from said launch vehicle.

31. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 30, wherein said refractory target is a plasma core impinged by a focused beam.

32. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 30, wherein said refractory target is a plurality of heat exchangers impinged by an expanded beam.

33. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 30, wherein said plurality of thruster assemblies are equally distributed radially about a centerline of said vehicle, said plurality of thruster assemblies canted at a predetermined divergence angle from said centerline.

34. An optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit comprising:

a high power laser source;

a plurality of fiber spoolers;

a first plurality of fiber having a first end connected to said high power laser source and a second end connected to said plurality of fiber spoolers;

a plurality of fiber guides extending distally from said plurality of fiber spoolers, said plurality of fiber guides partially enclosing said first plurality of fiber;

a plurality of laser injection assemblies in optical communication with said plurality of fiber spoolers;

a second plurality of fiber having a first end connected to said plurality of laser injection assemblies and a second end connected to said plurality of fiber spoolers;

at least one coupler positioned inline between said plurality of fiber spoolers and said plurality of laser injection assemblies; and

at least one thruster assembly in optical communication with said plurality of laser injection assemblies.

35. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 34, wherein said plurality of laser injection assemblies further comprises beam forming optics for directing optical energy received from said at least one coupler into at least one thruster assembly.

36. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 35, wherein said at least one thruster assembly further comprises:

a reaction chamber optically connected to said beam forming optics;

a refractory target contained within said reaction chamber; and

a nozzle connected to and extending distally from said reaction chamber, said nozzle directing thrust generated away from said launch vehicle.

37. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 36, wherein said refractory target is a plasma core impinged by a focused beam.

38. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 36, wherein said refractory target is a plurality of heat exchangers impinged by an expanded beam.

39. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 36, wherein said plurality of fiber spoolers is radially arrayed about the centerline of the launch vehicle.

40. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 39, wherein said at least one thruster assembly is positioned centrally about said centerline of said launch vehicle to create central thrust.

41. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 39, wherein said at least one thruster assembly is arrayed symmetrically about said centerline of said launch vehicle to create central thrust.

42. The optical power transfer system for launching a multiple thruster spacecraft into low Earth orbit, as recited in claim 41, wherein said at least one thruster assembly is gimbaled.