Non-line-of-sight optical power transfer system for launching a spacecraft into low earth orbit
First Claim
1. An optical power transfer system for launching a spacecraft into low Earth orbit comprising:
- a ground-based laser power generation station comprising;
a high power source;
a chilling station;
a laser connected to said high power source and said chilling station;
an optical fiber connected to said laser at a first end and to said launch vehicle at a second end; and
at least one coupler connected to said optical fiber, said at least one coupler positioned inline between said laser and said launch vehicle; and
a launch vehicle optically connected to said ground-based laser power generation station, said launch vehicle comprising;
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; and
wherein said optical connection between said launch vehicle and said ground-based laser power generation station may be direct non-line-of-sight communication.
2 Assignments
0 Petitions
Accused Products
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.
-
Citations
26 Claims
-
1. An optical power transfer system for launching a spacecraft into low Earth orbit comprising:
-
a ground-based laser power generation station comprising; a high power source; a chilling station; a laser connected to said high power source and said chilling station; an optical fiber connected to said laser at a first end and to said launch vehicle at a second end; and at least one coupler connected to said optical fiber, said at least one coupler positioned inline between said laser and said launch vehicle; and a launch vehicle optically connected to said ground-based laser power generation station, said launch vehicle comprising; 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; and
wherein said optical connection between said launch vehicle and said ground-based laser power generation station may be direct non-line-of-sight communication. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
-
-
12. 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; 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; and a plurality of thruster assemblies optically connected to said beam switch assembly. - View Dependent Claims (13, 14, 15, 16, 17, 18)
-
-
19. 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;
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. - View Dependent Claims (20, 21, 22, 23, 24, 25, 26)
-
Specification