In orbit space transportation and recovery system
An In Orbit Transportation & Recovery System (IOSTAR™) ( 10 ) One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor ( 19 ). The IOSTAR™ includes a collapsible boom ( 11 ) connected at one end to a propellant tank ( 13 ) which stores fuel for an electric propulsion system ( 12 ). This end of the boom ( 11 ) is equipped with docking hardware ( 14 ) that is able to grasp and hold a satellite ( 15 ) and as a means to refill the tank ( 13 ). Radiator panels ( 16 ) mounted on the boom ( 11 ) dissipate heat from the reactor ( 19 ). A radiation shield ( 20 ) is situated next to the reactor ( 19 ) to protect the satellite payload ( 15 ) at the far end of the boom ( 11 ). The IOSTAR™ ( 10 ) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.
1. An apparatus comprising:
a boom means ( 11 ) for providing support;
a nuclear reactor means ( 19 ) for generating heat; said nuclear reactor means ( 19 ) being coupled to said boom means ( 11 );
a payload protection means ( 20 ) for protecting a payload ( 15 ) from radiation; said payload protection means ( 20 ) being coupled to said nuclear reactor means ( 19 );
a radiator means ( 16 ) for dissipating heat; said radiator means ( 16 ) being coupled to said nuclear reactor means ( 19 );
an electric propulsion means ( 12 ) for supplying thrust; said electric propulsion means ( 12 ) being coupled to said nuclear reactor means ( 19 );
a propellant tank means ( 13 ) for storing fuel for said electric propulsion means ( 12 );
said propellant tank means ( 13 ) being coupled to said boom means ( 11 ); and
a multiple-use grasping means ( 14 ) for interacting with a plurality of different objects and being configured to partially surround one of said plurality of different objects; said grasping means for engaging and grasping said object without the need for any preconfigured docking interface on said object; said grasping means ( 14 ) extending outwardly at one end away from said boom means ( 11 ); said grasping means ( 14 ) being coupled to said boom means ( 11 ), generally at one end of said boom means ( 11 ).
2. An apparatus as recited in claim 1 , in which said nuclear reactor means ( 19 ) includes a Brayton Cycle energy converter.
3. An apparatus as recited in claim 1 , in which said payload protection means ( 20 ) includes a recuperator.
4. An apparatus as recited in claim 3 , in which said recuperator is employed as a gamma shield.
5. An apparatus as recited in claim 3 , in which said recuperator is cooled by a thermoelectric cooler.
6. An apparatus as recited in claim 1 , which may be controlled from an on-orbit controller.
7. An apparatus as recited in claim 1 , further comprising a laser used for orbital debris removal.
8. An apparatus as recited in claim 1 , which is used to produce propellant from an asteroid.
9. An apparatus as recited in claim 8 , in which ice present on said asteroid is electrolyzed to form hydrogen and oxygen.
10. An apparatus as recited in claim 8 , in which a carbonaceous material present on said asteroid is processed to form a storable propellant.
11. An apparatus as recited in claim 1 , in which a propellant is produced from water launched into orbit from Earth.
12. An apparatus as recited in claim 1 , in which a propellant is produced from a stable, storable material launched into orbit from Earth.
13. An apparatus as recited in claim 1 , further comprising:
a conductor ( 21 ); said conductor ( 21 ) for generating an electrical current.
14. Apparatus as recited in claim 13 , in which said conductor ( 21 ) is coupled to said boom ( 11 ).
15. An apparatus as recited in claim 13 , in which said conductor ( 21 ) is coupled to said radiator ( 16 ).
16. An apparatus as recited in claim 13 , in which said electrical current is consumed.
17. An apparatus as recited in claim 13 , in which said electrical current is conveyed to another satellite.
18. An apparatus as recited in claim 13 , in which an opposite electrical current is imparted into said conductor ( 21 ) to change the orbit of a satellite.
19. An apparatus as recited in claim 18 , in which said opposite electrical current is used to deorbit a satellite.
20. An apparatus as recited in claim 13 , further comprising:
a plasma contactor ( 23 ); said plasma contactor ( 23 ) being coupled to said conductor ( 21 ).
21. An apparatus as recited in claim 20 , in which said plasma contactor ( 23 ) is a hollow cathode assembly.