초록 ▼

An In Orbit Transportation & Recovery System (IOSTAR짰) (10) One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR짰 includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric pro

An In Orbit Transportation & Recovery System (IOSTAR짰) (10) One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR짰 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 IOSTAR짰 (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.

대표청구항 ▼

What is claimed is: 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 paylo

What is claimed is: 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.