In orbit space transportation & recovery system

• US 20110180670A1
• Filed: 02/07/2007
• Published: 07/28/2011
• Est. Priority Date: 07/30/2001
• Status: Abandoned Application

• Current Assignee: Iostar Corporation
• Original Assignee: Iostar Corporation
• Inventors: Stuart, James R., Williams, Franklin H. JR., D'Ausilio, Robert F.
• Application Number:
  US11/703,288
• Publication Number:
  US 20110180670A1
• Time in Patent Office: Days
• US Class Current: 244/159.3
• CPC Class Codes: B64G 1/1078 Maintenance satellites refuelling in space B64G1/4024
• CPC Class Codes: B64G 1/222 for deploying structures between a stowed and deployed state
• CPC Class Codes: B64G 1/2224 about multiple axes
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/2427 Transfer orbits
• CPC Class Codes: B64G 1/283 using reaction wheels
• CPC Class Codes: B64G 1/363 using sun sensors
• CPC Class Codes: B64G 1/369 using gyroscopes as attitude sensors
• CPC Class Codes: B64G 1/4024 refuelling in space
• CPC Class Codes: B64G 1/405 Ion or plasma engines per se F03H1/00
• CPC Class Codes: B64G 1/408 Nuclear spacecraft propulsion
• CPC Class Codes: B64G 1/413 Ion or plasma engines
• CPC Class Codes: B64G 1/415 Arcjets or resistojets
• CPC Class Codes: B64G 1/422 Nuclear power generation
• CPC Class Codes: B64G 1/44 using radiation, e.g. deployable solar arrays
• CPC Class Codes: B64G 1/503 Radiator panels
• CPC Class Codes: B64G 1/646 Docking or rendezvous systems refuelling in space B64G1/4024
• CPC Class Codes: B64G 1/6462 characterised by the means for engaging other vehicles
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for

Abstract

An In Orbit Transportation & Recovery System (IOSTAR™) (10) is disclosed. 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.

Claims

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 engaging a satellite above the surface of the Earth;

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 boom means (11) is a partially foldable frame which may be collapsed to fit within a launch vehicle.

3. An apparatus as recited in claim 1, which may be launched into orbit using a single launch vehicle.

4. An apparatus as recited in claim 1, in which said boom means (11) can be folded into a launch vehicle, and then be deployed in its fully extended position after launch.

5. An apparatus as recited in claim 4, in which said launch vehicle is expendable.

6. An apparatus as recited in claim 4, in which said launch vehicle is reusable.

7. An apparatus as recited in claim 4, in which said reusable launch vehicle is a United States Space Shuttle.

8. An apparatus as recited in claim 1, in which said boom means (11) also functions as a radiator means (16).

9. An apparatus as recited in claim 1, in which said radiator means (16) also provides structural support and takes the place of said boom means (11).

10. An apparatus as recited in claim 1, which is able to perform autonomous position and attitude control.

11. An apparatus as recited in claim 1, in which said satellite is a satellite (15).

12. An apparatus as recited in claim 1, further including a RADAR unit.

13. An apparatus as recited in claim 1, further including a LIDAR unit.

14. An apparatus as recited in claim 1, which is capable of rendezvous with a satellite (15) in orbit around the Earth.

15. An apparatus as recited in claim 14, which is capable of navigation in orbit around the Earth

16. An apparatus as recited in claim 1, which is capable of rendezvous with a satellite beyond Earth orbit.

17. An apparatus as recited in claim 15, which is capable of navigation beyond Earth orbit.

18. An apparatus as recited in claim 1, including an on-board sensor for performing a satellite rendezvous.

19. An apparatus as recited in claim 1, including an on-board sensor for performing remote sensing.

20. An apparatus as recited in claim 14, including an on-board sensor for performing remote sensing of a satellite in Earth orbit.

21. An apparatus as recited in claim 17, including an on-board sensor for performing remote sensing of a satellite beyond Earth orbit.

22. An apparatus as recited in claim 1, which is capable of docking with a satellite in orbit.

23. An apparatus as recited in claim 1, which is capable of docking with a satellite beyond Earth orbit.

24. An apparatus as recited in claim 1, including on-board sensor for performing a satellite docking maneuver.

25. An apparatus as recited in claim 1, in which said multiple-use grasping means (14) is not permanently affixed to a payload (15).

26. An apparatus as recited in claim 1, in which said radiation shield means (20) incorporates multiple zone shielding to minimize mass.

27. An apparatus as recited in claim 1, further including a shield to provide protection from impact with a satellite (15) in space.

28. An apparatus as recited in claim 1, in which said radiator means (16) is a pumped fluid loop.

29. An apparatus as recited in claim 1, in which said propellant tank means (13) may be refilled using a separate service vehicle.

30. An apparatus as recited in claim 1, in which said propellant tank means (13) can be refilled in a relatively low gravity environment.

31. An apparatus as recited in claim 1, in which said propellant tank means (13) may be filled with multiple propellants.

32. An apparatus as recited in claim 1, which may be controlled from a terrestrial operations center.

33. An apparatus as recited in claim 1, which is completely constructed on Earth.

34. An apparatus as recited in claim 1, in which said multiple-use grasping means (14) may grasp a payload (15) after launch.

35. An apparatus as recited in claim 1, in which said multiple-use grasping means (14) may release a payload (15) after launch.

36. An apparatus as recited in claim 1, in which said multiple-use grasping means (14) is adapted to seize a satellite (15) in Earth orbit so it may be transported to a different orbit.

37. An apparatus as recited in claim 1, in which said multiple-use grasping means (14) is adapted to seize a satellite (15) in Earth orbit to transport said satellite (15) to a different position.

38. An apparatus as recited in claim 1, in which said grasping means (14) is adapted to engage a satellite (15) at a payload launch vehicle interface.

39. An apparatus as recited in claim 1, in which said grasping means (14) is adapted to seize a satellite (15) in Earth orbit to transport said satellite (15) to another celestial body.

40. An apparatus as recited in claim 1, in which said grasping means (14) is adapted to seize a satellite (15) in Earth orbit so it may be de-orbited.

41. An apparatus as recited in claim 1, in which said grasping means (14) is adapted to seize a satellite (15) in Earth orbit so it may be transported for retrieval and repair.

42. An apparatus as recited in claim 41, in which said satellite (15) is placed in an operational orbit by moving along an incremental, expanding, generally spiral pathway.

43. An apparatus comprising:

a collapsible boom (11);

said boom being configured to collapse to fit within a launch vehicle and then expand once deployed in orbit;

a nuclear reactor (19) for generating heat;

said nuclear reactor (19) being mounted at one end of said collapsible boom (11);

an energy converter (22) coupled to said nuclear reactor (19) for generating electrical power;

a payload protection shield (20);

said payload protection shield (20) being disposed between a payload (15) and said nuclear reactor (19);

a radiator (16) for dissipating heat;

said radiator (16) being connected to said energy converter (22);

an ion propulsion system (12);

said ion propulsion system (12) being connected to said nuclear reactor (19);

a propellant tank (13) for storing fuel for said ion propulsion system (12);

said propellant tank (13) being coupled to said collapsible boom (11); and

a multiple-use docking device (14) for engaging a satellite (15) above the surface of the Earth.

44. A method of building an orbital facility comprising the steps of:

providing a boom means (11) for providing support;

adding a nuclear reactor means (19) for generating heat;

said nuclear reactor means (19) being coupled to said boom means (11);

adding 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);

adding a radiator means (16) for dissipating heat;

said radiator means (16) being coupled to said nuclear reactor means (19);

adding an ion propulsion system (12) for supplying thrust;

said ion propulsion system (12) being coupled to said nuclear reactor means (19);

adding a propellant tank means (13) for storing propellant for said ion propulsion system (12);

said propellant tank means (13) being coupled to said boom means (11); and

adding a multiple-use grasping means (14) for engaging a satellite (15) above the surface of the Earth;

said grasping means (14) being coupled to said boom means (11).