In orbit space transportation and recovery system

• US 7,611,097 B2
• Filed: 01/10/2007
• Issued: 11/03/2009
• Est. Priority Date: 07/30/2001
• Status: Expired due to Fees

• Current Assignee: Iostar Corporation
• Original Assignee: Iostar Corporation
• Inventors: Giaccherini, Thomas N., Stuart, James R., D'Ausilio, Robert F., Williams, Franklin H. Jr.
• Primary Examiner(s): SWIATEK, ROBERT P
• Application Number:
  US11/651,826
• Publication Number:
  US 20090242704A1
• Time in Patent Office: 1,028 Days
• Field of Search: 244/158.1, 244/158.2, 244/158.9, 244/171.1, 244/172.2, 244/172.4, 244/172.5
• US Class Current: 244/171.1
• CPC Class Codes: B64G 1/1078 Maintenance satellites refueling in space B64G1/4024
• CPC Class Codes: B64G 1/2427 Transfer orbits
• 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 1/422 Nuclear power generation
• CPC Class Codes: B64G 1/503 Radiator panels
• CPC Class Codes: B64G 1/506 Heat pipes
• CPC Class Codes: B64G 1/54 Protection against radiation
• CPC Class Codes: B64G 1/646 Docking or rendezvous systems refueling in space B64G1/4024
• CPC Class Codes: G21D 5/02 Reactor and engine structurally combined, e.g. portable
• CPC Class Codes: Y02E 30/00 Energy generation of nuclear origin

Abstract

A preferred In Orbit Transportation & Recovery System (IOSTAR™) (10) includes 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. A method comprising the steps of:

a) operating a nuclear powered vehicle in orbit;

b) generating electrical energy on board said nuclear powered vehicle by a gas cooled nuclear reactor on board said nuclear powered vehicle, wherein the nuclear reactor and an energy converter, comprising a turbine and a compressor, coupled to the nuclear reactor produce at least 250 kW of sustained electrical power; and

c) conveying said electrical energy to a satellite from said nuclear powered vehicle.

2. A method as recited in claim 1, in which said electrical energy is conveyed to said satellite using a conductive link connected to another satellite.

3. A method as recited in claim 1, in which said electrical energy is conveyed to said satellite using a radiated energy beam.

4. A method as recited in claim 1, in which said electrical energy is conveyed to said satellite by first storing said electrical energy on board said nuclear powered vehicle in a storage device, and then physically delivering said storage device to said satellite.

5. A method as recited in claim 4, in which said storage device is a battery.

6. A method as recited in claim 4, in which said storage device is a fuel cell.

7. A method as recited in claim 1, in which said electrical energy is provided to a plurality of customers.

8. A method as recited in claim 7, in which said plurality of customers utilize said electrical energy on a time-share basis.

9. A method as recited in claim 1, in which the nuclear powered vehicle comprises

a) a boom;

b) said nuclear reactor coupled to said boom;

c) a radiation shield coupled to said nuclear reactor and incorporating multiple zone shielding;

d) a radiator coupled to said nuclear reactor;

e) an electric propulsion device coupled to said nuclear reactor;

f) a propellant tank storing fuel for said electric propulsion device coupled to said boom; and

g) a multiple-use grasping device capable of engaging a satellite above the surface of the Earth coupled to said boom generally at one end of said boom.

10. A method as recited in claim 1, in which the energy converter coupled to the nuclear reactor further includes a radiator and a generator.

11. A method as recited in claim 10 wherein the nuclear powered vehicle is further provided with a boom and the nuclear reactor is coupled to said boom proximate a second end of said boom opposite the first end of said boom, and wherein the nuclear powered vehicle is further provided with docking hardware proximate a first end of said boom, a radiation shield coupled to said nuclear reactor, an ion propulsion system coupled to said boom, and a propellant tank storing fuel for the ion propulsion system coupled to said boom.

12. A method of operating a nuclear powered vehicle in orbit comprising the steps of:

a) providing said nuclear powered vehicle in orbit with a radiation shield for protecting a detachable payload;

b) providing said nuclear powered vehicle with a grasping means extending outwardly therefrom at one end for docking and interacting with a satellite;

said grasping means being configured for multiple use and for interacting with a plurality of different objects;

said grasping means including a plurality of segments;

c) configuring said plurality of segments to partially surround one of said plurality of different objects and to engage and to grasp said object without the need for any preconfigured docking interface on said object;

d) generating electrical energy from a nuclear reactor onboard said nuclear powered vehicle; and

e) using said generated electrical energy to interact with at least one of a celestial body and a satellite.

13. A method as recited in claim 12, in which said electrical energy is used to move a satellite.

14. A method as recited in claim 12, in which said electrical energy is used to rescue a satellite.

15. A method as recited in claim 12, in which said electrical energy is used to repair a satellite.

16. A method as recited in claim 12, in which said electrical energy is used to transport a payload to a satellite.

17. A method as recited in claim 12, in which said electrical energy is used to transport a payload from a satellite.

18. A method as recited in claim 12, in which said electrical energy is used to transport a payload to a celestial body.

19. A method as recited in claim 12, in which said electrical energy is used to transport a payload from a celestial body.

20. A method as recited in claim 12, in which said electrical energy is sold.

21. A method as recited in claim 12, in which said electrical energy is traded.

22. A method as recited in claim 12, in which said nuclear powered vehicle is leased for a specified task.

23. A method as recited in claim 12, in which said nuclear powered vehicle is leased for a specified time.

24. A method as recited in claim 12, in which a customer who uses said nuclear powered vehicle is charged according to a specified rate.

25. A method as recited in claim 24, in which said specified rate is determined by a quantity of mass in orbit that is moved by said electrical energy.

26. A method as recited in claim 25, in which said specified rate is determined by a distance that said quantity of mass in orbit that is moved by said electrical energy.

27. A method as recited in claim 25, in which said specified rate is determined by a change in an orbital parameter that is altered by said electrical energy.

28. A method as recited in claim 27, in which said orbital parameter is altitude.

29. A method as recited in claim 27, in which said orbital parameter is apogee.

30. A method as recited in claim 27, in which said orbital parameter is perigee.

31. A method as recited in claim 27, in which said orbital parameter is inclination.