Orbit space transportation and recovery system

• US 7,575,199 B2
• Filed: 01/10/2007
• Issued: 08/18/2009
• 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.
• Primary Examiner(s): SWIATEK, ROBERT P
• Application Number:
  US11/651,825
• Publication Number:
  US 20070114334A1
• Time in Patent Office: 951 Days
• Field of Search: 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 outer space wherein the nuclear powered vehicle is provided with a boom, docking hardware proximate a first end of said boom used to capture a satellite, a nuclear reactor coupled to said boom proximate a second end of said boom opposite the first end of said boom, a radiation shield coupled to said nuclear reactor, and an energy converter coupled to the nuclear reactor, the nuclear reactor and energy converter producing at least 250 kW of sustained electrical power; and

b) processing information on board said nuclear powered vehicle to rescue a said satellite, wherein the nuclear powered vehicle travels to and captures the satellite from a first orbit and transfers the satellite to a second orbit, and wherein the nuclear powered vehicle approaches, connects to and transits with the satellite such that the radiation shield protects the satellite from radiation from the nuclear reactor.

2. 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 at least one other satellite;

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

d) said grasping means including a plurality of segments;

e) 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; and

f) processing information;

said processed information for interacting with at least one other satellite.

3. A method as recited in claim 2, in which said information is used to affect another satellite.

4. A method as recited in claim 2, in which said information is used to move a satellite.

5. A method as recited in claim 2, in which said information is used to transport a payload to a satellite.

6. A method as recited in claim 2, in which said information is used to transport a payload from a satellite.

7. A method as recited in claim 2, in which said information is used to transport a payload to a celestial body.

8. A method as recited in claim 2, in which said information is used to transport a payload from a celestial body.

9. A method as recited in claim 2, in which said nuclear powered vehicle for providing said information is sold.

10. A method as recited in claim 2, in which said nuclear powered vehicle for providing said information is leased for a specified task.

11. A method as recited in claim 2, in which said nuclear powered vehicle for providing said information is leased for a specified time.

12. A method as recited in claim 2, in which a customer who uses said nuclear powered vehicle for providing said information is charged according to a specified rate.

13. A method as recited in claim 2, in which said information is conveyed to another satellite.

14. A method as recited in claim 12, in which said information is conveyed to a receiver generally near a celestial body.

15. A method as recited in claim 2, in which said information is conveyed using a radio signal.

16. A method as recited in claim 2, in which said information is provided to a plurality of customers.

17. A method as recited in claim 2, in which a customer is charged for receiving said information by the number of packets conveyed.

18. A method as recited in claim 2, in which said information is used for reconnaissance.

19. A method as recited in claim 2, in which said information is used for surveillance.

20. A method comprising the steps of:

a) operating a nuclear powered vehicle in outer space wherein the nuclear powered vehicle is provided with a boom, docking hardware proximate a first end of said boom used to capture a satellite, a nuclear reactor coupled to said boom proximate a second end of said boom opposite the first end of said boom, a radiation shield coupled to said nuclear reactor, and an energy converter coupled to the nuclear reactor, the nuclear reactor and energy converter producing at least 250 kW of sustained electrical power; and

b) processing information on board said nuclear powered vehicle to repair said satellite, wherein the nuclear powered vehicle travels to and captures the satellite from a first orbit and transfers the satellite to a second orbit where the satellite is repaired, and wherein the nuclear powered vehicle approaches, connects to and transits with the satellite such that the radiation shield protects the satellite from radiation from the nuclear reactor.

21. A method of rescuing a satellite comprising the steps of:

a) operating a nuclear powered vehicle in outer space to capture the satellite while it is in a first orbit, wherein the nuclear powered vehicle is provided with a boom, docking hardware proximate a first end of said boom used to capture the satellite, a nuclear reactor coupled to said boom proximate a second end of said boom opposite the first end of said boom, a radiation shield coupled to said nuclear reactor, and an energy converter coupled to the nuclear reactor, the nuclear reactor and energy converter producing at least 250 kW of sustained electrical power; and

b) using the nuclear powered vehicle to move the satellite from its first orbit to a second orbit, and wherein the nuclear powered vehicle approaches, connects to and transits with the satellite such that the radiation shield protects the satellite from radiation from the nuclear reactor.

22. The method of claim 21 wherein the nuclear powered vehicle is further provided with an ion propulsion system coupled to said boom, a propellant tank storing fuel for the ion propulsion system coupled to said boom, and a radiator, and the energy converter comprises a turbine, a compressor and a generator.

23. The method of claim 21 wherein the first orbit is a geosynchronous orbit.

24. The method of claim 23 wherein the second orbit is a low Earth orbit.

25. A method comprising the steps of:

a) operating a nuclear powered vehicle in outer space to capture a satellite while it is in a first orbit, wherein the nuclear powered vehicle is provided with a boom;

docking hardware proximate a first end of said boom used to capture the satellite;

a nuclear reactor coupled to said boom proximate a second end of said boom opposite the first end of said boom;

a radiation shield coupled to said nuclear reactor; and

an energy converter coupled to the nuclear reactor, the nuclear reactor and energy converter producing at least 250 kW of sustained electrical power; and

b) using the nuclear powered vehicle to move the satellite from its first orbit to a second orbit, and wherein the nuclear powered vehicle approaches, connects to and transits with the satellite such that the radiation shield protects the satellite from radiation from the nuclear reactor.