In orbit space transportation & recovery system
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.
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 ).