Patent Number: 
Section: claims

1. A space vehicle comprising:a capsule; anda radiation shield device comprising:at least one first coil comprised of a superconductive material;first and second conduits extending about the capsule, wherein the at least one first coil is disposed within the first conduit so as to also extend within the first conduit about the area to be shielded from radiation, and wherein the first conduit is disposed within the second conduit;first and second cryogen liquids disposed within the first and second conduits, respectively, wherein the second cryogen liquid is disposed within the second conduit exterior of the first conduit, and wherein the first cryogen liquid has a lower boiling point than the second cryogen liquid;at least one second coil comprised of a superconductive material;third and fourth conduits extending about the capsule and also extending about the first and second conduits, wherein the at least one second coil is disposed within the third conduit so as to extend within the third conduit about the capsule, and wherein the third conduit is disposed within the fourth conduit; andfirst and third cryogen liquids disposed within the third conduit and the fourth conduit, respectively, wherein the third cryogen liquid is different than the first and second cryogen liquids. 2. The space vehicle according to claim 1 wherein the first cryogen liquid comprises liquid helium and the second cryogen liquid comprises one of liquid oxygen, liquid nitrogen or liquid hydrogen. 3. The space vehicle according to claim 1 wherein the second cryogen liquid comprises liquid hydrogen and the third cryogen liquid comprises liquid oxygen, and wherein the space vehicle further comprises a fuel cell configured to receive boil off of the second and third cryogen liquids. 4. The space vehicle according to claim 1 wherein the at least one first coil is spaced apart from the at least one second coil. 5. The space vehicle according to claim 1 wherein the radiation shield device further comprises thermal insulation surrounding the second conduit. 6. The space vehicle according to claim 5 wherein the radiation shield device further comprises a first intermediate conduit extending about the capsule, wherein the first conduit is disposed within the first intermediate conduit, and wherein the first intermediate conduit is disposed within the thermal insulation and the second conduit. 7. The space vehicle according to claim 1 wherein the first conduit is larger than the first coil. 8. The space vehicle according to claim 1 wherein the third conduit is larger than the second coil. 9. The space vehicle according to claim 1 wherein at least one first coil is comprised of a niobium titanium (NbTi) copper matrix multifilament superconducting wire winding. 10. The space vehicle according to claim 1 wherein at least one second coil is comprised of a niobium titanium (NbTi) copper matrix multifilament superconducting wire winding. 11. The space vehicle according to claim 1 further comprising a thermal control system in thermal communication with the superconductive material of the at least one first and second coils. 12. The space vehicle according to claim 1 wherein the at least one first conduit has a length in an axial direction that is greater than a radial width of the at least one first conduit. 13. The space vehicle according to claim 12 wherein the at least one second conduit has a length in the axial direction that is greater than the length of the at least one first conduit, and wherein the at least one second conduit has a radial width that is greater than the radial width of the at least one first conduit. 14. The space vehicle according to claim 1 wherein the at least one first and second conduits are formed of aluminum. 15. The space vehicle according to claim 1 further comprising a power source in communication with the at least one first and second coils. 16. The space vehicle according to claim 1 further comprising a source of the first, second and third cryogen liquids. 17. The space vehicle according to claim 16 wherein the source of the first, second and third cryogen liquids comprises a plurality of tanks configured to store the first, second and third cryogen liquids. 18. The space vehicle according to claim 17 wherein the plurality of tanks are nested. 19. The space vehicle according to claim 1 further comprising a controller for controlling flow of the first, second and third cryogen liquids through the first, second, third and fourth conduits. 20. The space vehicle according to claim 19 wherein the controller is configured to determine that particle radiation is approaching and to issue instructions regarding circulation of the first, second and third cryogen liquids.