Heat shield for a spacecraft
View Patent ↗Various material compositions of a heat shield for a spacecraft are described. The heat shield can be formed by multi-dimensional weaver or three-dimensional (3-D) printer. Furthermore, the heat shield can be configured with a superconducting coil.
1. A spacecraft;
a heat shield for minimizing heat transfer to the spacecraft; the heat shield comprising:
(a) a carbon phenolic material; and
(b) a nanostructural material, wherein the nanostructural material comprises: graphene in an amount of 0.1 wt % to 10 wt % and graphene nanoribbons in an amount of 0.1 wt % to 10 wt %.
2. The spacecraft of claim 1 , wherein the heat shield further comprises: a hollow microsphere or a syntactic microfoam.
3. The spacecraft of claim 1 , wherein the heat shield further comprises: a ceramic material.
4. The spacecraft of claim 1 , wherein the heat shield further comprises: a light silicate frame material.
5. The spacecraft of claim 1 , wherein the heat shield further comprises: a superconducting coil.
6. A spacecraft;
a heat shield for minimizing heat transfer to the spacecraft; the heat shield comprising:
(a) a matrix material, wherein the matrix material comprises: a carbon phenolic material and a silicon carbide material, wherein the silicon carbide material comprises: carbon fibers; and
(b) a nanostructural material, wherein the nanostructural material comprises: graphene in an amount of 0.1 wt % to 10 wt % and graphene nanoribbons in an amount of 0.1 wt % to 10 wt %.
7. The spacecraft of claim 6 , wherein the heat shield further comprises: a hollow microsphere or a syntactic microfoam.
8. The spacecraft of claim 6 , wherein the heat shield further comprises: a ceramic material.
9. The spacecraft of claim 6 , wherein the heat shield further comprises: a light silicate frame material.
10. The spacecraft of claim 6 , wherein the heat shield further comprises: a superconducting coil.
11. A spacecraft;
a heat shield for minimizing heat transfer to the spacecraft; the heat shield comprising:
(a) a matrix material, wherein the matrix material comprises: a carbon phenolic material and a silicon carbon nitride material, wherein the silicon carbon nitride material comprises: carbon fibers; and
(b) a nanostructural material, wherein the nanostructural material comprises: graphene in an amount of 0.1 wt % to 10 wt % and graphene nanoribbons in an amount of 0.1 wt % to 10 wt %.
12. The spacecraft of claim 11 , wherein the heat shield further comprises: a hollow microsphere or a syntactic microfoam.
13. The spacecraft of claim 11 , wherein the heat shield further comprises: a ceramic material.
14. The spacecraft of claim 11 , wherein the heat shield further comprises: a light silicate frame material.
15. The spacecraft of claim 11 , wherein the heat shield further comprises: a superconducting coil.
16. A spacecraft;
a heat shield for minimizing heat transfer to the spacecraft; the heat shield comprising:
(a) an in-situ planetary material; and
(b) a first nanostructural material, wherein the in-situ planetary material is not from planet earth, wherein the first nanostructural material comprises: graphene in an amount of 0.1 wt % to 10 wt % and graphene nanoribbons in an amount of 0.1 wt % to 10 wt %.
17. The spacecraft of claim 16 , wherein the heat shield further comprises: a hollow microsphere or a syntactic microfoam.
18. The spacecraft of claim 16 , wherein the heat shield further comprises: a second nanostructural material.
19. The spacecraft of claim 16 , wherein the heat shield further comprises: a ceramic material.
20. The spacecraft of claim 16 , wherein the heat shield further comprises: a superconducting coil.