Vehicle ablator system
US-9527609-B2 · Dec 27, 2016 · US
Heat shield for a spacecraft
US9656769B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9656769-B2 |
| Application number | US-201414266158-A |
| Country | US |
| Kind code | B2 |
| Filing date | Apr 30, 2014 |
| Priority date | May 1, 2013 |
| Publication date | May 23, 2017 |
| Grant date | May 23, 2017 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
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.
First claim
Opening claim text (preview).
We claim: 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.
Assignees
Inventors
Classifications
- B64G1/62Primary
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Unconventional spacecraft propulsion systems · CPC title
Three-dimensional woven fabrics · CPC title
Textiles & Paper · mapped topic
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Frequently asked questions
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- What does patent US9656769B2 cover?
- 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.
- Who is the assignee on this patent?
- Mazed Mohammad A, Wiig Rex, Martinez Angel
- What technology area does this patent fall under?
- Primary CPC classification B64G1/62. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue May 23 2017 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).