Method of applying ablative insulation coatings and articles obtained therefrom
View Patent ↗A method of forming ablative insulation coatings on aerospace structures and articles produced thereby. The method includes forming a mold having a cavity configured to complementarily receive at least a portion of the structure and directly molding the ablative coating to a surface of the structure by introducing a prepared ablative mixture, such as an epoxy resin, into the mold. The process may desirably include curing at atmospheric pressures to reduce the expense and equipment required in carrying out the process. The method of applying the ablative coating further includes features such as varying the thickness of the ablative coating from one portion of the component to another. Control of the thickness may be effected through use of spacers embedded into the ablative coating and formed of the same or similar material previously cured prior to placement in the mold.
1. An aerospace vehicle component comprising:
a structure;
an ablative insulation coating molded directly to a surface of the structure; and
at least one discrete spacer formed of an ablative insulative material having a first side, a second side, and a lateral peripheral surface between the first side and the second side, the at least one discrete spacer being fixedly disposed in the ablative insulation coating with the lateral peripheral surface being contiguously secured to the ablative insulation coating.
2. The aerospace vehicle component of claim 1 , wherein the ablative insulation coating has a thickness which varies from a first portion of the surface of the structure to a second portion of the surface of the structure.
3. The aerospace vehicle component of claim 1 , wherein the at least one discrete spacer includes at least two discrete spacers formed of an ablative insulative material, at least a first discrete spacer of the at least two discrete spacers being located proximate a first portion of the surface of the structure and at least one other discrete spacer of the at least two discrete spacers being located proximate a second portion of the surface of the structure.
4. The aerospace vehicle component of claim 1 , further comprising at least one stay-out zone formed in the ablative insulation coating comprising an ablative coating-devoid area adjacent an otherwise coated surface of the structure.
5. The aerospace vehicle component of claim 4 , wherein the at least one stay-out zone includes a plurality of stay-out zones.
6. The aerospace vehicle component of claim 1 , wherein the ablative insulation coating includes an epoxy resin.
7. The aerospace vehicle component of claim 6 , wherein the ablative insulation coating includes a fiber reinforcement component.
8. The aerospace vehicle component of claim 6 , wherein the ablative insulation coating includes a mixture of a salt-filled epoxy resin base, a fiber-filled polyamide hardener and a silicone resin modifier.
9. The aerospace vehicle component of claim 8 , wherein the mixture includes approximately 100 parts by weight of the salt-filled epoxy resin base, approximately 86 parts by weight of the fiber-filled polyamide hardener, and approximately 35 parts by weight of the silicone resin modifier.
10. The aerospace vehicle component of claim 1 , wherein the ablative insulation coating is substantially devoid of air bubbles.
11. The aerospace vehicle component of claim 1 , wherein the ablative insulation coating and the at least one discrete spacer exhibit a substantially similar material composition.
12. The aerospace vehicle component of claim 1 , wherein the ablative insulative material exhibits a coefficient of thermal expansion that is substantially similar to a coefficient of thermal expansion of the ablative insulation coating.
13. The aerospace vehicle component of claim 1 , wherein the at least one discrete spacer includes a plurality of discrete spacers.
14. The aerospace vehicle component of claim 1 , wherein the at least one discrete spacer includes a first spacer exhibiting a first thickness and a second spacer exhibiting a second thickness, the second thickness being greater than the first thickness.
15. The aerospace vehicle component of claim 1 , wherein the ablative insulation coating exhibits a first thickness at a first location of the structure and wherein the ablative insulation coating exhibits a second thickness at a second location of the structure, the second thickness being greater than the first thickness.
16. The aerospace vehicle component of claim 1 , wherein the structure includes a snap ring.
17. The aerospace vehicle component of claim 1 , wherein the structure includes an access door cover.
18. The aerospace vehicle component of claim 1 , wherein the structure includes a shell.
19. The aerospace vehicle component of claim 1 , wherein at least a portion of the at least one discrete spacer is contiguous with the surface of the structure.