US12663245 - Heat resistant structure of flying body and manufacturing method of heat resistant structure of flying body

The patent describes a heat-resistant structure for a flying body, featuring a tip part with a surface member made of materials like zirconium carbide, designed to withstand high temperatures during atmospheric travel. The structure includes a base part that connects the tip to the body and an insulation member that thermally isolates the base part from the surface member, with the density of the heat-resistant materials decreasing from the front to the back of the flying body.

Claim 1

1 . A heat resistant structure of a flying body, applied to a flying body comprising: a tip part arranged at a front end of the flying body with respect to a direction of travel of the flying body; and a body part arranged in a back direction from the tip part with respect to the direction of travel of the flying body, wherein the tip part comprises: a surface member arranged on an outer surface of the tip part, the surface member having a melting point higher than a maximal temperature reached on a surface of the flying body when the flying body moves in an atmosphere and is heated; a base part configured to couple the surface member to the body part; and an insulation member arranged between the surface member and the base part, the insulation member configured to thermally insulate the base part from the surface member, wherein the surface member comprises a heat resistant material including a zirconium carbide, a tantalum carbide or a hafnium carbide on at least an outer surface of a carbon fiber reinforced carbon composite material that has a shape of the surface member, and wherein a density of the zirconium carbide, the tantalum carbide or the hafnium carbide in the heat resistant material decreases continuously from a front direction to a back direction with respect to the direction of travel of the flying body. a tip part arranged at a front end of the flying body with respect to a direction of travel of the flying body; and a body part arranged in a back direction from the tip part with respect to the direction of travel of the flying body, wherein the tip part comprises: a surface member arranged on an outer surface of the tip part, the surface member having a melting point higher than a maximal temperature reached on a surface of the flying body when the flying body moves in an atmosphere and is heated; a base part configured to couple the surface member to the body part; and an insulation member arranged between the surface member and the base part, the insulation member configured to thermally insulate the base part from the surface member, a surface member arranged on an outer surface of the tip part, the surface member having a melting point higher than a maximal temperature reached on a surface of the flying body when the flying body moves in an atmosphere and is heated; a base part configured to couple the surface member to the body part; and an insulation member arranged between the surface member and the base part, the insulation member configured to thermally insulate the base part from the surface member, wherein the surface member comprises a heat resistant material including a zirconium carbide, a tantalum carbide or a hafnium carbide on at least an outer surface of a carbon fiber reinforced carbon composite material that has a shape of the surface member, and wherein a density of the zirconium carbide, the tantalum carbide or the hafnium carbide in the heat resistant material decreases continuously from a front direction to a back direction with respect to the direction of travel of the flying body.

Google Patents

https://patents.google.com/patent/US12663245

USPTO PDF

https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/12663245