Title:
【発明の名称】熱保護システム
Document Type and Number:
Japanese Patent JP2538351
Kind Code:
B2
Abstract:
An integral structure and thermal protection system, particularly designed for hypersonic aerospace vehicles, is comprised of a hard external shell or outer face sheet formed of a ceramic matrix, such as silicon carbide, and a rigid insulator core in the form of foamed ceramic, such as silicon carbide, the outer face sheet being integrally connected to the insulator core. A prime strucutral material, such as an aircraft structural member, is integrally connected as by bonding or brazing to the insulator core, the core being attached to the prime structural material or aircraft structural member by an inner face sheet forming the outer skin of such structural member.
Inventors:
HARII EI SUKOTSUTO
Application Number:
JP24784289A
Publication Date:
September 25, 1996
Filing Date:
September 22, 1989
Export Citation:
Assignee:
ROCKWELL INTERNATIONAL CORP
International Classes:
B64C1/38; B64C3/36; B64G1/58; B64C1/40; (IPC1-7): B64G1/58; B64C1/40
Domestic Patent References:
| JP6325588A | ||||
| JP6326758U |
Attorney, Agent or Firm:
Fukami Hisaro (2 outside)