Insulation thermal separating wall for solid propellant rocket, has metallic base body with insulating layer, where density of layer is comprised between specified percentage of theoretical density of material at sintered state

摘要

#CMT# #/CMT# The wall has a metallic base body, which is in the form of plate, including a thermal insulating layer made of aluminum oxide or zirconium oxide based ceramic material. The density of the insulating layer is comprised between eighty and ninety percentage of a theoretical density of the material at a sintered state. The insulating layer is applied to the body by thermal spraying. #CMT# : #/CMT# An independent claim is also included for a method for manufacturing an insulation thermal separating wall. #CMT#USE : #/CMT# Used for thermally separating a combustion chamber of a solid propellant rocket and a guiding electronic device of the chamber (claimed) during combustion of a fuse material. #CMT#ADVANTAGE : #/CMT# The wall permits to reduce the temperature of the electronic device to a negligible value in a simple and economical manner during the combustion of the fuse material, in order to provide sufficient insulation between the chamber and the eletronic device of the chamber, thus avoiding the device from premature destruction.