Explanation

A kind of materials coated or bonded on the inner wall of solid propellant shell to protect the shell from high temperature flame ablation and prevent heat loss. The combustion temperature of solid propellant is as high as 2400-3800K, and the working pressure in the rocket engine is generally between 2-30MPa. In order to prevent the chemical ablation, airflow erosion, particle erosion and other harmful effects of fuel gas on the rocket engine housing under high temperature and pressure, it is necessary to select materials with good thermal insulation efficiency and lay them on the inner wall of the engine housing. The commonly used thermal insulation layer is composed of acrylonitrilebutadiene rubber, ethylene-propylene-diene-terpolymer rubber or silicone rubber with good carbonization, flame retardant or fire retardant, heat-resistant agent and other fillers and other functional components. Generally, the insulation layer is required to have low ablation rate, low density and good mechanical properties.

Classification