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Tungsten alloy throat lining

Tungsten alloy throat lining is a solid rocket engine nozzle throat lining material. When the rocket is launched, the fuel gas accelerates to the speed of sound through the nozzle throat to produce 65-75% thrust, which is subjected to the test of high temperature and pressure in the nozzle throat. Therefore, the material of the lining directly affects the performance of the rocket engine.

The solid rocket motor is a chemical rocket motor using solid propellant, which is composed of a propellant column, combustion chamber, nozzle assembly and ignition device. The rocket engine nozzle belongs to the convergent - diffusion nozzle (laval-delaval nozzle), which is composed of the inlet section (convergent section), throat (throat line), and outlet cone (diffusion section or expansion section). Its function is to convert the thermal energy of combustion products into the kinetic energy of high-speed jet to generate thrust. The expansion ratio, that is, the area ratio between the throat and the nozzle, directly affects the performance of the engine.
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