According to the entire design requirements and restraints of a certain solid propellant rocket motor, design method of nozzle contour is put forward.

根据某型号固体火箭发动机总体设计要求及限制条件，给出了喷管型面设计方法。

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The most basic contour that can be considered for a nozzle is a truncated cone.

最基本的轮廓，可以被视为一个喷嘴是一个截断锥。

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In order to determine temperature and pressure on nozzle inner contour, the gas was regarded as one-dimension isoentropic flow.

将燃气简化为一维等熵流，以确定喷管内型面所承受的温度和压强载荷。

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