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本文记述了无后座炮内弹道的气动力数学模型。给出用差分格式求解拟线性偏微分方程组的方法,并获得在气相和固相流动速度相等的条件下的数值解。计算结果与常规方法进行比较,最后得出了一些常规方法不可能反映的规律。
This paper describes the aerodynamic mathematical model of a ballistic missile without rear seat. The method of solving a quasilinear system of partial differential equations by using the differential scheme is given and the numerical solution is obtained under the condition that the flow velocities between gas and solid are equal. The result of calculation is compared with the conventional method, and finally some laws that conventional methods can not reflect are obtained.