用于固体火箭发动机总体参数选择的两条曲线

TWO CURVES FOR SELECTING GENERAL PARAMETERS OF SOLID PROPELLANT ROCKET MOTORS

从最小质量的观点出发，分析了合理地选择燃烧室工作压强和喷管膨胀比这两个固体火箭发动机总体参数的问题。用迭代法求解，给出了两条工程上行之有效的曲线──最佳燃烧室工作任强随喷管膨胀比ε的变化曲线和最佳喷管膨胀比ε*随燃烧室工作压强pc的变化曲线。ε*=f2（pc），从而可得到燃烧室压强和喷管膨胀比的最佳选择。

The key of solid propellant rocket motors design is to choose proper combustionchamber pressure and nozzle expansion ratio. The two parameters are analysed in the view ofminimum mass. The two feasible engineering application curves are given which curve pc* =f1(ε),optimum combustion chamber Pc* versus nozzle expansion ratio ε and curve ε* = f2 (pc), optimumnozzle expansion ratio ε versus combustion chamber pressure Pc resoved by iteration method.Therefor, the optimum choice of combustion chember pressure and nozzle expansion ratio is obtained.