论文部分内容阅读
以一种高声速导弹作为应用对象,计算了喷水预冷却发动机的安装特性,建立了导弹/喷水预冷却发动机一体化设计的约束分析和任务分析模型,给出了高超声速导弹的升阻特性的确定方法,结合任务剖面、导弹的重量组成以及发动机模型,取爬升率为100m/s,80m/s和50m/s对导弹的爬升和加速任务段进行约束分析,选择巡航马赫数为4.0,5.0和6.0三种情况进行了导弹任务分析。计算结果表明,建立的导弹/发动机一体化约束分析与任务分析模型合理,当巡航马赫数小于5.0时,虽然装备喷水预冷却发动机与亚燃冲压发动机的导弹相比爬升率和加速度较低,但是导弹射程却有较大幅度的提高,因而在高声速导弹的应用是可行的。
A kind of hypersonic missile was used as an application object to calculate the installation characteristics of the pre-cooling water jet engine. The constraint analysis and mission analysis model of the missile / pre-cooling engine integrated design were established. The lifting resistance of the hypersonic missile was given. Based on the mission profile, the weight composition of the missile and the engine model, the cruise rate of 100m / s, 80m / s and 50m / s were used to determine the mission characteristics of the missile. The cruise Mach number was chosen to be 4.0 , 5.0 and 6.0 conducted three cases of missile mission analysis. The results show that the missile / engine integrated constraint analysis and mission analysis model are reasonable. When the cruise Mach number is less than 5.0, although the rate of climb and acceleration are lower than that of a missile equipped with pre-cooled jet engine and submarine ramjet engine, However, the range of missiles has been greatly improved, so the application of high-speed missiles is feasible.