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700 km太阳同步轨道为运载火箭弹道设计中典型的发射任务。采用轨迹分解优化策略对此类任务的发射轨道进行研究,分析了中间轨道近地点高度、入轨点真近点角两个约束变量对火箭运载能力的影响,并重点结合气动热流限制对约束变量的取值进行了计算分析。采用的研究思路和得出的结论对于运载火箭上升段弹道的优化设计以及提升运算收敛性和设计效率均有一定的意义。
700 km The sun synchronous orbit is a typical launch mission in the design of launch vehicle trajectory. The orbit decomposition optimization strategy is used to study the launch orbit of such missions. The effects of two constraint variables such as the altitude of the mid-track orbit and the true or near point of the orbit on the rocket carrying capacity are analyzed. The aerodynamic heat flow restriction is used to analyze the influence of the constraint variables The values were calculated and analyzed. The research ideas and conclusions obtained are of great significance to the optimization design of the ascending trajectory of the launch vehicle and the improvement of convergence and design efficiency.