姿控载荷多约束下的内外弹道联合优化

发布时间：2018-01-15 15:39

本文关键词：姿控载荷多约束下的内外弹道联合优化　出处：《宇航学报》2016年06期 　论文类型：期刊论文

【摘要】：为提升固体运载器整体性能,提出一种姿控载荷多约束的内外弹道联合优化建模方法。首先,建立固体运载器内弹道计算模型和外弹道计算模型,给出大风区和级间分离的姿态控制模型以及杆状减阻装置载荷计算模型。其次,以灵敏度分析方法选择出内外弹道设计参数作为优化设计变量,将姿控摆角需求、减阻杆承载能力作为约束条件,建立以射程最优为目标的优化模型。最后,将该方法应用在某三级固体运载器的优化设计中,以差分进化算法开展仿真校验,射程提高了10.8%,并且优化结果满足姿控和载荷约束。
[Abstract]:In order to improve the overall performance of the solid launch vehicle, a joint optimization modeling method of internal and external trajectory with multiple constraints of attitude control load is proposed. Firstly, the interior trajectory calculation model and the external trajectory calculation model of the solid launch vehicle are established. The attitude control model and the load calculation model of the rod drag reducing device are given. Secondly, the interior and exterior ballistic design parameters are selected as the optimization design variables by sensitivity analysis method. The requirements of attitude control pendulum angle and the bearing capacity of drag reducing rod are taken as the constraint conditions to establish an optimization model with optimal range. Finally, the method is applied to the optimal design of a three-stage solid carrier. The differential evolution algorithm is used to verify the simulation, the range is increased by 10.8, and the optimization results satisfy the attitude control and load constraints.
【作者单位】：北京宇航系统工程研究所;
【分类号】：V412.1
【正文快照】： 0引言固体运载器的射程是一项重要的技术指标。为提高射程能力,一方面可针对固体火箭发动机开展性能优化,通过优化药柱、喷管等几何尺寸获得优化的内弹道参数[1-3],提升运载器本身的推进能力;另一方面,可通过开展外弹道优化设计[4-6],优化固体运载器的飞行程序,为运载器提供良

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