基于序列近似优化方法的探空火箭气动/动力一体化优化

摘要

总体设计是探空火箭研制的先行牵引工作，是一项复杂的系统工程。针对探空火箭总体设计一体化优化问题，基于序列近似优化方法，将代理模型方法应用于优化过程，通过不断更新代理模型和采样点对最优解进行高效预测，是对复杂模型进行优化设计的有效方法。针对某单级固体探空火箭，建立其弹道、动力、气动计算模型，使用序列近似优化方法，以火箭理论弹道顶点高度最大为优化目标，对其气动/动力参数进行一体化优化，最后得到一组较优的总体设计参数。结果表明：整个优化过程模型调用次数少，收敛速度快，工作效率较高，体现了序列近似优化方法的优越性。%Aimed at a certain type of a single stage solid sounding rocket,traj ectory,power and aerodynam-ic models are established in this paper.Taking the maximum height of rocket theory traj ectory peak as op-timization goal,the aerodynamic/power integrated optimization are realized by using the method of se-quential approximate optimization to obtain a set of better parameters in conception design.In the whole process of optimization,the number of times for shifting model is less and the convergence is quick in ve-locity.