基于Gauss伪谱法的高空飞行器再入段轨迹优化对传热效应的影响分析  

Influence Analysis of Heat Transfer Effect on Reentry Trajectory Optimization of Adjacent Space Vehicles based on Gauss Pseudospectral Method

作　　者：邵嘉健 薛鹏飞 Shao Jia-jian;Xue Peng-fei(Science and Technology on Space Physics Laboratory,Beijing,100076)

机构地区：[1]空间物理重点实验室,北京100076

出　　处：《导弹与航天运载技术（中英文）》2023年第1期11-15,共5页Missiles and Space Vehicles

摘　　要：基于Gauss伪谱法和二阶有限差分(Gauss Pseudospectral Method,GPM),研究了再入过程中高速飞行器的传热问题,并依据最内温层升温最小的目的进行飞行轨迹的数值优化。主要思路:构造传热分析模型,并依据传热方程构造每一温层的传热微分方程;将各温层微分方程以及动力学微分方程作为伪谱法中的微分方程约束条件代入,进行轨迹数值优化设计;利用少量LG点构造拉格朗日多项式,再通过一维插值获得大量LG点的值,获得更高精度的拟合结果曲线。以某高超声速飞行器为对象用本方法进行数值计算,结果验证了方法具有一定的可行性。Based on Gauss Pseudospectral and the second order finite difference method,to study the heat transfer problem in the process of hypersonic flight vehicle reentry,and according to the purpose of the lowest temperature rise in the innermost layer to perform numerical optimization of flight path.The main train of thought.constructing the heat transfer analysis model andthe heat transfer differential equation of each temperature layer according to the heat transfer equation.Substituting differential equation of every temperature layer and dynamic differential equation into the constraint conditions of the differential equation in the pseudo-spectral method,for the trajectory numerical optimization design;constructing lagrangian polynomials with a small number of LG points,and a large number of LG points are obtained through one-dimensional interpolation,to obtain the fitting result curve with higher accuracy.This method is used for numerical calculation of a hypersonic vehicle,and the results verify the feasibility of it.

关 键 词：GAUSS伪谱法 传热分析模型 轨迹优化设计 

分 类 号：V412.44[航空宇航科学与技术—航空宇航推进理论与工程]