采用改进模拟退火算法的高速飞行器随控总体优化方法

选取翼身组合体气动布局的高速飞行器为研究对象，基于已建立的飞行器总体参数与气动非线性/耦合性等随控性指标间的表征数学模型，开展高速飞行器的随控总体优化方法研究，使得飞行器在全弹道上所有特征点处的非线性度/耦合度的最大绝对值达到最小。为改善经典模拟退火算法的全局搜索能力, 提高退火算法的趋优避劣性，引入精英集合策略。算法测试结果表明：改进模拟退火算法比经典模拟退火算法具有更好的收敛稳定性和收敛速度。算例飞行器的随控总体优化结果表明：飞行器在全弹道上的非线性度m α  NL 、耦合度C xy 、C yx 分别改进了90.6%、99%、36.5%，取得了较好的优化效果。

The Control Configured Optimization Method for Hypersonic Vehicles Using the Improved Simulated Annealing Algorithm

Based on the established model that both aerodynamic nonlinearity and aerodynamic coupling are the function of configuration parameters, a chosen hypersonic vehicle’s shape will be optimized to search for optimal configuration parameters with the lowest nonlinearity and coupling of the all ballistic feature points. To improve simulated annealing algorithm’s search capability in the whole feasible region, a well chosen aggregation strategy containing a few locally best optimal elements is introduced. The optimization results of test functions indicate that the improved algorithm possesses a better convergence stability and speed. The specific vehicle’s control\|configured optimization results reveal that the improved simulated annealing algorithm is more effective and has a better search capability in the whole feasible region.