摘要
为量化无动力滑翔飞行器末制导初始参数不确定性的综合影响,提升飞行器落点精度,提出基于不确定性的末制导初始参数优化设计方法。面向飞行器末端高动态打击需求,采用落角约束下的滑模变结构导引律进行实时弹道成型,进而考虑末制导初始参数的不确定性。以落点有效毁伤半径概率和落点圆概率偏差为多优化目标,建立基于不确定性的末制导初始参数及制导律参数优化模型。针对这一不确定性优化模型,研究利用高效全局优化和蒙特卡洛方法,给出末制导初始参数及制导律参数的最优设计方案。仿真结果表明:该方法能显著提升落点精度,为方案设计阶段飞行器末制导交接点的选取提供决策支持。
In order to quantify the influence of uncertainties in the terminal guidance initial parameters for unpowered gliding vehicle, an uncertainty-based design optimization method of terminal guidance initial parameters was developed to improve the accuracy of impact point. The sliding-mode variable structure control was used to predict trajectory of vehicle in real time to meet the requirements of high dynamic strike in the terminal stage of flight vehicle. In consideration of the uncertainties in the terminal guidance initial parameters, the optimization model of uncertainty-based terminal guidance initial parameters and guidance law parameters was built. The circular error probability and the probability of impact points in the effective damage radius were considered into the multiple-objective function. Effective global optimization and Monte Carlos method were used to obtain the optimum of initial parameters and guidance law parameters efficiently. It was shown that the accuracy of impact point is improved significantly, which can further provide decision support for the connection point of terminal guidance in the stage of vehicle conceptual design.
作者
张海瑞
王浩
王尧
洪东跑
卜奎晨
ZHANG Hairui;WANG Hao;WANG Yao;HONG Dongpao;BU Kuichen(China Academy of Launch Vehicle Technology,Beijing 100076,China)
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2019年第6期33-38,共6页
Journal of National University of Defense Technology
基金
国家部委基金资助项目(6140244010216HT15001)
关键词
末制导
多目标优化
不确定性优化
高效全局优化
terminal guidance
multi-objective optimization
uncertainty optimization
efficient global optimization
