固定鸭舵二维修正弹比例导引律参数优化

曹立飞; 曹红松; 刘鹏飞; 刘恒著; 肖艳文

doi:10.7527/S1000-6893.2020.24751

航空学报 >

2021 , Vol. 42 >Issue 6: 324751 - 324751

DOI: https://doi.org/10.7527/S1000-6893.2020.24751

电子电气工程与控制

固定鸭舵二维修正弹比例导引律参数优化

曹立飞 ,
曹红松 ,
刘鹏飞 ,
刘恒著 ,
肖艳文

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1. 中北大学机电工程学院, 太原 030051;
2. 中国人民解放军 32381部队, 北京 100071

收稿日期: 2020-09-14

修回日期: 2020-10-15

网络出版日期: 2020-12-25

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Parameter optimization of proportional navigation guidance for 2D trajectory correction projectile with fixed canards

CAO Lifei ,
CAO Hongsong ,
LIU Pengfei ,
LIU Hengzhu ,
XIAO Yanwen

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1. College of Mechatronics Engineering, North University of China, Taiyuan 030051, China;
2. Unit 32381, PLA, Beijing 100071, China

Received date: 2020-09-14

Revised date: 2020-10-15

Online published: 2020-12-25

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摘要

针对固定鸭舵二维修正机构控制力有限和比例导引法控制末段需用过载变化过大的问题，提出了一种基于重力补偿比例导引律的过载阈值控制策略。分析了固定鸭舵二维修正机构的控制力及力矩，以落点弹目距离最小为目标函数，选取纵向和横向平面导引系数及过载阈值为设计变量，在重力补偿比例导引律的基础上建立了导引律参数优化模型，并采用差分进化算法（DE）对其进行优化。最后通过外弹道仿真分别从控制段飞行稳定性、控制效率、控制机构过载及控制精度几个方面与传统比例导引律进行对比分析，同时使用蒙特卡洛法验证了控制策略的有效性。结果表明：与传统比例导引律相比，使用该控制策略提高了二维弹道修正迫弹的控制效率，有效降低了控制末段需用过载，弹道控制段飞行稳定性明显提高。

关键词： 固定鸭舵; 比例导引; 优化设计; 差分进化; 飞行稳定性

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曹立飞 , 曹红松 , 刘鹏飞 , 刘恒著 , 肖艳文 . 固定鸭舵二维修正弹比例导引律参数优化[J]. 航空学报, 2021 , 42(6) : 324751 -324751 . DOI: 10.7527/S1000-6893.2020.24751

Abstract

To solve the problems of limited control force of the 2D correction mechanism with fixed canards and the overload variation required at the end of the control section by the Proportional Navigation Guidance (PNG), an overload threshold control strategy based on the PNG is proposed. The control forces and moments of the correction mechanism are analyzed. With the objective function of the minimum distance between the projectile and target, the longitudinal and transverse planar guidance coefficients and overload thresholds are selected as the design variables, and a parameter optimization model is established based on the PNG. The model is then optimized by the Differential Evolution (DE) algorithm. Finally, the control strategy proposed is compared with the traditional PNG in terms of flight stability, control efficiency, control mechanism overload, and control accuracy by external ballistic simulation, and the effectiveness of the control strategy is also verified by the Monte-Carlo method. The results show that compared with the traditional PNG, the control strategy proposed can improve the flight stability of the control section and reduce the overload at the end of the control section of the 2D ballistic correction projectile.

Key words： fixed canards; proportional navigation guidance; optimal design; differential evolution; flight stability

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