基于落点预测的双旋火箭弹末段飞行控制方法研究  

Study on the Flying Control Method at Terminal Flight of a Dual-Spin Rocket Based on the Prediction for the Impact Point

作　　者：曹小兵[1] 徐伊岑[2] 常思江[3] 钱晓忠[1] CAO Xiao-bing;XU Yi-cen;CHANG Si-jiang;QIAN Xiao-zhong(School of Control Technology/Wuxi Institute of Technology,Wuxi 214121,China;School of Mechatronic Technology/Wuxi Institute of Commerce,Wuxi 214153,China;School of Energy and Power Engineering/NUST,Nanjing 210094,China)

机构地区：[1]无锡职业技术学院控制技术学院,江苏无锡214121 [2]无锡商业职业技术学院机电技术学院,江苏无锡214153 [3]南京理工大学能源与动力工程学院,江苏南京210094

出　　处：《山东农业大学学报（自然科学版）》2021年第2期308-312,共5页Journal of Shandong Agricultural University：Natural Science Edition

基　　金：国家自然科学基金(11402117);江苏省第五期“333高层次人才培养工程”资助(2018Ш-1893)。

摘　　要：针对某双旋火箭弹的末端弹道控制问题,本文提出了一种基于落点预测的弹道控制算法。分析了舵机控制力及控制力矩,建立了该火箭弹的六自由度弹道模型。在匀加速运动假设下,利用三自由度质点弹道方程推导了落点坐标预测解析式及剩余飞行时间计算式,给出了偏差控制方位确定算法,并通过算例仿真分析了不同启控时间和不同控制方位角作用下火箭弹攻角的变化规律,得到了有效控制范围,并针对多个不同目标点应用所设计的控制算法对偏差控制效果进行了计算。结果表明,在有效可控范围内,该控制方法能够有效修正偏差,提高落点精度。A trajectory control algorithm based on the prediction of the impact point was proposed to solve the problem of the terminal trajectory control of a dual-spin rocket.The control force and torque of the canards were analyzed,and the six degrees of freedom equations were established.Under the assumption of uniform acceleration motion,this paper deduced the analytic expressions of the predicted impact point coordinates and the calculation formula of the remaining flight time,based on the three degrees of freedom equations.The algorithm of the control azimuth was given.Simulations for a certain rocket were carried out.The change of the attack angle of the rocket under different start control times and different control azimuths were analyzed.The effective control area was obtained.The control results based on the control algorithm for different assumed targets were presented.The results indicate that the control method can effectively correct the deviation and improve the precision of the impact point.

关 键 词：火箭 落点预测 飞行控制 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]