一种新型后舵尾控修正弹的弹道控制仿真

doi:10.12382/bgxb.2023.0178

摘要/Abstract

摘要：

为增强修正弹控制舵的快速响应能力和弹道修正效果,且理论上减弱舵片在高旋状态下对弹体的气动扰流影响,设计一种控制舵置于质心后部、与弹尾部高度配合的新型二维修正弹。建立弹体模型,设计以优化后的新式制导方案和比例微积分控制法为主体的组合控制策略,分析无控和有控状态下关键变量参数的变化规律,对基于参数最优值下的弹道修正过程进行仿真计算;采用蒙特卡洛打靶法分析扰动状态下的落点散布情况。仿真结果表明:此控制策略下后舵尾控弹的实际滚转角吻合于输入指令,整个过程速度高低角和方向角的变化范围仅为2°和7°,基于最优值的控制修正过程和扰动状态下的最终落点情况也保证了弹体进行平稳运动的同时具备更优的偏差修正能力,进一步证实了设计的新型弹体模型具有较高的可行性和参考价值。

关键词: 精确制导弹药, 弹道修正弹, 尾控舵, 控制策略, 弹道修正

Abstract:

In order to enhance the response ability and trajectory correction effect of trajectory correction projectile’s control rudder and greatly reduce the aerodynamic turbulence influence of rudder on the projectile body in theory, a new type of two-dimensional trajectory correction projectile,in which the control rudder is placed behind the center of mass and can be highly matched with the tail of the projectile,is designed.A projectile body model is established, and a composite control strategy with the new optimized guidance scheme and proportional calculus control method as the main body is designed.The change law of state variable parameters in the uncontrolled and controlled states are analyzed, and the trajectory correction process based on the optimal values of parameters are simulated; Monte Carlo method is used to analyze the dispersion of impact points under the disturbance state. The simulated results show that the actual roll angle of tail rudder controlled projectile is basically consistent with the input command under this control strategy, and the change ranges of speed angle and direction angle in the whole process is only 2° and 7°, respectively. The control correction process based on the optimal values and the final impact point in the disturbance state also ensures that the projectile body can move smoothly and has better deviation correction ability, which further confirms that the designed new projectile model has high feasibility and reference value.

Key words: precision-guided munition, trajectory correction projectile, tail rudder, control strategy, trajectory correction

中图分类号:

TJ761.3

郭首邑, 王良明, 傅健, 雷鑫. 一种新型后舵尾控修正弹的弹道控制仿真[J]. 兵工学报, 2024, 45(7): 2209-2217.

GUO Shouyi, WANG Liangming, FU Jian, LEI Xin. Simulation Research on Ballistic Control of a New Tail Rudder Controlled Trajectory Correction Projectile[J]. Acta Armamentarii, 2024, 45(7): 2209-2217.

图/表 14

图1 控制舵部分的理论结构模型

Fig.1 Theoretical structural model of tail rudder

图2 新型弹体模型的位置示意图

Fig.2 Location diagram of the entire projectile model

图3 制导方案原理图

Fig.3 Schematic diagram of guidance scheme

图4 设定的两种情况

Fig.4 Set two situations

图5 控制策略流程图

Fig.5 Flow chart of control strategy

表1 调节后的控制方案参数值

Table 1 Parameter values of the adjusted control scheme

设定3个参数的最优值	数值
K_P	0.25
K_I	0.6
K_D	0.1

表2 计算前提的基本参数

Table 2 The basic parameter values for the prerequisites for calculation

参数	弹丸前体	控制舵部分
赤道转动惯量/(kg·m^-2)	0.3865	0.003566
极转动惯量/(kg·m^-2)	0.041	0.0034

图6 控制舵的滚转角速度

Fig.6 Roll angular speed of rudder

表3 关键参数的最优值

Table 3 Optimal values of key parameters

参数	数值
控制舵的舵偏角/(°)	2
导转舵的舵偏角/(°)	1
方案两点间隔距离/m	1 500
启控的最低高度/m	1 500
纵向及横向权重比	3∶1

图7 滚转角变化的对比曲线

Fig.7 Alignment curve of roll angle change

图8 弹丸前体的滚转角速度变化图

Fig.8 Diagram of the change in rolling angular speed of the front part of projectile

图9 速度姿态角的变化图

Fig.9 Diagram of the change in velocity attitude angle

图10 弹道的控制修正及落点情况

Fig.10 Control correction of trajectory and impact point

图11 落点散布图

Fig.11 Dispersion of impact points

参考文献 25

[1]	杨志伟, 王良明, 钟扬威, 等. 旋转稳定弹丸非线性角运动吸引域计算方法[J]. 兵工学报, 2021, 42(6):1196-1203.
	YANG Z W, WANG L M, ZHONG Y W, et al. Calculation method of nonlinear angular motion attraction domain of rotationally stabilized projectile[J]. Acta Armamentarii, 2021, 42(6):1196-1203. (in Chinese)
[2]	王中原, 史金光, 常思江, 等. 弹道修正弹技术发展综述[J]. 弹道学报, 2021, 33(2):1-12. doi: 10.12115/j.issn.1004-499X(2021)02-001
	WANG Z Y, SHI J G, CHANG S J, et al. A review of the development of ballistic modified projectile technology[J]. Journal of Ballistics, 2021, 33(2):1-12. (in Chinese)
[3]	冯昌林, 陈峰, 易文俊. 滑翔增程制导炮弹复合导引算法设计及仿真[J]. 兵工学报, 2022, 43(1):128-132.
	FENG C L, CHEN F, YI W J. Design and simulation of composite guidance algorithm for gliding extended range guided projectiles[J]. Acta Armamentarii, 2022, 43(1):128-132. (in Chinese)
[4]	王雅琳, 刘都群, 宋怡然. 2021精确打击武器领域技术发展综述[J]. 战术导弹技术, 2022, 2(6):20-28.
	WANG Y L, LIU D Q, SONG Y R. Overview of technological developments in the field of precision strike weapons[J]. Tactical Missile Technology, 2022, 2(6):20-28. (in Chinese)
[5]	张蛟龙. 鸭式布局双旋弹飞行力学特性研究[D]. 南京: 南京理工大学, 2015.
	ZHANG J L. Study on flight dynamics of canard layout double-spinner[D]. Nanjing: Nanjing University of Science and Technology, 2015. (in Chinese)
[6]	张嘉易, 王广, 郝永平. 二维弹道修正弹鸭舵修正机构气动特性研究[J]. 弹箭与制导学报, 2013, 33(2):88-91.
	ZHANG J Y, WANG G, HAO Y P. Research on aerodynamic characteristics of two-dimensional ballistic correction duck rudder correction mechanism[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2013, 33(2):88-91. (in Chinese)
[7]	汪亚利, 邵伟平, 郝永平, 等. 舵片修正弹丸气动特性仿真研究[J]. 兵器装备工程学报, 2016, 12(6):65-68.
	WANG Y L, SHAO W P, HAO Y P, et al. Simulation study on aerodynamic characteristics of rudder modified projectile[J]. Journal of Ordnance Equipment Engineering, 2016, 12(6):65-68. (in Chinese)
[8]	许巍, 郝永平, 汪亚利, 等. 鸭舵机构对旋转弹丸气动特性作用研究[J]. 弹箭与制导学报, 2017, 36(6):118-120.
	XU W, HAO Y P, WANG Y L, et al. Study on the aerodynamic characteristics of the duck rudder mechanism on the rotating projectile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2017, 36(6):118-120. (in Chinese)
[9]	许巍. 二维修正机构修正策略与模拟仿真分析[D]. 沈阳: 沈阳理工大学, 2017.
	XU W. Two-dimensional correction mechanism correction strategy and simulation analysis[D]. Shenyang: Shenyang Ligong University, 2017. (in Chinese)
[10]	邢炳楠, 杜忠华, 杜成鑫. 二维弹道修正弹及其制导控制技术综述[J]. 国防科技大学学报, 2021, 43(4):53-68.
	XING B N, DU Z H, DU C X. Review of two-dimensional ballistic modified projectiles and their guidance control technology[J]. Journal of National University of Defense Technology, 2021, 43(4):53-68. (in Chinese)
[11]	张鑫, 姚晓先. 固定翼双旋弹修正组件滚转控制研究[J]. 北京理工大学学报, 2020, 40(4):386-395.
	ZHANG X, YAO X X. Research on roll control of fixed-wing dual-rotor correction components[J]. Transactions of Beijing Institute of Technology, 2020, 40(4):386-395. (in Chinese)
[12]	SEVE F, THEODOULIS S, WERNERT P, et al. Flight dynamics modeling of dual-spin guided projectiles[J]. IEEE Transactions on Aerospace and Electronic Systems, 2017, 53(4):1625-1641.
[13]	马国梁, 蔡红明, 常思江. 固定鸭舵双旋弹动态稳定性分析[J]. 兵工学报, 2019, 40(10):8-13.
	MA G L, CAI H M, CHANG S J. Dynamicstability analysis of fixed duck rudder double spin projectile[J]. Acta Armamentarii, 2019, 40(10):8-13. (in Chinese)
[14]	WANG J B. A deep learning approach for atrial fibrillation signals classification based on convolutional and modified Elman neural network[J]. Future Generation Computer Systems, 2020, 102:670-679.
[15]	SHERSTINSKY A. Fundamentals of recurrent neural network and long short-term memory network[J]. Physical D:Nonlinear Phenomena, Elsevier, 2020, 404:132306.
[16]	JIA W K, ZHAO D A, ZHENG Y J, etal. A novel optimized GA-Elman neural network algorithm[J]. Neural Computing and Applications, 2019, 31(2):449-459.
[17]	LEWIS F W, JAGANNATAN S, YESILDIRAK A. Neural network control of robot manipulators and non-linear systems[M]. FL, US: CRC Press, 2020.
[18]	张明环, 马万超, 郭云鹤, 等. 具有鸭舵/尾舵多操纵面的导弹复合控制方法研究[J]. 西北工业大学学报, 2019, 37(5):962-967.
	ZHANG M H, MA W C, GUO Y H, et al. Research on missile composite control method with duck rudder/tail rudder multi-control surface[J]. Journal of Northwestern Polytechnical University, 2019, 37(5):962-967. (in Chinese)
[19]	彭俊然, 陈庆, 邓健辉, 等. 高精度一体化PGK控制算法的仿真设计与实现[J]. 航天控制, 2019, 37(4):27-34.
	PENG J R, CHEN Q, DENG J H, et al. Simulation design and implementation of high-precision integrated PGK control algorithm[J]. Space Control, 2019, 37(4):27-34. (in Chinese)
[20]	殷婷婷. 隔转鸭舵式弹道修正弹固定鸭舵滚转控制系统研究[D]. 南京: 南京理工大学, 2019.
	YIN T T. Research on the rolling control system of fixed canard rudder with a spaced duck rudder ballistic correction projectile[D]. Nanjing: Nanjing University of Science and Technology, 2019. (in Chinese)
[21]	李志鹏, 赵捍东, 王惟, 等. 一种基于神经网络的弹箭飞行控制方法[J]. 弹箭与制导学报, 2014, 34(4):37-40.
	LI Z P, ZHAO H D, WANG W, et al. A projectile flight control method based on neural network[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2014, 34(4):37-40. (in Chinese)
[22]	王钰, 于纪言, 王晓鸣. 摄动落点预测法的快速建模与基于精度最优的分段预测控制法[J]. 兵工学报, 2017, 38(5):867-876. doi: 10.3969/j.issn.1000-1093.2017.05.005
	WANG Y, YU J Y, WANG X M. Fast modeling of perturbation landing point prediction method and segmented prediction control method based on optimal accuracy[J]. Acta Armamentarii, 2017, 38(5):867-876. (in Chinese) doi: 10.3969/j.issn.1000-1093.2017.05.005
[23]	钟扬威, 王良明, 国晨, 等. 旋转稳定二维弹道修正弹落点预测制导方法研究[J]. 火炮发射与控制学报, 2018, 39(3):11-16.
	ZHONG Y W, WANG L M, GUO C, et al. Research on rotationally stable two-dimensional ballistic correction projectile landing point prediction guidance method[J]. Journal of Artillery Firing and Control, 2018, 39(3):11-16. (in Chinese)
[24]	韩子鹏. 弹箭外弹道学[M]. 北京: 北京理工大学出版社, 2014.
	HAN Z P. Exterior ballistics of projectiles and rockets[M]. Beijing: Beijing Institute of Technology Press, 2014. (in Chinese)
[25]	曹红锦. 美国精确制导组件技术发展现状分析[J]. 四川兵工学报, 2015, 36(9):22-25.
	CAO H J. Analysis of the development status of precision guidance component technology in the United States[J]. Journal of Sichuan Ordnance, 2015, 36(9):22-25. (in Chinese)