基于线性弹道模型的末段修正弹落点预测

doi:10.3969/j.issn.1000-1093.2015.07.006

兵工学报 ›› 2015, Vol. 36 ›› Issue (7): 1188-1194.doi: 10.3969/j.issn.1000-1093.2015.07.006

基于线性弹道模型的末段修正弹落点预测

李兴隆¹，贾方秀¹，王晓鸣¹，姚文进¹, 吴巍²

（1.南京理工大学智能弹药国防重点学科实验室，江苏南京 210094; 2.63863部队，吉林白城 137001）

收稿日期:2014-10-15 修回日期:2014-10-15 上线日期:2015-09-21
作者简介:李兴隆（1988—），男，博士研究生
基金资助:
中央高校基本科研业务费专项资金项目（30920130122001）

Impact Point Prediction of Terminal Correction Projectile Based on Linear Trajectory Model

LI Xing-long¹, JIA Fang-xiu¹, WANG Xiao-ming¹, YAO Wen-jin¹, WU Wei²

(1.ZNDY of Ministerial Key Laboratory, Nanjing University of Science and Technology, Nanjing 210094, Jiangsu, China;2.Unit 63863 of PLA, Baicheng 137001, Jilin, China)

Received:2014-10-15 Revised:2014-10-15 Online:2015-09-21

摘要/Abstract

摘要： 针对末段修正弹在弹道末段快速预测落点的问题，提出一种将六自由度刚体外弹道模型线性化的方法，得到线性弹道方程组并求其解析解，结合剩余飞行弧长估算公式，推导出弹道落点快速预测解析公式。以六自由度弹道为基准，通过仿真分析了不同射角不同预测点下线性弹道模型预测法的预测精度和解算时间，结果表明该方法对偏流方向的落点预测误差小于8 m，解算速度相比三自由度数值积分落点预测法提高了一个数量级。该方法为弹载计算机进行实时快速弹道解算提供理论依据，对末段修正弹的工程应用具有参考价值。

关键词: 兵器科学与技术, 弹道解算, 落点预测, 末段修正弹, 线性弹道

Abstract: A method of linearizing the 6 degrees of freedom(DOF) rigid trajectory model is proposed for the rapid impact point prediction of terminal correction projectile in terminal trajectory. The linearized trajectory equations and the analytical solution are obtained, and The analytic formula for rapid impact point prediction is derived in combination with the remaining flight arc length estimation formula. With the reference of 6 DOF trajectory, the prediction accuracy and calculation time of this linear trajectory model prediction method are analyzed at different firing angles and prediction points through simulation. The results show that the impact point prediction error is less than 8 m in cross range direction, the solution speed is improved by an order of magnitude compared to 3DOF numerical integral impact point prediction method. The proposed method provides the basis for rapid ballistic calculation in real-time by onboard computer, and also provides a reference for the engineering application of terminal correction projectile.

Key words: ordnance science and technology, trajectory calculation, impact point prediction, terminal correction projectile, linearized trajectory

中图分类号:

TJ012.3

李兴隆，贾方秀，王晓鸣，姚文进, 吴巍. 基于线性弹道模型的末段修正弹落点预测[J]. 兵工学报, 2015, 36(7): 1188-1194.

LI Xing-long, JIA Fang-xiu, WANG Xiao-ming, YAO Wen-jin, WU Wei. Impact Point Prediction of Terminal Correction Projectile Based on Linear Trajectory Model[J]. Acta Armamentarii, 2015, 36(7): 1188-1194.

参考文献

［1］杨俊，钱宇. 基于预测落点导引律的制导炸弹中制导律设计[J]. 计算机仿真, 2011, 28(8):87-89.
YANG Jun, QIAN Yu. Midcourse guidance law design for guided bomb based on impact point predication guidance law[J]. Computer Simulation, 2011,28(8):87-89. (in Chinese)
[2] 常思江,王中原,刘铁铮,等. 鸭舵控制防空制导炮弹导引方法[J]. 南京理工大学学报, 2014, 38(1):123-128.
CHANG Si-jiang, WANG Zhong-yuan, LIU Tie-zheng, et al. Guidance law for air-defense guided projectiles equipped with canards control [J]. Journal of Nanjing University of Science and Technology, 2014, 38(1):123-128. (in Chinese)
[3] 李超旺, 高敏, 宋卫东. 基于摄动原理的火箭弹落点实时预测[J]. 兵工学报, 2014, 35(8): 1164-1171.
LI Chao-wang, GAO Min, SONG Wei-dong. Real-time impact point prediction of rocket projectile based on perturbation theory[J]. Acta Armamentarii, 2014, 35(8): 1164-1171. (in Chinese)
[4] Ollerenshaw D, Costello M. Simplified projectile swerve solution for general control inputs[J]. Journal of Guidance Control & Dynamics, 2012, 31(5):1259-1265.
[5] Burchett B, Costello M. Model predictive lateral pulse jet control of an atmospheric rocket[J]. Journal of Guidance, Control, and Dynamics, 2002, 25(5): 860-867.
[6] Hainz L C, Costello M. Modified projectile linear theory for rapid trajectory prediction[J]. Journal of Guidance, Control, and Dynamics, 2005, 28(5): 1006-1014.
[7] Wernert P, Theodoulis S, Morel Y. Flight dynamics properties of 155 mm spin-stabilized projectiles analyzed in different body frames[C]∥Atmospheric Flight Mechanics Conference. Toronto, Ontario, Canada: AIAA, 2010:1-17.
[8] 修观, 王良明, 杨荣军. 线性弹道模型建立与仿真[J]. 海军工程大学学报, 2010, 22(2):84-91.
XIU Guan, WANG Liang-ming, YANG Rong-jun. Construction and simulation of linear trajectory model [J]. Journal of Naval University of Engineering, 2010, 22(2):84-91. (in Chinese)
[9] 曹小兵. 脉冲末修迫弹弹道特性分析与控制方案设计[D]. 南京：南京理工大学, 2012.
CAO Xiao-bing. Analysis of ballistic characteristics and design of control scheme for terminal trajectory correction mortar projectile equipped with lateral impulses [D]. Nanjing: Nanjing University of Science and Technology, 2012. (in Chinese)
[10] McCoy R L. Modern exterior ballistics: the launch and flight dynamics of symmetric projectiles[M]. Atglen, PA: Schiffer Publishing Ltd, 1999.

[1]	申程, 张连超, 张卓, 朱文亮, 陈雨康. 轻量化弹道解算系统火控修正和瞄准线滤波预测[J]. 兵工学报, 2024, 45(2): 429-442.
[2]	周伯俊, 于传强，刘志浩，柯冰. 基于高压储能的特种车辆快速起竖技术与验证[J]. 兵工学报, 2022, 43(7): 1488-1497.
[3]	高月光，冯顺山，刘云辉，黄岐. 不同端盖厚度的圆柱形装药壳体破片初速分布[J]. 兵工学报, 2022, 43(7): 1527-1536.
[4]	丁天宝，何朝，王良明，林智伟. 高速旋转炮弹宽海拔弹道解算方法[J]. 兵工学报, 2021, 42(1): 209-213.
[5]	韩晋阳, 白春华，檀盼龙. 伞降战斗部毁伤试验落点预测方法研究[J]. 兵工学报, 2020, 41(6): 1077-1084.
[6]	金文奇，宁金贵，王剑，邓波. 基于全膛烧蚀磨损特征的火炮内弹道仿真研究[J]. 兵工学报, 2019, 40(5): 968-977.
[7]	娄伟鹏，郑长松，李和言，陈建文，张周立，马源. 高速《Symbol》v湿式换挡离合器排油阀临界开启和关闭压力研究[J]. 兵工学报, 2017, 38(9): 1665-1672.
[8]	王宪成，杨绍卿，马宁，赵文柱. 车辆柴油机缸套动载荷磨损计算模型研究[J]. 兵工学报, 2017, 38(9): 1673-1680.
[9]	孙皓泽，常天庆，王全东，孔德鹏，戴文君. 一种基于分层多尺度卷积特征提取的坦克装甲目标图像检测方法[J]. 兵工学报, 2017, 38(9): 1681-1691.
[10]	张玉燕，孙莎莎，王振春，曹海要，战再吉. 高速载流电枢表面瞬态温度场仿真与测量[J]. 兵工学报, 2017, 38(9): 1692-1698.
[11]	李臣明，宦超，石怀龙. 某箱式火箭炮对面目标分布式杀伤最优火力分配[J]. 兵工学报, 2017, 38(9): 1699-1704.
[12]	雷娟棉，张嘉炜，谭朝明. 小攻角下船尾外形对旋转弹丸马格努斯效应影响的数值研究[J]. 兵工学报, 2017, 38(9): 1705-1715.
[13]	李泽，闫晓鹏，栗苹，郝新红，王建涛. 扫频式干扰对调频多普勒引信的干扰机理研究[J]. 兵工学报, 2017, 38(9): 1716-1722.
[14]	张浩为，谢军伟，张昭建，宗彬锋，陈唐军. 基于混合自适应遗传算法的相控阵雷达任务调度[J]. 兵工学报, 2017, 38(9): 1761-1770.
[15]	李茂，侯海量，朱锡，黄晓明，李典，陈长海，胡年明. 结构间隙对芳纶纤维增强复合装甲结构抗侵彻性能的影响[J]. 兵工学报, 2017, 38(9): 1797-1805.

基于线性弹道模型的末段修正弹落点预测

Impact Point Prediction of Terminal Correction Projectile Based on Linear Trajectory Model

PDF

可视化

被引次数

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价