[1]宋谢恩,高 敏,李超旺,等.弹道修正火箭弹修正方案与射击精度研究[J].弹道学报,2020,32(01):38-46.[doi:10.12115/j.issn.1004-499X(2020)01-006]
 SONG Xieen,GAO Min,LI Chaowang,et al.Research on Correction Method and Firing Accuracyof Trajectory Correction Rocket[J].Journal Of Ballistics,2020,32(01):38-46.[doi:10.12115/j.issn.1004-499X(2020)01-006]
点击复制

弹道修正火箭弹修正方案与射击精度研究()
分享到:

《弹道学报》[ISSN:1004-499X/CN:32-1343/TJ]

卷:
32
期数:
2020年01期
页码:
38-46
栏目:
出版日期:
2020-03-31

文章信息/Info

Title:
Research on Correction Method and Firing Accuracyof Trajectory Correction Rocket
文章编号:
1004-499X(2020)01-0038-09
作者:
宋谢恩高 敏李超旺王 毅吴汉洲
陆军工程大学 石家庄校区,河北 石家庄 050003
Author(s):
SONG XieenGAO MinLI ChaowangWANG YiWU Hanzhou
Shijiazhuang Campus,Army Engineering University,Shijiazhuang 050003,China
关键词:
脉冲推冲器 阻力板 弹道修正弹 弹道仿真实验 飞行试验 落点散布
Keywords:
impulse jet drag brake trajectory correction projectile trajectory simulation experimentation flight test impact point dispersion
分类号:
TJ012.3
DOI:
10.12115/j.issn.1004-499X(2020)01-006
文献标志码:
A
摘要:
为了提高弹药射击精度,采用脉冲推冲器和阻力板作为修正执行机构对弹道进行修正。针对不同修正方案,建立了各自对应的的六自由度弹道模型,设计了以落点预测为基础的控制策略。在分析、比较单一执行机构弹道修正特点的基础上,提出了组合修正方案。以某型火箭弹为应用对象,对不同修正方案的弹道修正效果进行了仿真实验。结果表明:脉冲推冲器对横向偏差修正效果明显,对纵向偏差修正能力不足; 阻力板对纵向偏差修正效果明显,无法消除横向偏差; 组合修正方案对横向偏差和纵向偏差都具有较好的修正效果,能将火箭弹的圆概率误差提高到28 m。最终通过飞行试验对上述结论进行了验证,结果验证了组合修正方案对弹道修正的有效性。
Abstract:
In order to improve the firing accuracy of ammunition,impulse jets and drag brakes were used to correct the trajectory. Aiming at different correct methods,the 6-degrees of freedom trajectory equations corresponding to impulse jects and drag brakes were constructed. The control method was proposed based on impact point prediction. After analyzing impulse jets and drag brakes separately,a combined correction strategy was put forward. In view of a typical rocket projectile,Monte-Carlo simulations were performed to analyze the trajectory correction precision of different correction methods. Results show that the correction effect of impulse jet on lateral deviation is obvious,and the capacity of impulse jets correcting the longitudinal deviation is inadequate. The drag brake can reduce the longitudinal deviation significantly,and it can’t eliminate the lateral deviation. The combined method is the best choice to decrease both lateral and longitudinal deviation,and the circular probable error can be improved to 28 meters. The above conclusions were validated by flight tests. The result shows that the combined trajectory correction method is effective.

参考文献/References:

[1] 曹营军,杨树兴,李杏军. 基于脉冲控制的末段弹道修正弹点火相位优化研究[J]. 兵工学报,2008,29(8):897-901.
CAO Yingjun,YANG Shuxing,LI Xingjun. Research on firing phase angle optimization of terminal trajectory correction projectile based on pulse jet control[J]. Acta Armamentarii,2008,29(8):897-901.(in Chinese)
[2]杨红伟,窦丽华,甘明刚. 防空弹道修正弹脉冲执行机构的控制方法[J]. 北京理工大学学报,2011,31(10):1184-1188.
YANG Hongwei,DOU Lihua,GAN Minggang. Control method of impulse actuator of antiaircraft trajectory correction projectile[J]. Transactions of Beijing Institute of Technology,2011,31(10):1184-1188.(in Chinese)
[3]刘松,范宁军. 弹体姿态调控引信系统设计与仿真[J]. 兵工学报,2010,31(1):18-22.
LIU Song,FAN Ningjun. The design and simulation of munition attitude correction fuze system[J]. Acta Armamentarii,2010,31(1):18-22.(in Chinese)
[4]李超旺,高敏,刘秋生,等. 脉冲推冲器性能参数确定与试验验证研究[J]. 现代防御技术,2015,43(5):77-82.
LI Chaowang,GAO Min,LIU Qiusheng,et al. Parameters determination and confirmation experimentation of lateral pulse jet[J]. Modern Defence Technology,2015,43(5):77-82.(in Chinese)
[5]常思江,王中原,史金光,等. 阻尼片横向弹道修正的落点预测方法[J]. 弹道学报,2015,27(2):14-18.
CHANG Sijing,WANG Zhongyuan,SHI Jinguang,et al. Impact point prediction method for lateral trajectory correction with spin brakes[J]. Journal of Ballistics,2015,27(2):14-18.(in Chinese)
[6]吴汉洲,宋卫东,王毅,等. 一维弹道修正弹飞行稳定性研究[J]. 计算机测量与控制,2016,24(1):132-136.
WU Hanzhou,SONG Weidong,WANG Yi,et al. Research of stability of flight of one dimension trajectory correction projectile[J]. Computer Measurement & Control,2016,24(1):132-136.(in Chinese)
[7]王巍,陈卫东,张宝财,等. 多管火箭弹射击精度的复合形法优化[J]. 哈尔滨工程大学学报,2014,35(9):1112-1116.
WANG Wei,CHEN Weidong,ZHANG Baocai,et al. Firing accuracy optimization of the multi-tube rocket based-on composite method[J]. Journal of Harbin Engineering University,2014,35(9):1112-1116.(in Chinese)
[8]贺军义,芮筱亭,王国平,等. 提高多管火箭射击密集度设计技术研究[J]. 振动工程学报,2011,24(6):676-681.
HE Junyi,RUI Xiaoting,WANG Guoping,et al. Design technology of improving firing dispersion of MLRS[J]. Journal of Vibration Engineering,2011,24(6):676-681.(in Chinese)
[9]王江,林德福,祁载康. 脉冲直接力控制简易制导弹药命中精度研究[J]. 系统仿真学报,2008,20(15):4176-4178.
WANG Jiang,LIN Defu,QI Zaikang. Research of hit accuracy based on pulse direct force control of simple guidance ammunition[J]. Journal of System Simulation,2008,20(15):4176-4178.(in Chinese)
[10]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.
WANG Yu,YU Jiyan,WANG Xiaoming. Rapid impact-point prediction modeling based on perturbation theory and piecewise prediction control method[J]. Acta Armamentarii,2017,38(5):867-876.(in Chinese)
[11]赵捍东. 脉冲发动机提供控制力的火箭弹弹道修正理论及技术研究[D]. 南京:南京理工大学,2008:49-89.
ZHAO Handong. The study of theory and technique for rocket trajectory correction by the control force of lateral push jet[D]. Nanjing:Nanjing University of Science & Technology,2008:49-89.(in Chinese)
[12]盛启辉. 基于脉冲发动机的旋转火箭弹简易控制系统研究[D]. 哈尔滨:哈尔滨工程大学,2013.
SHENG Qihui. Research on simple control system of the spinning artillery rocket based on pulse jet[D]. Harbin:Harbin Engineering University,2013.(in Chinese)
[13]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 Chaowang,GAO Min,SONG Weidong. Real-time impact point prediction of rocket projectile based on perturbation theory[J]. Acta Armamentarii,2014,35(8):1164-1171.(in Chinese)
[14]胡荣林,李兴国. 确定射程弹道修正弹阻力器展开时刻的算法研究[J]. 兵工学报,2008,29(2):235-239.
HU Ronglin,LI Xingguo. Research on deciding the deployment time of damper for correction projectiles[J]. Acta Armamentarii,2008,29(2):235-239.(in Chinese)
[15]史金光,王中原,曹小兵,等. 一维弹道修正弹气动力计算方法和射程修正量分析[J]. 火力与指挥控制,2010,35(7):80-83.
SHI Jinguang,WANG Zhongyuan,CAO Xiaobing,et al. Aerodynamic calculational method and range correction analysis of the dimensional trajectory correction projectile[J]. Fire Control & Command Control,2010,35(7):80-83.(in Chinese)
[16]PHILIP V H,ROBERT A F,NATHAN S. Predictive guidance of a projectile for hit-to-kill interception[J]. IEEE Transactions on Control Systems Technology,2009,17(4):745-755.
[17]RAVINDRA V C,BAR-SHALOM Y,WILLETT P. Projectile identification and impact point prediction[J]. IEEE Transactions on Aerospace and Electronic Systems,2010,46(4):2004-2021.
[18]母文词,黎春明. 某型火箭弹横向射击密集度分析及控制措施[J]. 机械工程师,2014(3):240-242.
MU Wenci,LI Chunming. Transverse firing dispersion analysis and control measures for a certain rocket projectile[J]. Mechanical Engineer,2014(3):240-242.(in Chinese)

备注/Memo

备注/Memo:
收稿日期:2019-05-31
作者简介:宋谢恩(1988- ),男,博士研究生,研究方向为外弹道学理论与技术。E-mail:songxieen@163.com
更新日期/Last Update: 2020-03-30