[1]吴汉洲,高 敏,王 毅,等.基于摄动理论的动态弹道偏差阈值修正方法[J].弹道学报,2020,32(02):22-28.[doi:10.12115/j.issn.1004-499X(2020)02-004]
 WU Hanzhou,GAO Min,WANG Yi,et al.Dynamic Threshold Correction Method of Trajectory DeviationBased on Perturbation Theory[J].Journal Of Ballistics,2020,32(02):22-28.[doi:10.12115/j.issn.1004-499X(2020)02-004]
点击复制

基于摄动理论的动态弹道偏差阈值修正方法()
分享到:

《弹道学报》[ISSN:1004-499X/CN:32-1343/TJ]

卷:
32
期数:
2020年02期
页码:
22-28
栏目:
出版日期:
2020-06-30

文章信息/Info

Title:
Dynamic Threshold Correction Method of Trajectory DeviationBased on Perturbation Theory
文章编号:
1004-499X(2020)02-0022-07
作者:
吴汉洲1高 敏1王 毅1杨玉良2董 磊3
1.陆军工程大学石家庄校区 导弹工程系,河北 石家庄 050003; 2.陆军工程大学石家庄校区 火炮工程系,河北 石家庄 050003; 3.中国人民解放军66069部队,河南 洛阳 471000
Author(s):
WU Hanzhou1GAO Min1WANG Yi1YANG Yuliang2DONG Lei3
1.Missile Engineering Department,Shijiazhuang Campus,Army University of Engineering,Shijiazhuang 050003,China; 2.Artillery Engineering Department,Shijiazhuang Campus,Army University of Engineering,Shijiazhuang 050003,China; 3.Unit 66069 of PLA,Luoyang 471000,China
关键词:
弹道 二维弹道修正 摄动理论 落点偏差 偏导数
Keywords:
trajectory two-dimensional trajectory correction perturbation theory impact-point deviation partial derivative
分类号:
TJ41
DOI:
10.12115/j.issn.1004-499X(2020)02-004
文献标志码:
A
摘要:
基于摄动落点偏差预测的弹道修正方法具有落点偏差计算精度高,弹上计算量小等优点。研究了基于该理论在二维弹道修正应用中相关的系列问题。基于多元函数的泰勒级数展开理论,推导了完整的摄动落点偏差预测理论模型。基于摄动偏差理论提出了一种修正步长自适应的射角诸元快速求解方法,一般循环解算弹道模型不超过3次即可得到落点误差不超过1 m的射角诸元。基于不同弹道位置上平均弹道误差,给出了偏导数求解中弹道偏差设置方法。提出了一种动态弹道偏差阈值修正方法,选用该方法进行弹道修正,平均弹道修正次数减少29.1%,而弹丸落点CEP增大不明显。
Abstract:
The trajectory correction method based on the perturbation theory of impact-point prediction has the advantages of high accuracy and small amount of calculation. A series of problems related to the application of the perturbation theory to the impact-point prediction in the two-dimensional trajectory correction were studied. Based on the Taylor series expansion theory of multivariate functions,a complete theoretical model for impact-point prediction was derived. Based on the perturbation deviation theory,a modified step-size adaptive method was proposed to solve the shooting angle data quickly. Generally,the firing angle data can be obtained by solving the ballistic model in a cycle no more than 3 times,whose fall-point error is no more than 1 m. Based on the average trajectory error of different trajectory positions,the setting method of trajectory deviation in partial derivative solution was given. The proposed method of dynamic trajectory deviation correction threshold can reduce 29.1% of trajectory correction times without increasing CEP.

参考文献/References:

[1] ROHINSON J W C. On guidance and control for guided artillery projectiles,Part 1:general considerations:FOI-R-3291-SE[R]. Sweden:Swedish Defence Research Agency,2011.
[2]HAHN P V,FREDERICK R A,SLEGEUS N. Predictive guidance of a projectile for hit-to-kill interception[J]. IEEE Transactions on Control Systems Technology,2009,17(4):745-755.
[3]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.
[4]李兴隆,贾方秀,王晓鸣,等. 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 Xinglong,JIA Fangxiu,WANG Xiaoming. Impact point prediction of terminal correction projectile based on linear trajectory model[J]. Acta Armamentarri,2015,36(7):1188-1194.(in Chinese)
[5]张成. 脉冲修正弹药射程预测控制方法[J]. 弹道学报,2010,22(1):20-23.
ZHANG Cheng. Range prediction control method for pulse jet correction projeetdes[J]. Journal of Ballistics,2010,22(1):20-23.(in Chinese)
[6]GHOSH A K,PRAKASH O. Neural models for predicting trajectory performance of an artillery rocket[J]. Journal of Aerospace Computing,Information and Communication,2004,1(2):112-115.
[7]曹营军,朱宗平,李丽春,等. 基于BP人工神经网络的末修弹落点预测导引模式[J]. 弹箭与制导学报,2011,31(6):76-78.
CAO Yingjun,ZHU Zongping,LI Lichun,et al. Impact point prediction guidance mode of terminal trajectory correction projectile based on BP artificial neural networks[J]. Journal of Projectiles,Rockets,Missiles and Guidance,2011,31(6):76-78.(in Chinese)
[8]KRAMER K A,STUBBERUD S C. Impact time and point predicted using a neural extended Kalman filter[C]//The 2nd International Conference on Intelligent Sensors,Sensor Networks and Information Processing. Melbourne,Australia:IEEE,2005:199-204.
[9]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)
[10]王毅,宋卫东,宋谢恩,等. 基于摄动理论的弹道修正榴弹落点偏差预测[J]. 弹道学报,2015,27(3):18-23.
WANG Yi,SONG Weidong,SONG Xieen. Impact-point prediction of trajectory-correction genade based nn perturbation theory[J]. Journal of Ballistics,2015,27(3):18-23.(in Chinese)
[11]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发[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,2014,38(5):867-876.(in Chinese)

相似文献/References:

[1]常思江,王中原,牛春峰.基于卡尔曼滤波的弹箭飞行状态估计方法[J].弹道学报,2010,22(03):94.
 CHANG Si jiang,WANG Zhong yuan,NIU Chun feng.Estimation Approach of Flight State for Guided Projectiles Based on Kalman Filter[J].Journal Of Ballistics,2010,22(02):94.
[2]刘济民,侯志强,宋贵宝,等.乘波外形导弹弹道特性分析与优化设计[J].弹道学报,2010,22(04):19.
 LIU Ji min,HOU Zhi qiang,SONG Gui bao,et al.Trajectory Characteristics Analysis and Optimization Design of Hypersonic WaveriderBased Missile[J].Journal Of Ballistics,2010,22(02):19.
[3]王旭刚,王中原,李小元.一种非线性方案弹道跟踪算法[J].弹道学报,2010,22(04):23.
 WANG Xu gang,WANG Zhong yuan,LI Xiao yuan.Nonlinear Algorithm for Flight Trajectory Tracking[J].Journal Of Ballistics,2010,22(02):23.
[4]杨红伟,甘明刚.基于粒子群算法的防空修正弹控制方法研究[J].弹道学报,2011,23(02):0.
 YANG Hong-wei,GAN Ming-gang.Research on Control Method of Anti-aircraft Correction Ammunition Based on Particle Swarm Optimization[J].Journal Of Ballistics,2011,23(02):0.
[5]杨荣军,王良明,曹小兵,等.低速滚转末修弹修正量估算方法[J].弹道学报,2010,22(02):47.
 YANG Rong jun,WANG Liang ming,CAO Xiao bing,et al.Correction Estimation of LowRolling Terminal Trajectory Correction Projectile[J].Journal Of Ballistics,2010,22(02):47.
[6]张成,曹营军,杨树兴.一种低速滚转弹药脉冲发动机弹道修正方法[J].弹道学报,2008,20(02):45.
 ZHANG Cheng,CAO Ying jun,YANG Shu xing.Trajectory Correction Scheme Based on Pulse Jet for Low Speed Rolling Projectile[J].Journal Of Ballistics,2008,20(02):45.
[7]林献武,王中原,常思江.曲面地表对弹道影响的一种计算方法[J].弹道学报,2008,20(04):12.
 LIN Xian wu,WANG Zhong yuan,CHANG Si jiang.A Calculation Method for Influence of Curved Earth Surface on Calculating Trajectory[J].Journal Of Ballistics,2008,20(02):12.
[8]李臣明,刘怡昕.非对称赤道阻尼力矩对远程火箭弹道的影响[J].弹道学报,2009,21(02):36.
 LI Chen ming,LIU Yi xin.Influence of Unsymmetrical Equatorial Damp Momenton Longrange Rockets Trajectory[J].Journal Of Ballistics,2009,21(02):36.
[9]张广明,高普云,冯志刚,等.基于脉冲点火弹头平面机动的被动段弹道设计[J].弹道学报,2009,21(02):53.
 ZHANG Guang ming,GAO Pu yun,FENG Zhi gang,et al.Design of Trajectory of the Maneuver of Warhead in a PlaneBased on Impulse Firing in the Passive Curve[J].Journal Of Ballistics,2009,21(02):53.
[10]陈琦,王中原,常思江.基于Gauss伪谱法的滑翔弹道快速优化[J].弹道学报,2014,26(02):17.
 CHEN Qi,WANG Zhong yuan,CHANG Si jiang.Rapid Optimization of Gliding Trajectory Based on Gauss Pseudospectral Method[J].Journal Of Ballistics,2014,26(02):17.

备注/Memo

备注/Memo:
收稿日期:2019-11-22基金项目:军队重点预研项目
作者简介:吴汉洲(1989- ),男,博士研究生,研究方向为弹道修正理论与技术。E-mail:whz00717@163.com。
通信作者:高敏(1963- ),男,教授,博导,研究方向为弹箭信息化理论与技术。E-mail:gaomin1103@yeah.net。
更新日期/Last Update: 1900-01-01