[1]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(自然科学版),2014,38(01):123-128.
 Chang Sijiang,Wang Zhongyuan,Liu Tiezheng,et al.Guidance laws for air-defense guided projectiles equipped with canards control[J].Journal of Nanjing University of Science and Technology,2014,38(01):123-128.
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鸭舵控制防空制导炮弹导引方法
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《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

卷:
38卷
期数:
2014年01期
页码:
123-128
栏目:
出版日期:
2014-02-28

文章信息/Info

Title:
Guidance laws for air-defense guided projectiles equipped with canards control
作者:
常思江1王中原1刘铁铮2余劲天1
1.南京理工大学 能源与动力工程学院,江苏 南京 210094; 2.中国兵器科学研究院 军贸装备发展部,北京 100089
Author(s):
Chang Sijiang1Wang Zhongyuan1Liu Tiezheng2Yu Jintian1
1.School of Energy and Power Engineering,NUST,Nanjing 210094,China; 2.Department of Military Equipment Development,Ordnance Science Institute of China,Beijing 100089,China
关键词:
制导炮弹 防空 导引方法 弹道预测 剩余飞行时间 修正比例导引
Keywords:
guided projectiles air defense guidance law trajectory prediction time-to-go modified proportional navigation guidance
分类号:
TJ765.4
摘要:
为提高防空炮弹的精确打击能力,该文以一类鸭舵控制的防空制导炮弹为对象,根据防空弹药的作战特点,对弹道预测导引法和修正比例导引法的应用进行了研究。基于三自由度有风质点弹道模型,提出了具有良好精度和较快计算速度的弹道预测解析模型及相应的剩余飞行时间估算公式,并分析了不同条件对预测模型精度的影响; 根据炮弹当前位置和目标未来点间的位置偏差矢量,推导了修正比例导引的加速度指令。理论分析及仿真结果表明,两种导引方法在一定条件下均具有较好的控制效果; 对于不同弹道控制量及不同有效射程,弹道预测导引法适用于防空炮弹的弹道末段,而修正比例导引法则适用于弹道初始段及中段,可满足控制精度和飞行稳定性的要求。
Abstract:
To improve the fire accuracy of air-defense projectiles,taking a type of air-defense guided projectiles with canard control as an object,the application process of trajectory prediction guidance(TPG)and modified proportional navigation guidance(MPNG)is studied in terms of the properties of air-defense projectiles.Based on the 3D trajectory model containing wind,an analytical model for trajectory prediction and the corresponding algorithm for estimating time-to-go are proposed,both of which are of good accuracy.According to the bias vector between the projectile and the future position of maneuvering target,a simple expression of acceleration command for MPNG is derived.Theoretical analysis and simulation results indicate that both of TPG and MPNG are satisfactorily effective under some conditions.For different control quantities and flight ranges,the TPG can be applied to the terminal phase of trajectory while the MPNG is more appropriate for the initial phase and mid-course.Both of the accuracy and stability requirements can be attained.

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相似文献/References:

[1]常思江,王中原,余劲天.鸭舵控制低旋尾翼弹有控弹道参数设计方法[J].南京理工大学学报(自然科学版),2011,(02):173.
 CHANG Si-jiang,WANG Zhong-yuan,YU Jin-tian.Design Method of Controllable Trajectory Parameters for Fin-stabilized Projectiles with Low Spin Speed Equipped with a Pair of Canards[J].Journal of Nanjing University of Science and Technology,2011,(01):173.
[2]王旭刚,王中原.弹体滚速和舵机时间常数对炮弹制导精度的影响[J].南京理工大学学报(自然科学版),2011,(02):182.
 WANG Xu-gang,WANG Zhong-yuan.Effect of Roll Angular Velocity and Actuator Time Constant on Guidance Precision of Guided Projectile[J].Journal of Nanjing University of Science and Technology,2011,(01):182.
[3]修观,王良明.制导炮弹姿态非线性模型预测控制仿真分析[J].南京理工大学学报(自然科学版),2011,(01):66.
 XIU Guan,WANG Liang-ming.Simulation and Analysis of Nonlinear Model Predictive Control for Guided Projectile Attitude[J].Journal of Nanjing University of Science and Technology,2011,(01):66.
[4]史金光,王中原,孙洪辉,等.制导炮弹滑翔弹道优化设计方法研究[J].南京理工大学学报(自然科学版),2011,(05):610.
 SHI Jin-guang,WANG Zhong-yuan,SUN Hong-hui,et al.Optimization Design Method for Glide Trajectory of Guided Projectiles[J].Journal of Nanjing University of Science and Technology,2011,(01):610.

备注/Memo

备注/Memo:
收稿日期:2012-02-26 修回日期:2012-05-09
作者简介:常思江(1983-),男,博士,讲师,主要研究方向:弹箭飞行控制技术、外弹道仿真设计,E-mail:ballistics@126.com。
引文格式: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.
投稿网址:http://njlgdxxb.paperonce.org
更新日期/Last Update: 2014-02-28