[1]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):182-186.
 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,(02):182-186.
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弹体滚速和舵机时间常数对炮弹制导精度的影响
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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:
期数:
2011年02期
页码:
182-186
栏目:
出版日期:
2011-04-30

文章信息/Info

Title:
Effect of Roll Angular Velocity and Actuator Time Constant on Guidance Precision of Guided Projectile
作者:
王旭刚王中原
南京理工大学能源与动力工程学院,江苏南京210094
Author(s):
WANG Xu-gangWANG Zhong-yuan
School of Energy and Power Engineering,NUST,Nanjing 210094,China
关键词:
制导炮弹 滚转速度 舵机时间常数 制导精度
Keywords:
guided projectiles roll angular velocity actuator time constant guidance precision
分类号:
TJ410.3
摘要:
通过建立滚转制导炮弹的动力学模型,分析了弹体滚转速度与舵机时间常数对于炮弹落点精度的影响。采用2对舵面控制俯仰与偏航运动的制导炮弹,它的舵系统输入指令为三角函数。随着滚速的提高和舵机时间常数的增大,舵系统的跟踪误差加大;在舵系统输入指令中适当增加相位超前角时,舵系统的跟踪精度显著提高,相位超前角约为弹体滚速和舵机时间常数的乘积。对包含舵指令转换方程和舵机动力学方程的制导炮弹动力学模型进行仿真。仿真结果表明,当弹体滚速为5 r/s,时间常数为0.01时,相位补偿前的落点误差为50.31 m;增加相位超前角2.5,°落点误差为5.14 m。说明选择与弹体滚速和时间常数相匹配的相位补偿角可大大提高制导炮弹的落点精度。该文分析结果可为炮弹滚转速度选择和舵机系统设计提供参考。
Abstract:
This paper presents the effect of the actuator time constant and roll angular velocity on the fall point accuracy of the guided projectile by building a dynamic model.The input commands of an actuator are trigonometric functions when the guided projectile is equipped with a pair of control surfaces to control the pitch and yaw.The tracking error of the actuator increases with the increment of the roll angular velocity and the actuator time constant.If the proper phase lead angle is added to the input commands of an actuator,the tracking precision of an actuator is enhanced.The phase lead angle is obtained assumably using the product of the actuator time constant and the roll angular velocity.The six degrees of freedom simulation is done with the dynamic model of the guided projectile which includes the transform functions of the actuator commands and the dynamic equations of an actuator.The simulation result shows that the guidance precision increases from 50.31 m to 5.14 m with the phase lead angle 2.5°,the body roll angle velocity 5 r/s and the actuator time constant 0.01 s.The fall point accuracy of the projectile can be enhanced greatly by selecting the proper phase lead angle matching the roll angular velocity and the actuator time constant.The analytical results can be used as the reference to the selection of the roll angular velocity and the design of an actuator.

参考文献/References:

[1] Mehul P,Zak H,Russ S. Aerodynamic control of a small projectile[A]. 4th AIAA Aerospace Science Meeting and Exhibit[C]. Nevada,USA: AIAA, 2006: 1 -24.
[2] Glebocki R,Zugui M. Gasodynamic control system for INS guided bomb[A]. 47th AIAA Aerospace Science Meeting[C]. Florida,USA: AIAA, 2009: 1 - 13.
[3] 易文俊,王中原,史金光,等. 带鸭舵滑翔增程炮弹 方案弹道研究[J]. 南京理工大学学报( 自然科学 版) , 2008, 32( 3) : 322 - 326.
[4] 史金光,王中原,曹小兵,等. 滑翔增程弹滑翔弹道 设计[J]. 南京理工大学学报( 自然科学版) ,2007, 31( 2) : 147 - 150.
[5] 穆育强,盛安冬. 制导炸弹命中精度的仿真研究 [J]. 系统仿真学报,2009, 21( 3) : 730 - 734.
[6] 钱杏芳,林瑞雄,赵亚男. 导弹飞行力学[M]. 北京: 北京理工大学出版社,2000.
[7] 王强. 21 世纪末制导弹药的发展预测[J]. 制导与 引信, 2004, 25( 1) : 5 - 10.
[8] 吴甲生,雷娟棉. 制导兵器气动布局与气动特性 [M]. 北京: 国防工业出版社,2008.

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备注/Memo

备注/Memo:
作者简介:王旭刚( 1979 - ) ,男,讲师,主要研究方向: 飞行器动力学制导与控制,E-mail: xgwang@ yahoo. cn。
更新日期/Last Update: 2012-04-30