制导炮弹末端落角约束积分滑模变结构制导律  被引量:1

Integral Sliding Mode Variable Structure Guidance Law with Landing Angle Constrain of the Guided Projectile

在线阅读下载全文

作  者:魏军辉 孙越林 张俊 WEI Junhui;SUN Yuelin;ZHANG Jun(Naval Research Academy, Beijing 100161, China)

机构地区:[1]海军研究院,北京100161

出  处:《兵器装备工程学报》2019年第S02期103-105,共3页Journal of Ordnance Equipment Engineering

摘  要:建立制导炮弹与目标相对运动方程,得到以弹道视线角和角速率为变量的状态方程;在构建包含视线角和指令落角差积分滑动模态的基础上,采用趋近律设计了落角约束制导律。仿真表明,所设计的落角约束制导律能够使制导炮弹保持弹道平稳,实现落点和落角双重约束下的精确制导。Aiming at the double constraint of the guided projectile on the terminal landing point and angle,the integral sliding mode variable structure control method is adopted to realize the accurate control of the point and angle.By setting up the relative motion equation between the guided projectile and the target,the state equation with trajectory line of sight Angle and angular velocity is obtained.On the basis of constructing sliding modes including sight angle and integral of the command landing angle errors,the guidance law with landing angle constraint is designed by using the approach law.Simulation results show that the proposed algorithm can realize the precise guidance under the double constraints of landing point and angle while keeping the trajectory steady.

关 键 词:制导炮弹 落角约束 滑动模态 制导律 

分 类 号:TJ431.+6[兵器科学与技术—火炮、自动武器与弹药工程]

 

参考文献:

正在载入数据...

 

二级参考文献:

正在载入数据...

 

耦合文献:

正在载入数据...

 

引证文献:

正在载入数据...

 

二级引证文献:

正在载入数据...

 

同被引文献:

正在载入数据...

 

相关期刊文献:

正在载入数据...

相关的主题
相关的作者对象
相关的机构对象