基于对数型障碍Lyapunov函数的俯仰驾驶仪设计
TJ760%V448.133; 相控阵雷达制导拦截弹在拦截高速大机动目标时,弹体气动参数剧烈非线性变化影响控制系统对大攻角的响应效果,应设计考虑攻角指令跟踪误差约束的鲁棒自动驾驶仪控制律.基于双幂次趋近律和对数型障碍李雅普诺夫函数设计了鲁棒非线性自动驾驶仪控制律,可将攻角指令的跟踪误差快速收敛于约束范围内.通过降阶扩张状态观测器对系统中存在的气动参数不确定性和系统外部扰动进行在线估计和补偿.稳定性分析和数值仿真表明,攻角可在 1s内达到稳态且攻角响应的稳态误差＜10-4°,所提出的自动驾驶仪控制律具有较强的鲁棒性,能够准确稳定地跟踪攻角指令,控制导弹产生所需过载进而精准拦截目标....
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| Published in | 航空兵器 Vol. 31; no. 2; pp. 106 - 113 |
|---|---|
| Main Authors | , , , , |
| Format | Journal Article |
| Language | Chinese |
| Published |
北京理工大学 宇航学院,北京 100081
30.04.2024
北京理工大学 中国-阿联酋智能无人系统"一带一路"联合实验室,北京 100081%中国兵器科学研究院,北京 100089%西北工业集团有限公司,西安 710043 |
| Subjects | |
| Online Access | Get full text |
| ISSN | 1673-5048 |
| DOI | 10.12132/ISSN.1673-5048.2023.0108 |
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| Abstract | TJ760%V448.133; 相控阵雷达制导拦截弹在拦截高速大机动目标时,弹体气动参数剧烈非线性变化影响控制系统对大攻角的响应效果,应设计考虑攻角指令跟踪误差约束的鲁棒自动驾驶仪控制律.基于双幂次趋近律和对数型障碍李雅普诺夫函数设计了鲁棒非线性自动驾驶仪控制律,可将攻角指令的跟踪误差快速收敛于约束范围内.通过降阶扩张状态观测器对系统中存在的气动参数不确定性和系统外部扰动进行在线估计和补偿.稳定性分析和数值仿真表明,攻角可在 1s内达到稳态且攻角响应的稳态误差＜10-4°,所提出的自动驾驶仪控制律具有较强的鲁棒性,能够准确稳定地跟踪攻角指令,控制导弹产生所需过载进而精准拦截目标. |
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| AbstractList | TJ760%V448.133; 相控阵雷达制导拦截弹在拦截高速大机动目标时,弹体气动参数剧烈非线性变化影响控制系统对大攻角的响应效果,应设计考虑攻角指令跟踪误差约束的鲁棒自动驾驶仪控制律.基于双幂次趋近律和对数型障碍李雅普诺夫函数设计了鲁棒非线性自动驾驶仪控制律,可将攻角指令的跟踪误差快速收敛于约束范围内.通过降阶扩张状态观测器对系统中存在的气动参数不确定性和系统外部扰动进行在线估计和补偿.稳定性分析和数值仿真表明,攻角可在 1s内达到稳态且攻角响应的稳态误差＜10-4°,所提出的自动驾驶仪控制律具有较强的鲁棒性,能够准确稳定地跟踪攻角指令,控制导弹产生所需过载进而精准拦截目标. |
| Abstract_FL | When the phased array radar-guided missile intercepts a high speed target with large maneuve-ring,the aerodynamic parameters of the missile body vary dramatically and become nonlinear,which affects the response of the control system to the large angle-of-attack,the robust autopilot control law should be designed considering the tracking error constraint of the angle-of-attack command.A robust nonlinear autopilot control law is designed based on the double power reaching law and logarithmic barrier Lyapunov function can make the tracking error of the angle-of-attack command converge to the constraint range rapidly.The aerodynamic parame-ter uncertainty and external disturbance of the system are estimated and compensated online by using the reduced order extended state observer.Stability analysis and numerical simulation show the angle-of-attack can reach a steady state within 1 second and the steady-state error of the angle-of-attack response＜10-4°.The proposed au-topilot control law has strong robustness,can accurately and stably track the command of angle of attack,control the missile produces the required overload accurately to intercept the target. |
| Author | 林时尧 王伟 王宏 杨婧 王少龙 |
| AuthorAffiliation | 北京理工大学 宇航学院,北京 100081;北京理工大学 中国-阿联酋智能无人系统"一带一路"联合实验室,北京 100081%中国兵器科学研究院,北京 100089%西北工业集团有限公司,西安 710043 |
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| Author_FL | Wang Shaolong Yang Jing Wang Hong Wang Wei Lin Shiyao |
| Author_FL_xml | – sequence: 1 fullname: Wang Wei – sequence: 2 fullname: Yang Jing – sequence: 3 fullname: Lin Shiyao – sequence: 4 fullname: Wang Hong – sequence: 5 fullname: Wang Shaolong |
| Author_xml | – sequence: 1 fullname: 王伟 – sequence: 2 fullname: 杨婧 – sequence: 3 fullname: 林时尧 – sequence: 4 fullname: 王宏 – sequence: 5 fullname: 王少龙 |
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| DocumentTitle_FL | Robust Pitch Autopilot Design Based on Logarithmic Barrier Lyapunov Method |
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| Keywords | 鲁棒非线性自动驾驶仪 扩张状态观测器 extended state observer robust nonlinear autopilot double power reaching law 双幂次趋近律 障碍李雅普诺夫函数 barrier Lyapunov function |
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| Title | 基于对数型障碍Lyapunov函数的俯仰驾驶仪设计 |
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