摘要
为解决新一代空空导弹飞行包线大、飞行环境复杂和气动参数变化剧烈的特点所带来的控制难题，采用“综合方法对不确定性与扰动界的估计以及执行机构特性等，选取了不同环节的权函数，设计了算例空对空导弹纵向鲁棒驾驶仪。对设计结果进行了性能分析，并与传统的PID控制方法进行了比较，结果显示在0．01～100rad／s范围内，采用弘综合控制器的闭环系统结构奇异值几乎在所有频率范围内都小于PID控制器，前者对建模不确定性和扰动的抑制能力要大大优于后者。
The new-generation air-to-air missile has characteristics of large envelope, complex flight environment and dramatic changing aerodynamic parameters. In order to solve the control problem, the corresponding weighted functions are selected by usingμ synthesis. As an example, an air-to-air missile longitudinal robust autopilot is designed based on such criteria as boundary of uncertainties and disturbances and characteristics of actuators. The characteristics of the design results are analyzed. Compared with the classical PID controller, the structured singular value of the closed-loop system withμ-synthesis controller is smaller in almost whole frequency ranges between 0.01 rad/s to 100 rad/s, and the μ-synthesis controller＇s rejection capability against model uncertainty and external disturbances is much better.
出处
《南京理工大学学报》
EI
CAS
CSCD
北大核心
2009年第6期766-769,共4页
Journal of Nanjing University of Science and Technology
基金
南京航空航天大学青年科研基金(1003-906714)
关键词
空空导弹
导弹控制
不确定性建模
鲁棒控制
Μ综合
air-to-air missiles
missile control
uncertainties models
robust control
μsynthesis
