摘要
在气动弹性领域内对结构 /控制一体化设计作了初步的探索与研究。针对采用加速度传感器的气动伺服弹性模型 ,建立了在拉普拉斯域中颤振速度对结构设计变量及控制设计变量的解析导数表达式。同时也建立了奇异值对结构设计变量的解析导数表达式。对一矩形机翼以输出反馈的形式进行了结构 /控制一体化设计。目标函数为结构重量最轻 ,满足闭环系统颤振速度和以奇异值为基础的鲁棒稳定性指标约束 。
The integrated design of a flexible structure/flutter active control law is researched. For the aeroservoelastic model carrying accelerated sensors with output feedback,the sensitive derivatives of the flutter speed with respect to the structural and control design variables are established in Laplace domain,and the analytical derivative of singular value with respect to the structural design variable is contributed also. Satisfactory results have been obtained by use of a rectangular wing model.The objective function is the minimal structural weight,subject to the inequal constraints of the flutter speed,and robust stability of the closed loop system.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1995年第5期521-527,共7页
Acta Aeronautica et Astronautica Sinica
关键词
一体化设计
鲁棒性
翼面结构
颤振
飞机
integrated design,aeroservoelasticity,derivative,robust
