一类大气层内超高速飞行器鲁棒控制器设计研究  

Robust Control for Elastic Hypersonic Vehicles with Uncertainty

作　　者：佘智勇[1] 马广富[1] 

机构地区：[1]哈尔滨工业大学航天学院,黑龙江哈尔滨150001

出　　处：《战术导弹技术》2010年第5期79-83,共5页Tactical Missile Technology

摘　　要：针对一类带有稳定性导数的大气层内超高速飞行器,根据所给出考虑机体弹性弯曲的线性系统模型,计算其特征值与特征向量,确定其各个模态,进而分析其对应模态之间的耦合效应;同时考察控制输入矩阵,分析控制输入对状态量的影响;针对建模过程中的参数不确定性,基于线性矩阵不等式理论,设计渐进稳定控制器,给出工程化设计过程,并分析控制器控制能量的分配性质.仿真结果表明,所设计的控制器能够有效的镇定参数不确定摄动系统.For a kind of hypersonic vehicle with stability derivation,according to the linear system model considering elasticity,eigenvalues and eigen-vectors have been calculated,various modes have been established,then couple effects would been analyzed between modes as while as influence of control input.For parameter uncertainty,based on linear matrix inequation theory,asymptotically stable controller has been designed,energy allocation characters have been analyzed.According to the results given by the simulatio...

关 键 词：稳定性导数 耦合 模态 参数不确定 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]