Mixed H_2/H_∞ Control Using a Fuzzy Singularly Perturbed Model with Multiple Perturbation Parameters for Gust Load Alleviation

This paper presents a mixed H2/H∞ control using fuzzy singularly perturbed model (FSPM) with multiple perturbation parameters. Since FSPM with multiple perturbation parameters is an extension of models with a single perturbation parameter, the theoretical results are applicable to a larger class of systems described by multiple time scale nonlinear models, such as flying aircraft and flexible space robots. The parameter-independent solution of the mixed H2/H∞ controller was obtained in the form of linear ma...     

ε-Dependent Controllability for Two Time-Scale Systems

This paper investigates the controllability of two time-scale systems using both the time-scale separation model and the slow-fast order reduction model.This work considers the effect of a singular perturbation parameter on the model transformations to improve the criterion precision.The Maclaurin expansion method and homotopy arithmetic are introduced to obtainε-dependent controllability criteria.Examples indicate that theε-dependent controllability criteria are more accurate and that the controllabilit...     

基于控制分配的飞翼式飞机机动载荷控制研究

针对飞翼式飞机的非常规气动布局特点和传统的机动载荷控制方案存在的问题,将控制分配技术应用于机动载荷控制系统,得到了一种基于多操纵面优化分配的机动载荷控制方案.然后,采用分布估计算法以翼根弯矩为优化指标进行控制分配,实现了机动载荷控制,同时提供了一种翼根弯矩的估算方法,为优化算法的实施提供了便利.仿真结果验证了本方法的有效性.     

Mixed H2/H∞ Control Using a Fuzzy Singularly Perturbed Model with Multiple Perturbation Parameters for Gust Load Alleviation

This paper presents a mixed H2/H∞ control using fuzzy singularly perturbed model (FSPM) with multiple perturbation parameters. Since FSPM with multiple perturbation parameters is an extension of models with a single perturbation parameter, the theoretical results are applicable to a larger class of systems described by multiple time scale nonlinear models, such as flying aircraft and flexible space robots. The parameter-independent solution of the mixed H2/H∞ controller was obtained in the form of linear matrix inequalities (LMIs). The application of this approach to gust load alleviation of a flying vehicle verifies its effectiveness and flexibility.