摘要
研究了非线性飞行控制律的全局连续设计方法——分支裁剪技术。该方法以分叉分析和连续算法计算得到的飞行动力学系统平衡图为基础,采用特征结构配置方法设计全局调参的纵、横航向解耦反馈控制律,满足飞行品质要求,从而裁剪偏离运动对应的平衡分支;应用前馈控制修改平衡图的主分支形状,使系统输出根据设计要求跟踪操纵输入指令。控制律设计和仿真计算结果表明,采用分支裁剪技术可以系统把握飞行动力学系统的全局特性,在整个包线范围内便捷地设计初步的飞行控制律,为现代飞行器设计阶段的气动布局评估、控制效能确定、设计参数选择等研究工作提供基础。
The bifurcation tailoring technique is used as a global and continuous design method for the nonlinear flight control law. Based on equilibrium branches of flight dynamics calculated by bifurcation analysis and continuation methods, the feedback control law is designed by the eigenstructure assign-ment technique with the characteristic of the global continuation schedule of gains and the uncoupled longitudinal-lateral dynamics. As a result, the requirement of flying qualities is satisfied, and the equilibrium branches of the departure motion are tailored. Then, the shape of the main equilibrium branch is modified by the feedforward control law to make the output variables trace the input commands. Results of the control law design and the simulation show that the bifurcation tailoring technique can be used to control the global characteristics of flight dynamics and design the primary flight control law across the whole flight envelope quickly and conveniently. The technique can be used for the design of modern flight vehicle, such as evaluation of aerodynamic configuration, determination of control power, and selection of design parameters.
出处
《南京航空航天大学学报》
CAS
CSCD
北大核心
2008年第3期302-307,共6页
Journal of Nanjing University of Aeronautics & Astronautics
基金
总装预研资助项目
航空科学基金(2007ZA52010)资助项目
关键词
飞行控制律
分叉分析
连续算法
分支裁剪技术
特征结构配置
飞行力学
flight control law
bifurcation analysis
continuous algorithms
bifurcation tailoring tech-nique
eigenstructure assignment
flight dynamics
