飞翼式UCAV着陆段纵向飞行控制律研究  

Study of Longitudinal Flight Control Law of a Flying Wing UCAV During Landing

作　　者：丁立冬[1] 陆宇平[1] 

机构地区：[1]南京航空航天大学自动化学院,江苏南京210016

出　　处：《计算机测量与控制》2007年第7期882-884,886,共4页Computer Measurement &Control

基　　金：国家863基金资助项目(2003AA755021)

摘　　要：针对飞翼式无人机着陆段的控制要求,需要精心设计纵向内回路控制律及着陆轨迹曲线,从而实现着陆轨迹的精确跟踪;采用线性矩阵不等式(LMI)方法设计了纵向姿态回路控制律,在设计过程中结合了线性二次型原理,并实现了区域极点配置、控制量约束等多目标控制;在此基础上,设计了着陆轨迹曲线并进行了非线性仿真试验;仿真结果表明,飞机着陆段性能达到了设计要求,并且优于常规的PID控制,从而验证了设计方案的可行性。For the control requirements during landing, longitudinal control system and trajectory of landing should be well -designed, thus, trajectory of landing will be tracked accuralely, A flight control law based on linear matrix inequality （LMI） for longitudinal pitch attitude control system is designed. Combining with the principle of linear quadric, multi -objective control including pole placement and controlled variable constraints is achieved during the designing process. Based on these, trajectory of landing is designed and then nonlinear simulation is carried out. The simulation results show that the performance during landing achieve the index and it is superior to conventional PID control, thus, this design approach is feasible.

关 键 词：飞翼 纵向 轨迹 线性矩阵不等式(LMI) 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]