飞翼布局无人作战飞机自动着陆控制系统设计  

Control System Design of a Flying Wing UCAV's Automatic Landing

作　　者：嵇鼎毅[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10期1340-1342,1345,共4页Computer Measurement &Control

基　　金：国家863资助项目(2003AA755021)

摘　　要：飞翼飞机是一种先进的飞行结构。但由于气动外形的特殊,无垂直尾翼的飞翼飞机在着陆阶段,极易受到侧风的干扰,而使其偏离航线;根据飞翼飞机的气动参数,建立了飞翼飞机的非线性数学模型,设计了飞翼无人机的着陆轨迹和控制方案;针对飞翼飞机的特性,采用不同于常规飞机的控制律,设计了抗侧风自动着陆控制系统;设计的控制系统经过非线性仿真试验,结果显示,飞机抗侧风着陆性能达到了设计要求,从而验证了设计方案的可行性。The flying wing aireraft is an advanced aero configuration. Because of its unconventional configuration, the flying wing UCAV is easily disturbed by the erosswind especially in the landing phase, which causes the plane to leave its flight course. Based on the aerodynamic derivatives of the flying wing aircraft, a nonlinear system and the trajectory of landing are devised. According to the characteristics of the flying wing UCAV, three counteracting erosswind control systems are designed by adopting especial control methods which are different from natural plane. Finally, the nonlinear simulation results show that the desired performance of the counteracting erosswind control systems is a- chieved.

关 键 词：飞翼 无人作战飞机 非线性 侧风 着陆 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]