%0 Journal Article
%T 飞翼布局无人机阵风减缓主动控制研究<br>Active Control of Gust Alleviation for Flying Wing Configuration UAV
%A 刘伏虎
%A 马晓平
%A 张子健
%J 机械科学与技术
%D 2015
%X 阵风减缓是弹性飞行器研究的重要内容之一,针对某大展弦比飞翼布局弹性无人机,考虑刚体模态俯仰控制回路提出了阵风减缓控制方案,在控制器设计前后分别进行模型降阶,设计出低阶的输出反馈鲁棒控制器,闭环系统控制仿真结果显示对于离散突风翼尖加速度响应最大振幅减小21.8%,重心加速度响应最大振幅下降39%;对于连续阵风整个频带内阵风响应都得到有效控制,且在6.024 Hz处翼尖过载响应振幅下降53%,重心过载响应振幅下降45%,同时由抗阵风不灵敏度研究表明整个闭环系统具有抗阵风干扰能力。<br>Gust alleviation is the main research aspect on elastic aircraft. Combined rigid mode pitch control loop and elastic model control loop, the gust alleviation control schemes is proposed for a flying wing configuration elastic unmanned aerial vehicle(UAV). The low order output feedback controller is designed based on model reduction technique. The close loop system simulation results show that the wingtip acceleration maximum vibration range decreases 21.8% and acceleration maximum vibration range at center of gravity decreases 39% to the discrete gust. The continuous gust responses are alleviated effectively in all frequency ranges. Especially the wingtip load factor vibration range decreases 53% and acceleration vibration range at center of gravity decreases 45% at 6.024Hz. At the same time, the gust insensitivity calculation validates that the close loop system could keep insensitivity to gust
%K 阵风减缓
%K 飞翼布局
%K 模型降阶
%K 鲁棒控制
%K 灵敏度&lt
%K br&gt
%K acceleration
%K aeroelasticity
%K angular velocity
%K calculations
%K closed loop systems
%K control surfaces
%K controllers
%K design
%K efficiency
%K flying wing configuration
%K gust alleviation
%K Mach number
%K MATLAB
%K matrix algebra
%K model reduction
%K power spectral density
%K robust control
%K rocket nozzles
%K sensitivity
%K structural dynamics
%K transfer functions
%K unmanned aerial vehicles(UAV)
%K vibrations(mechanical)
%U http://journals.nwpu.edu.cn/jxkxyjs/CN/abstract/abstract5898.shtml