弹性机翼阵风响应和载荷减缓与风洞试验验证

GUST RESPONSE,LOAD ALLEVIATION AND WIND-TUNNEL EXPERIMENT VERIFICATION OF ELASTIC WING

针对弹性机翼风洞模型,采用经典控制理论设计能够同时减缓翼尖加速度(WTA)和翼根弯矩(WRBM)的阵风减缓控制律。试验在航天空气动力技术研究院FD-09低速风洞进行。风洞试验段尺寸为3m×3m。理论和试验结果均表明,当来流速度为14m/s时,针对频率为2Hz―3Hz的阵风,阵风减缓控制律可使WTA和WRBM分别减小25%―35%和30%―40%。当来流速度为10m/s―16m/s时,针对频率为2Hz的阵风,阵风减缓控制律使WTA和WRBM分别减小27%―34%和30%―40%。本算例中控制律在低频段对WTA的减缓效果直接影响该控制律对WRBM的减缓效果。结构有限元模型与真实模型存在工程允许的误差使得理论与试验结果存在一定的误差。相关工作对工程实际中采用阵风减缓技术具有参考价值。

Based on a wind-tunnel model of an elastic wing,the gust response and the load alleviation control law design using classical control theory are presented.The test is performed in the FD-09 low-speed wind tunnel with the size of 3m×3m,which is located at China Academy of Aerospace Aerodynamics.Numerical analysis and test results show that（1） the wing tip acceleration（WTA） is alleviated by 25%―35% and the wing-root bending moment（WRBM） is alleviated by 30%―40% when the air speed is 14m/s and the gust frequency ranges from 2 to 3Hz;（2） the WTA in closed-loop is alleviated by 27%―34% and the WRBM in closed-loop is alleviated by 30%―40% when the air speed ranges from 10 to 16m/s and the gust frequency is 2Hz.In this study,the alleviation effect of WTA on the low frequency has direct influence on the alleviation effect of WRBM.The error between the finite element model and the reality model causes the error between the theoretical result and test result.