多控制面机翼阵风减缓主动控制与风洞试验验证

Active Control and Wind Tunnel Test Verification of Multi-control Surfaces Wing for Gust Alleviation

针对某大展弦比多控制面弹性机翼风洞模型,分别从频域和时域进行阵风响应分析和阵风响应减缓控制律设计。采用经典控制理论设计控制律,通过操纵位于0.6和0.8翼展处的内外侧控制面减小由正弦阵风引起的翼尖加速度(WTA)。低频段的阵风减缓的数值分析与风洞试验结果均表明:多控制面的阵风减缓效果优于单控制面。当来流速度为14 m/s时,针对频率为2～5 Hz的阵风,采用多控制面得到的WTA减小10%～24%;当来流速度在8～16 m/s时,针对频率为2 Hz的正弦阵风,闭环状态下的翼尖加速度减小10%～40%;结构有限元模型与真实模型存在工程允许的误差导致理论与试验结果存在一定的误差。本文的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 a high aspect ratio elastic wing which has multi-control surfaces,frequency-domain and time-domain approaches to gust response analysis and gust response alleviation control law design are presented.The control laws are designed using classical control theory.The control surfaces,which are located at 0.6 and 0.8 of the wingspan,are manipulated to reduce the wing-tip acceleration（WTA） excited by ＂sine＂ gust.Numerical analysis and test results on the low frequency show that gust alleviation using multi-control surfaces is better than that of single control surface. When the air speed is 14 m/s and the gust frequency ranges from 2-5 Hz, the WTA using multi-control surfaces is alleviated by 10%-24%. When the air speed ranges from 8-16 m/s, the WTA in close-loop is alleviated by 10%-40% for the ＂sine＂ gust whose frequency is 2 Hz. The error between the finite element model and the reality model brings on the error between the results obtained by theory and test. This article are of reference value to extend gust alleviation technique to engineering application.