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飞翼布局飞机具有优越的隐身和气动特性,但由于布局原因无法配置常规控制面,因此常规布局飞机的阵风减缓控制方法不再适用。针对大展弦比飞翼布局飞机,设计了风洞模型、具有沉浮和俯仰2个方向自由度的支持系统以及能够产生连续正弦阵风的阵风发生器,采用经典控制律理论设计了能够同时减缓翼尖过载和翼根弯矩的3组控制方案,开展了阵风减缓主动控制风洞试验,对开、闭环试验数据进行了分析。试验数据表明,和正常式布局飞机不同,阵风引起的飞翼布局飞机的翼尖过载和翼根弯矩在俯仰模态对应的频率处有一个很大的峰值,而在一弯频率附近峰值比较小;对于不同控制面组合,阵风减缓效果不一样;对于飞翼布局飞机,选用合适的控制面组合可以有效减缓阵风载荷和阵风响应。
Flying wing layout The aircraft has superior stealth and aerodynamic characteristics, but due to layout reasons can not be configured conventional control plane, the conventional layout of the aircraft gust mitigation control method is no longer applicable. The wind tunnel model is designed for large aspect ratio flying wing aircraft. The support system with two degrees of freedom in the ups and downs and pitching, as well as the gust generator capable of generating continuous sinusoidal gusts, are designed using the classical control law theory Three control schemes of tip overloading and wing root bending moment, wind tunnel test of gust mitigation active control was carried out, and open and closed loop test data were analyzed. The experimental data show that, unlike the normal layout aircraft, the wing tip overburden and the root bending moment caused by gusts have a very large peak at the frequency corresponding to the pitch mode, while the peak near the bend frequency For different control plane combinations, gust mitigation effects are not the same; for the flying wing layout aircraft, the selection of a suitable control plane combination can effectively reduce the gust load and gust response.