大展弦比无人机平台的阵风减缓飞行试验  

Flight test for gust alleviation on a high aspect ratio UAV platform

作　　者：周宜涛 杨阳 吴志刚[1] 杨超[1] ZHOU Yitao;YANG Yang;WU Zhigang;YANG Chao(School of Aeronautic Science and Engineering,Beihang University,Beijing 100083,China;China Airborne Missile Academy,Luoyang 471009,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083 [2]中国空空导弹研究院,洛阳471009

出　　处：《航空学报》2022年第6期319-330,共12页Acta Aeronautica et Astronautica Sinica

摘　　要：阵风减缓主动控制技术是飞机应对阵风影响的有力手段,为了对设计的阵风减缓系统进行评估,飞行试验是不可或缺的。由于阵风的精确测量较为困难,如何验证减缓系统是否有效是一个难题,提出一种“开-闭”式统计学试验方法以解决该问题。以一架大展弦比无人机作为试验对象,将基于PID控制原理设计的阵风减缓系统叠加在原飞机的增稳系统上进行了飞行试验。通过统计学方法对试验结果进行分析,结果表明搭载了阵风减缓系统的飞机质心过载降低20.5%,翼根弯矩降低12.9%,验证所提的试验方法可行、有效。Gust alleviation active control technology is a powerful means for aircraft to deal with the impact of gust.In order to evaluate the designed gust alleviation system,flight test is indispensable.However,how to evaluate the effectiveness of the gust alleviation system is a difficult problem,because it is difficult to accurately measure wind gusts under natural conditions.To solve this problem,this paper proposes an“open-close”statistical test method.Taking a large aspect ratio UAV as the test object,the gust alleviation system was designed based on PID control principles and was superimposed on the original aircraft’s stabilization system for flight tests.The results were analyzed by statistical methods which show that the centroid overload of the aircraft equipped with the gust alleviation system is reduced by 20.5%,and the wing root bending moment is reduced by 12.9%,which indicate that the test method proposed in this paper is feasible and effective.

关 键 词：飞行试验 阵风减缓 主动控制 阵风响应 气动弹性 

分 类 号：V217.39[航空宇航科学与技术—航空宇航推进理论与工程]