先进战斗机全动V尾抖振动强度设计与验证  

Strength desigh and test of advanced fighter all-moving twin V-tail buffet

作　　者：金伟[1] 杨智春[2] 孟德虹[3] 陈炎[1] 黄虎[1] 王勇军 何石[4] 陈园方[1] JIN Wei;YANG Zhichun;MENG Dehong;CHEN Yan;HUANG Hu;WANG Yongjun;HE Shi;CHEN Yuanfang(AVIC Chengdu Aircraft Design and Research Institute,Chengdu 610091,China;School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;China Aerodynamics Research and Development Center,Mianyang 621000,China;China Aircraft Strength Research Institute,Xi’an 710065,China)

机构地区：[1]中国航空工业成都飞机设计研究所,成都610091 [2]西北工业大学航空学院,西安710072 [3]中国空气动力研究与发展中心,绵阳621000 [4]中国飞机强度研究所,西安710065

出　　处：《航空学报》2020年第6期311-325,共15页Acta Aeronautica et Astronautica Sinica

摘　　要：大迎角(AoA)机动飞行能力是先进战斗机的标志性指标之一,中国先进战斗机采用V型垂尾布局的气动设计方案,可充分实现其良好的大迎角机动可控飞行。飞机在大迎角机动飞行时,前机身分离流所产生的高强度脱体涡破裂后产生的非定常扰流将不可避免地打在V型垂尾翼面上,导致V尾结构发生严重的抖振,这不仅会影响飞机的飞行品质等性能,还会导致V尾结构的疲劳损伤,大幅增加飞机的使用维护成本。本文详细阐述了其研发设计过程中攻克的以下关键技术:全动V尾抖振风洞试验"刚/弹"组合模型的设计技术与风洞试验方法,抖振风洞试验的动态测试结果向飞机尺度进行相似转换的原理;基于RANS/LES混合算法进行V尾结构抖振响应的CFD/CSD耦合计算方法;基于正加速度反馈(PAF)的V尾抖振响应压电控制技术;V尾抖振动态疲劳载荷谱的编谱方法与试验实施方案。本文为解决中国先进战斗机、无人机V尾结构抗抖振动强度设计与验证建立了一套较完备理论分析技术、设计准则和试验方法。High Angle of Attack(AoA)maneuverability is the symbolic characteristic of the fourth generation fighter.Our advanced fighter utilizes twin V-tails configuration,and this sort of aerodynamic design is proved to be well controllable at high AoA maneuvering flight.During high AoA maneuvering flight,the strong flow disturbance induced by the burst vortex shedding from fore-body impinge inevitably on the twin V-tails,and will induce severe buffet.The V-tails buffet will cause not only remarkable reduction of flight quality,but also structural fatigue damage,leading to high maintenance cost.This paper describes in detail the key techniques achieved during the engineering manufacturing and design of an aircraft with all-moving twin V-tails,which include:the design technique of rigid/flexible hybrid model and testing methods of all-moving V-tail buffet wind tunnel test,as well as the principle of similarity transformation method which transforms test data from buffet wind tunnel test to fighter flight condition;the CFD/CSD coupling calculation method based on the RANS/LES hybrid algorithm;active control technique on V-tail buffet response alleviation based on macro fiber composite piezoelectric actuators and Positive Acceleration Feedback(PAF);the V-tail buffet fatigue spectrum generation method and test program.This research has established a set of systematical theoretical analysis techniques,design criteria,and test methods for aircraft V-tail structure buffet dynamic strength design and test of advanced fighters and UAVs.

关 键 词：抖振 抖振谱 动态疲劳 风洞试验 脱体涡 压电纤维片 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程] V215