绳系并联支撑飞机模型绕速度矢量旋转运动设计与模拟  

Design and simulation of rotation around velocity vector of aircraft model with wire-driven parallel suspension system

作　　者：王家骏 王晓光 沈楚伦 林麒 WANG Jiajun;WANG Xiaoguang;SHEN Chulun;LIN Qi(School of Aerospace Engineering,Xiamen University,Xiamen 361102,China;National Key Laboratory of Science and Technology on Aerodynamic Design and Research,Xi’an 710072,China)

机构地区：[1]厦门大学航空航天学院,厦门361102 [2]翼型、叶栅空气动力学重点实验室,西安710072

出　　处：《航空学报》2023年第17期147-158,共12页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(12172315,12072304,11702232);翼型、叶栅空气动力学重点实验室基金(61422010103);福建省自然科学基金(2021J01050)。

摘　　要：绕速度矢量旋转运动风洞试验是研究战斗机尾旋和大迎角复杂机动特性的一种重要手段,其中模型支撑是关键。创新性地设计了基于六自由度绳系并联支撑的旋转运动方式。提出定旋转角速度和定气流角2种旋转运动设计方法,推导得到旋转运动参数与模型位姿之间的关系式,并给出两者的关联;结合支撑系统动力学模型,设计绳长为控制变量的计算力矩控制律。通过ADMAS软件仿真和原理样机试验验证,结果表明所提设计方法可以实现飞机模型绕速度矢量变气流角定速率、定气流角变速率等复杂变参数旋转运动,且定气流角方法既能满足三自由度定耦合比关系,还能准确地模拟战斗机正飞/倒飞尾旋运动,这将为深入研究尾旋和大迎角机动特性提供技术支持。The wind tunnel tests of rotation around the velocity vector are important in the study on fighter spin and maneuver characteristics at high angle of attack,in which the model suspension is a key issue.This paper innova⁃tively designs rotational methods based on the 6-DOF(degree of freedom)wire-driven parallel suspension mecha⁃nism.Firstly,two different methods with constant rotational velocity and constant airflow angles are proposed,and the relationships between the rotational parameters and the model attitude angles are derived.The correlation of the two methods is also expounded.Then,a computed torque control law with the wire length as the control variable is de⁃signed based on the dynamic equations of WDPSS.Finally,the proposed design methods are both verified through the ADAMS software simulations and the principle prototype experiments.The results show that the proposed meth⁃ods allow for the fighter model to achieve complex variable-parameter rotation with variable airflow angles/constant an⁃gular velocity or constant airflow angles/variable angular velocity.Furthermore,the method of constant airflow angles can meet the 3-DOF fixed-coupling-ratio relationship,and accurately simulate the erected/inverted spin of the fighter,providing technical support for the in-depth study on spin and maneuvering characteristics at high angle of attack.

关 键 词：风洞试验 绳系并联支撑 速度矢量 尾旋 大迎角 耦合比 

分 类 号：V216[航空宇航科学与技术—航空宇航推进理论与工程]