风洞虚拟飞行试验模型绳系并联支撑机构

吴惠松; 林麒; 柳汀; 刘震; 师璐; 王晓光

doi:10.7527/S1000-6893.2021.25758

航空学报 >

2022 , Vol. 43 >Issue 8: 125758 - 125758

DOI: https://doi.org/10.7527/S1000-6893.2021.25758

流体力学与飞行力学

风洞虚拟飞行试验模型绳系并联支撑机构

吴惠松 ,
林麒 ,
柳汀 ,
刘震 ,
师璐 ,
王晓光

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厦门大学航空航天学院, 厦门 361102

收稿日期: 2021-05-06

修回日期: 2021-07-22

网络出版日期: 2021-07-20

基金资助

国家自然科学基金(12072304,11472234,11702232);中央高校基本科研业务费专项资金(20720180071)

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Wire-driven parallel suspension mechanism of virtual flight test model in wind tunnel

WU Huisong ,
LIN Qi ,
LIU Ting ,
LIU Zhen ,
SHI Lu ,
WANG Xiaoguang

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School of Aerospace Engineering, Xiamen University, Xiamen 361102, China

Received date: 2021-05-06

Revised date: 2021-07-22

Online published: 2021-07-20

Supported by

National Natural Science Foundation of China (12072304,11472234,11702232);Fundamental Research Funds for the Central Universities (20720180071)

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摘要

提出了一种三自由度风洞虚拟飞行试验模型的绳系并联支撑机构,采用上下各两根绳索牵引飞行器模型,并配合偏航转台模拟飞行器模型的三轴姿态变化,实现3个转动自由度的自由耦合和解耦运动。首先通过螺旋理论的构型设计和自由度分析方法完成该风洞虚拟飞行试验模型支撑机构总体设计;接着通过对支撑平台的结构优化,使得机构运动过程中模型质心与机构转动中心重合,以保证支撑系统的稳定性;最后对该欠约束、可重构、被动驱动的虚拟飞行试验模型绳系并联支撑机构进行运动学和动力学建模,并通过动力学仿真和初步风洞试验,验证了该绳系支撑机构能够满足风洞虚拟飞行试验支撑系统的要求。为发展新型风洞虚拟飞行试验模型提供了新思路,也为飞行器模型的气动力耦合机理和气动参数辨识等风洞试验奠定了基础。

关键词： 螺旋理论; 虚拟飞行; 绳系并联支撑; 动力学建模; 风洞

本文引用格式

吴惠松 , 林麒 , 柳汀 , 刘震 , 师璐 , 王晓光 . 风洞虚拟飞行试验模型绳系并联支撑机构[J]. 航空学报, 2022 , 43(8) : 125758 -125758 . DOI: 10.7527/S1000-6893.2021.25758

Abstract

This paper proposes a three Degree-of-Freedom(DOF) mechanism with wire-driven parallel suspension of virtual flight test models in the wind tunnel. The upper and lower wires are used to suspend the aircraft model and incorporate a yaw turntable to simulate its three-axis attitude change to realize the free coupling and decoupling motions of three DOFs of rotation. The overall design of the suspension mechanism of the wind tunnel virtual flight test model is first conducted through the configuration design and the degrees of freedom analysis method of the screw theory. The structure of the supporting platform is then optimized to make the center of mass of the model coincide with the center of rotation of the mechanism during the movement of the mechanism to ensure the stability of the support system; Finally, the kinematics and dynamics model of the virtual flight test model with the unconstrained, reconfigurable and passive drive is established. The dynamic simulation and preliminary wind tunnel test verify the ability of the wire-driven parallel support mechanism to meet the requirements of the wind tunnel virtual flight test support system. This study provides a new idea for the development of new wind tunnel virtual flight test model support, meanwhile laying a foundation for the wind tunnel test research of the aerodynamic coupling mechanism and aerodynamic parameter identification of aircraft models.

Key words： screw theory; virtual flight; wire-driven parallel suspension; dynamics modeling; wind tunnel

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