风洞虚拟飞行模型机与原型机动力学特性分析

doi:10.7527/S1000-6893.2015.0296

实验研究

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风洞虚拟飞行模型机与原型机动力学特性分析

郭林亮¹, 祝明红², 孔鹏², 聂博文², 钟诚文¹

1. 西北工业大学航空学院, 西安 710072;
2. 中国空气动力研究与发展中心, 绵阳 621000

收稿日期:2015-09-24 修回日期:2015-11-02 出版日期:2016-08-15 发布日期:2015-11-24
通讯作者: 祝明红,Tel.:0816-2461016。E-mail:1400504410@qq.com E-mail:1400504410@qq.com
作者简介:郭林亮,男,博士研究生,助理研究员。主要研究方向:实验空气动力学,飞行动力学与控制。Tel:0816-2464702。E-mail:guolinliangliang@163.com;祝明红,男,研究员。主要研究方向:大迎角空气动力学和尾旋。Tel:0816-2461016。E-mail:1400504410@qq.com;孔鹏,男,助理研究员。主要研究方向:机械设计和机电一体化。E-mail:kp00139@sohu.com;聂博文,男,助理研究员。主要研究方向:测控技术。E-mail:xuanwen1981@163.com;钟诚文,男,博士,教授,博士生导师。主要研究方向:计算流体力学。Tel:029-88460412。E-mail:zhongcw@nwpu.edu.cn
基金资助:
国家“973”计划（2015CB755800）

Analysis of dynamic characteristics between prototype aircraft and scaled-model of virtual flight test in wind tunnel

GUO Linliang¹, ZHU Minghong², KONG Peng², NIE Bowen², ZHONG Chengwen¹

1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2015-09-24 Revised:2015-11-02 Online:2016-08-15 Published:2015-11-24
Supported by:
National Basic Research Program of China (2015CB755800)

摘要/Abstract

摘要：

在低速风洞虚拟飞行试验系统中，采用三自由度（3-DOF）球铰支撑动力学相似缩比飞机模型，在气动力矩作用下试验模型可绕质心自由转动。这种带约束的运动与具有六自由度（6-DOF）的真实大气飞行存在差别，鉴于此，对各影响因素逐个剖离并进行了数值模拟和对比分析。结果表明：位移约束使两者间的动力学特性产生较明显的差异，缩比的影响符合相似准则规律，机构摩擦、模型重心与支撑点不重合影响较小，常值干扰力矩对模型的初始响应有一定影响。对比分析结果可以用于指导风洞虚拟飞行试验的开展，并有助于完善风洞虚拟飞行试验技术及其拓展应用。

关键词: 风洞虚拟飞行试验, 动力学特性, 飞行力学, 仿真, 动态试验, 三自由度球铰

Abstract:

This paper presents a virtual flight testing system in low speed wind tunnel, which has a 3-degree-of-freedom (3-DOF) gimbal mechanism to connect a dynamically-scaled wind tunnel model supported by a vertical strut. The model can freely rotate around the center of gravity due to the aerodynamic moments. Obviously the constrained motion is different from the real 6-DOF free flight in the air. So the influencing factors which contribute to the dynamic characteristics' differences between the prototype aircraft and scaled-model are individually compared and investigated through flight dynamics simulation. The results demonstrate that the constrained translational movement has a significant impact on the dynamic characteristics while the dynamic response of the scaled-model and full-scale aircraft meets the similarity law; both the 3-DOF bearing friction and the non-coincidence between center of gravity and center of gimbal has small influence; the constant moment disturbance has some impact on the initial response. The comparison and analysis can provide a guide for the virtual flight test in wind tunnel, and are also helpful for the improvement and application of the wind tunnel testing technique.

Key words: wind tunnel-based virtual flight testing, dynamic characteristics, flight dynamics, simulation, dynamic test, 3-degree-of-freedom gimbal

中图分类号:

郭林亮, 祝明红, 孔鹏, 聂博文, 钟诚文. 风洞虚拟飞行模型机与原型机动力学特性分析[J]. 航空学报, 2016, 37(8): 2583-2593.

GUO Linliang, ZHU Minghong, KONG Peng, NIE Bowen, ZHONG Chengwen. Analysis of dynamic characteristics between prototype aircraft and scaled-model of virtual flight test in wind tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(8): 2583-2593.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

风洞虚拟飞行模型机与原型机动力学特性分析

Analysis of dynamic characteristics between prototype aircraft and scaled-model of virtual flight test in wind tunnel

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