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风洞虚拟飞行模型机与原型机动力学特性分析
引用本文: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. DOI: 10.7527/S1000-6893.2015.0296
作者姓名:郭林亮  祝明红  孔鹏  聂博文  钟诚文
作者单位: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
基金项目:国家“973”计划(2015CB755800)National Basic Research Program of China (2015CB755800)
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  
收稿时间:2015-09-24
修稿时间:2015-11-02

Analysis of dynamic characteristics between prototype aircraft and scaled-model of virtual flight test in wind tunnel
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 Aeronautica et Astronautica Sinica, 2016, 37(8): 2583-2593. DOI: 10.7527/S1000-6893.2015.0296
Authors:GUO Linliang  ZHU Minghong  KONG Peng  NIE Bowen  ZHONG Chengwen
Affiliation:1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;2. China Aerodynamics Research and Development Center, Mianyang 621000, China
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.
Keywords:wind tunnel-based virtual flight testing  dynamic characteristics  flight dynamics  simulation  dynamic test  3-degree-of-freedom gimbal
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