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

作　　者：郭林亮[1] 祝明红[2] 孔鹏[2] 聂博文[2] 钟诚文[1] 

机构地区：[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

出　　处：《航空学报》2016年第8期2583-2593,共11页Acta Aeronautica et Astronautica Sinica

基　　金：国家"973"计划(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。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.

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 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程] V211.7