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首页> 外文期刊>Aerospace science and technology >Passive gust alleviation of a flying-wing aircraft by analysis and wind-tunnel test of a scaled model in dynamic similarity
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Passive gust alleviation of a flying-wing aircraft by analysis and wind-tunnel test of a scaled model in dynamic similarity

机译：通过动态相似性缩放模型的分析和风隧道测试通过分析和风隧道试验的被动阵风

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An investigation was conducted to evaluate the effectiveness of a passive gust alleviation device (PGAD) installed in a flying-wing aircraft of 62.3 m wing span at large swept back angle. It was performed by numerical analysis and validated by wind-tunnel test of a 1:25 reduced scale physical model of dynamic similarity to the full-scale aircraft. The 1-cosine gust model with a range of gust parameters specified in the airworthiness regulation CS-23 was taken in the gust response analysis that led to 7 similar to 9% gust alleviation results by employing the PGAD. The gust response dominated by the first three modes of the aircraft was most critical in the frequency close to the first bending mode of the wing. The wind-tunnel test model was designed and manufactured based on dynamic scaling law, and proved to be of excellent dynamic similarity by the deviation of less than 5.5% between the first three modes of the physical model measured by vibration test and the full-scale aircraft model. The wind tunnel test results show that the gust response of the model in the specified range was reduced by 8.3 similar to 14.3% according to the measured wing tip deflection associated with the PGAD oscillation amplitude at 4.0 degrees similar to 15.5 degrees. The present study shows that the numerical analysis of gust response and alleviation of a full-scale aircraft installed with PGAD can be validated by wind tunnel test of a scaled physical model with dynamic similarity. (C) 2021 Elsevier Masson SAS. All rights reserved.
机译：进行了调查以评估安装在62.3 M翼跨度的飞行飞机中的被动阵风缓解装置（PGAD）的有效性。它是通过数值分析进行的，并通过风隧道试验验证1:25的动态相似度的减小物理模型与全尺寸飞机。在适航调节CS-23中指定的具有一系列阵风参数的1-余弦阵风模型在阵风响应分析中采用，通过使用PGAD导致了与9％阵风的阵风。由飞机的前三种模式主导的阵风响应在接近机翼的第一弯曲模式的频率中最关键。根据动态缩放法设计和制造风洞试验模型，并经证明在振动试验和全规模测量的物理模型的前三种模式之间的偏差小于5.5％的偏差优异的动态相似性飞机模型。风洞测试结果表明，根据与PGAD振荡幅度相关的测量的翼尖偏转，模型在指定范围内的阵风响应减少了8.3，其与类似于15.5度的4.0度的PGAD振荡幅度相关。本研究表明，通过具有动态相似性的缩放物理模型的缩放物理模型的风洞测试，可以通过动态相似性的缩放物理模型的风隧道试验来验证阵风响应和缓解全尺度飞机的数值分析。 （c）2021 Elsevier Masson SAS。版权所有。

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