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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >INVESTIGATION OF FIN BUFFET CHARACTERISTICS OF A DEVELOPMENTAL COMBAT AIRCRAFT THROUGH WIND TUNNEL EXPERIMENTS
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INVESTIGATION OF FIN BUFFET CHARACTERISTICS OF A DEVELOPMENTAL COMBAT AIRCRAFT THROUGH WIND TUNNEL EXPERIMENTS

机译：通过风洞实验研究战斗战斗机的鳍自助特性

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摘要

Airframe buffet is an important dynamic problem associated with combat aircraft flight, especially in the high Angle-of-Attack (AoA) regime. Occurrence of buffet due to flow separation at high angles of attack needs to be structurally cleared and a buffet boundary needs to be established. The methodology adopted to clear the aircraft from buffet during high AoA flight testing of a developmental light combat aircraft is focused in this article. Experimental unsteady pressure data from low speed wind tunnel tests conducted on a scaled down (1:10) model and airframe especially fin vibration data measured from flight tests formed the basis for this methodology. The reference spectrum has been formulated through unsteady pressures measured using pressure transducers mounted on the fin of the wind tunnel model. This spectrum (scaled up to 1:1) i.e. pressure Power Spectral Density (PSD) excitation was used as an input to the FE model of aircraft fin mounted on the rearfuselage. Buffeting response predicted in terms of acceleration PSD on the fin and rudder have been compared with the flight measured acceleration PSD data to validate the numerical model. The validated model is used to predict loads to clear the aircraft for further flight envelope expansion at high AoA.
机译：机身自助餐是与战斗机飞行相关的重要动态问题，尤其是在高攻角（AoA）体制下。需要在结构上清除由于在大迎角处的流动分离而引起的自助餐的发生，并且需要建立自助餐边界。本文重点介绍了在发展型轻型战斗机的高AoA飞行测试中从自助餐中清除飞机的方法。在按比例缩小（1:10）模型进行的低速风洞测试中获得的实验性非稳态压力数据以及机身，尤其是从飞行测试中测得的鳍片振动数据，构成了该方法的基础。参考光谱是通过使用安装在风洞模型翅片上的压力传感器测得的非稳态压力来制定的。该频谱（放大到1：1），即压力功率谱密度（PSD）激励用作安装在后机身上的飞机鳍有限元模型的输入。将鳍和舵上的加速度PSD预测的抖振响应与飞行测量的加速度PSD数据进行比较，以验证数值模型。经过验证的模型可用于预测载荷以清除飞机，以便在高AoA时进一步扩大飞行范围。

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