本文概述最初阶段利用风洞试验数据应用模糊逻辑研究飞机大攻角空气动力学的情况。
In this paper, the initial stage in application of fuzzy logic to aircraft high-Angle-of attack aerodynamics using wind tunnel test data is outlined.
以某歼击飞机前起落架为例，用落震试验的方法，通过分析起落架有关参数随机轮转速变化的情况，来研究飞机着陆瞬间起落架的状况。
The status of an undercarriage at the touchdown instant is studied by analyzing the undercarriage parameters which change with the wheel rotational speed in the drop test.
研究了飞机飞行试验数据处理中的非线性鲁棒滤波技术。
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