In this thesis, the control law based on adaptive filter for Smart Rotor with actively controlled trailing edge flap is researched.
本文主要研究基于自适应滤波的主动控制后缘附翼智能旋翼控制律设计问题。
The aeroelastic analysis of a helicopter rotor blade with the controlled oscillating trailing edge flap is presented by building an aeroelastic model of the new concept rotor blade.
通过建立带受控振荡附翼的新概念旋翼气动弹性分析模型，研究了采用受控振荡附翼的直升机旋翼气动弹性特性及其在降低旋翼振动载荷方面的有效性。
A section of (wing trailing-edge) flap detached during flight probably due to material fatigue.
一段襟翼在飞行中掉落可能因材料疲乏。
The study shows that: Mini-TED changes the curvature of trailing edge and increases effective aerodynamic chord length for high lift system, is an additional 'aerodynamic flap'.
研究表明：微型后缘装置明显改变了襟翼后缘弯度，对襟翼流动产生有利诱导作用，拓展加长了增升装置的有效“气动弦长”，是一种附加“气动襟翼”。
The study shows that: Mini-TED changes the curvature of trailing edge and increases effective aerodynamic chord length for high lift system, is an additional 'aerodynamic flap'.
研究表明：微型后缘装置明显改变了襟翼后缘弯度，对襟翼流动产生有利诱导作用，拓展加长了增升装置的有效“气动弦长”，是一种附加“气动襟翼”。
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