Abstract
A morphing wing concept allowing for coupled twist-camber shape adaptation is proposed. The design is based on an optimized thickness distribution both spanwise and chordwise to be able to morph the wing sections into targeted airfoil shapes. Simultaneously, the spanwise twist is affected by the actuation. The concept provides a higher degree of control on the lift distribution which can be used for roll control, drag minimization, and active load alleviation. Static deformation and flight tests have been performed to evaluate and quantify the performance of the proposed mechanism. The ground tests include mapped actuated wing shapes, and wing mass and actuation power requirements. Roll authority, load alleviation, and aerodynamic efficiency estimates for different configurations were calculated using a lifting line theory coupled with viscous 2D airfoil data. Roll authority was estimated to be low when compared to a general aviation aircraft while the load alleviation capability was found to be high. Differences between the lift to drag ratio between the reference and morphing wing configurations are considerable. Mass and actuation energy present challenges that can be mitigated. The flight tests were used to qualitatively assess the roll control capability of the prototype, which was found to be adequate.
Highlights
The idea of changing the geometry of the lifting surfaces to adapt them to the flight condition is not new
The challenges presented in shape adaptation remain unanswered due to the opposing requirements of flexibility and sufficient stiffness and load-bearing capability
A simplistic quantification of the potential maximum operational load increase stems directly from the Root Bending Moment (RBM) variation from configuration #1 to #5, which suggests that this load could increase from 16% up to 49%, depending on the current flight speed
Summary
The idea of changing the geometry of the lifting surfaces to adapt them to the flight condition is not new. Within the camber morphing research, aero-structural high-fidelity optimization of an adaptive trailing edge for transonic flight predicts decreased fuel burn by more than 5% [4]. Optimum deformations for a transonic airfoil with morphing leading and trailing edges were obtained using high-fidelity aero-structural modeling, showing significant aerodynamic performance improvement [5]. A prototype of a morphing wing with coupled camber-twist change capability and its testing is described. This novel concept contributes to the state-of-the-art as it explores multiple and coupled morphing concepts while exploring multiple functions for said concepts, improving the competitiveness of the morphing solution when compared to conventional ones.
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