At present, most of the research on adaptive wing is the trailing edge deformation of the wing. Because the trailing edge of the wing bears relatively small load, it is easier to achieve deformation in structure, and can also improve fuel efficiency, produce better aerodynamic performance.
An analysis of known approaches in the design of an adaptive wing was carried out. To do it modern publications with high data features and well-known data bases were used.
In the design process a high fidelity aerostructural model that enables the detailed optimization of wing shape and sizing using hundreds of design variables is used. A number of multipoint aerostructural optimizations can be performed. Multipoint analysis provides a better opportunity to deform trailing edges to improve performance.
The approaches to analyze were geometric parametrization, mesh deformation, CFD solver, structural solver, coupled aerostructural solver, optimization algorithm, problem formulation.
We should use some overview of numerical methods to achieve the best acceptable performances. Geometric shape changes are parametrized using a Free Form Deformation (FFD) approach [1]. An inverse-distance-weighting warping algorithm usually used in design process. The warping scheme interpolates both displacements and rotations of the surface into the volume mesh. It can preserve mesh perpendicularity near surfaces. The aerodynamic solver within the MACH framework is ADflow [1]. The structural solver in the MACH framework is the Toolkit for Analysis of Composite Structures (TACS) [1]. The main role of the aerostructural solver is to couple the aerodynamic and structural solvers, ADflow and TACS. The optimizations are performed using SNOPT (Sparse Nonlinear OPTimizer), an optimization algorithm that uses a sequential quadratic programming (SQP) approach with a quasi-Newton approximation of the Hessian of the Lagrangian [1].
For the optimization method, morphing 3-point optimizations with varying lift coefficient and morphing 7-point optimizations with varying lift coefficient, Mach number, and altitude were considered [1]. Finally, comparison those results using a smaller morphing device and a configuration with a higher aspect ratio.
Needs to optimize the coupling of high-fidelity aerodynamic and structural models in a trade-off between structural weight and aerodynamic robustness is important in adaptive wing investigation. Adding adaptive deforming trailing edge device can reduce the weight of structure obviously morphing technology is more effective for higher aspect ratio wings.
Future more comprehensive studies should be carried out to optimize the deformation mechanism for more weight and flight conditions.
References:
1. David A.BurdetteJoaquim R.R.A.Martins (2018). Design of a transonic wing with an adaptive morphing trailing edge via aerostructural optimization. Aerospace Science and Technology, (81), 192-203. https://doi.org/10.1016/j.ast.2018.08.004.
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