基于CFDCSD与Kriging插值模型的大展弦比复合材料机翼静气动弹性优化设计.docx

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Title: Static Aeroelastic Optimization Design of High Aspect Ratio Composite Wing Using CFDCSD and Kriging Interpolation Model
Introduction:
Composite materials have gained immense popularity in the aviation industry due to their superior strength-to-weight ratio, excellent corrosion resistance, and design flexibility. The static aeroelastic behavior of a composite wing, particularly for high aspect ratio wings, plays a significant role in determining its structural integrity and performance. This paper focuses on the optimization design of a high aspect ratio composite wing using the Coupled Fluid–Discrete Crack Surface Displacement (CFDCSD) method combined with Kriging interpolation.
Literature Review:
The static aeroelastic behavior of composite wings has been studied extensively in the past. Various optimization techniques, such as genetic algorithms, particle swarm optimization, and neural networks, have been applied to improve the wing's performance. Additionally, the CFDCSD method has gained attention for its ability to accurately predict the crack propagation behavior in composite materials. The use of Kriging interpolation, a metamodeling technique, allows for efficient approximation of the aerodynamic and structural responses, reducing the computational cost associated with traditional optimization methods.
Methodology:
1. Wing Geometry Modeling:
- The high aspect ratio composite wing geometry will be designed using computer-aided design (CAD) software. The wing parameters, such as span, chord length, sweep, and thickness distribution, will be specified as design variables.
2. Fluid-Structure Interaction Analysis:
- The CFDCSD method will be used to model the fluid-structure interaction of the composite wing. This method considers the aerodynamic loads acting on the wing and predicts the structural response, including crack growth, deformations, and failure.
3. Kriging Metamodel Development:
- The aerodynamic and structural responses obtained from the CFDCSD analysis will be used to develop Kriging metamodels. These metamodels provide efficient approximations of the responses, allowing for faster optimization iterations.
4. Optimization Framework:
- The optimization algorithm will be developed, considering the design variables, constraints, and objectives. The objective function could be minimizing the wing weight while maintaining structural integrity, maximizing lift-to-drag ratio, or other performance metrics.
5. Performance Evaluation:
- The optimized wing designs will be evaluated using computational fluid dynamics (CFD) simulations to validate their aerodynamic performance. The structural integrity and aeroelastic stability will be assessed through static and dynamic simulations.
Conclusion:
This paper proposes a static aeroelastic optimization design approach for high aspect ratio composite wings using the CFDCSD method and Kriging metamodels. The CFDCSD method accurately predicts the crack propagation in composite materials, while the Kriging interpolation technique provides efficient approximations of the aerodynamic and structural responses. The optimized wing designs derived from this approach are expected to exhibit improved performance in terms of weight, aerodynamics, and structural integrity.