Fast Parametric Modeling Method And Layout Optimization Design Of Wing Structure

The aircraft wing is the main component which determines the overall performance of the aircraft. The aircraft wing structure which was fixed during the stage of the preliminary structural design of the wing sets almost80%of the performance of the entire wing. The type selection in the stage of the preliminary structural design is usually determined by the constant revision and evaluation, which requires a large number of repeated modeling. Therefore, it is needed to study rapid and efficient modeling methods. On the other hand, for the high-quality structure, the advanced design methods and the structure design based on the advanced methods is becoming an important research topic. The purpose of this article is to develop rapid modeling methods for wing structural analysis to solve the problems of a large number of repeated modeling in the type selection design and the research on the design optimization methods and the design of the structural configurations with high performances. Specific content and results are as follows:1. The research and realization on rapid parametric modeling method of the aircraft wing structures. As per the characteristic of the wing structure, a parameterization-based rapid finite element modeling method is proposed. With Patran and Nastran platform, an automatic modeling of wing structure drived by parameter using PCL language is realized and an exclusive program module for rapid parametric modeling of the wing structure is programmed. Three key technologies used include:1) establishment of a new parametric modeling process;2) direct generation of the three-dimensional finite element model of the wing structure from the finite element of projection plane of the wing;3) Realization of the automatic distribution of the aerodynamic load. These technologies lay the foundation for the wing structure optimization design.2. Gradient-based optimization method for layout design of wing structures. As per the characteristic of the load-bearing components of wings, a unified parameter description on the main beams, walles, ribes, and stringers is established by the variable correlation technology, then ground structure method described the layout of the components, a multiple-component structural layout optimization model is formulated as maximizing structural stiffness under the structural weight limitation and deduced the relative sensitivity analysis formula, Specific example shows the effectiveness of the method and solution efficiency. Discussed the effect to optimal layout about the ground structure, optimization parameters, and offered reasonable optimization parameter settings suggestion; Studied the impact to the layout of the internal load-bearing components by the skinning thickness, illustrate the necessity for skin thickness and component layout collaborative optimization Design; Through specific example, the result of skin thickness and component layout collaborative optimization design, compared to only consider the component layout optimization design, improve8.76%in bending stiffness.3. The multi-material selection optimization design of the load-bearing components of wings. To achieve the goals of structural weight-reduction and cost saving, the main load-bearing components such as beams, are often assembled with components comprised of different materials along the longitudinal direction. Thus, it is very necessary to consider the multi-material selection design in the structural design process. Based on this background, a multi-material selection optimization design model is proposed with manufacturing cost as constraint, structural stiffness as target, and the sensitivity formula is derived, Several examples show that the method has good convergence and solution efficiency.