考虑复合材料蒙皮稳定性的飞机翼面结构布局优化设计

Layout Optimization Design of Wing Structures with Consideration of Stability of Composite Skin

复合材料蒙皮稳定性是飞机翼面结构设计需要考虑的重要方面。由于翼面结构稳定性理论分析的复杂性,工程中,通常采用与理论分析相比拟的简化方法、使用简便可靠的经验公式在设计过程中进行稳定性校核。多墙式结构是当前翼面结构中普遍采用的结构形式,墙的布局和蒙皮的厚度对复合材料蒙皮的临界屈曲载荷有着重要影响。因此,针对多墙式翼面结构,以工程经验公式为基础,以蒙皮单位长度上的的重量为优化目标,以墙的布局参数和蒙皮厚度为设计变量,以临界失稳载荷为约束,建立了一种考虑复合材料蒙皮稳定性的翼面结构布局优化问题的数学模型,导出了目标函数敏度计算的解析式,并提出了优化问题的求解方法。以翼盒结构为例,验证了该方法的有效性。

Ensuring the stability of the composite skin is of great significance in the design of aircraft wing structures.Theoretically,it is very difficult to solve the stability of wing structures.Therefore,a simple and reliable empirical formula,which is a simplified method by analogizing with the theoretical analysis,is adopted in engineering design.At present,the multi-spar structure is widely used in aircraft wing structures.When a multi-spar structure is designed,the focus is to reduce the structural weight through the optimal arrangement of the load-carrying components within the wing-box structures and the minimal thickness of the skin under a specified air-loading condition.The layout of the wing spars and the thickness of the skin have great effect on the stability of the composite skin.Therefore,a mathematical model on the layout optimization of wing structures is developed with the constraint of the stability of the composite skin.To solve this optimization problem,the stability of the composite skin is solved based on the empirical formula,and a sensitivity formula is also established.Finally,a wing box structure is taken as an example,and the optimal results prove that the method presented in this article is very effective in aircraft wing design.