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飞机颤振模型的结构设计是一个以固有频率为目标且具结构相似要求的反求问题。为了实现设计兼具结构和弹性特征相似的机身比例模型的目的,提出基于拓扑优化技术的机身颤振模型结构设计方法。该方法采用含规则几何形状的有限元集合描述机身骨架的结构特点,引入独立于有限单元网格的“节”作为结构修改的基本单位,构建与原机结构相似的格栅骨架加蒙皮有限单元模型,并将拓扑优化中的相邻敏度分配法与双向渐进结构法相结合,实现了以频率为目标、以体积为约束的拓扑优化。经过某圆筒机身的颤振模型优化算例证明,该方法有效地保证了优化后模型与原模型的结构相似性,并且达到了给定的固有频率,为飞机颤振模型设计提供了有益的借鉴方法。
The structural design of aircraft flutter model is an inverse problem with natural frequency as the target and similar structural requirements. In order to achieve the goal of designing a fuselage ratio model with similar structural and elastic characteristics, a structural design method of the flutter model based on topology optimization is proposed. The method uses the finite element set with regular geometric shape to describe the structural characteristics of the fuselage skeleton and introduces a “unit” independent of the finite element grid as the basic unit of structural modification to construct a grid skeleton with a similar structure to the original structure The finite element model of skin is combined with the method of adjacent sensitivity distribution in topology optimization and two-way progressive structure method to realize the topology optimization with the frequency as the target and the volume as the constraint. The flutter model optimization example of a cylinder fuselage shows that this method effectively guarantees the structural similarity between the optimized model and the original model and achieves the given natural frequency, which is beneficial to the design of aircraft flutter model The reference method.