中图分类号：TJ760.3 文献标志码：A

Topology optimization design method of metal powder particle damping composite rudder structure

LI Haidong1，SHI Xiaoming1，ZHANG Heng² （1.Shanghai Electro-Mechanical Engineering Institute，Shanghai2Ol1O9，China; 2.SchoolofMechanicalEngineering， University of Shanghai for Science and Technology， Shanghai 2Ooo93， China）

Abstract： The mechanical characteristics of the rudder structure have a critical impact on the flight performance of the aircraft， and these characteristics are governed by the structure’ s geometric configuration. A topology optimization method for designing the metal powder particle damping composite rudder structure was proposed. The load-bearing function was satisfied by optimizing the stiffners of the rudder structure and the vibration suppression was achieved by optimizing the position distribution of the powder particle dampers. The internal stiffener distribution of the rudder structure was determined via the adaptive growth method， while the equivalent performance of the powder particle damper was evaluated using the homogenization method. Based on the homogenized parameters， the position distribution of the powder particle dampers within the rudder was optimized to realize a collaborative design that concurrently addressed both load-bearing and vibration suppression functions. The simulation results show that， compared to the original rudder structure， the static mechanical performance of the optimized metal powder particle damping composite rudder structure is improved by 10.35% ， the first natural frequency is increased by 22.10% ， the frequency response at the first natural frequency is reduced by 22.88% ， and the flutter speed is increased by more than 10% when the Mach number is 4， 5， 6. The proposed design method provides a new solution for the design of lightweight， high-rigidity structures with vibration suppression functions.

Keywords： topology optimization; stiffener distribution design; powder particle damper; rudder structure

舵面结构是飞行器飞行过程中实现高速飞行和机动控制的核心部件之一，不仅要求其重量轻，还要求其具有较好的承载能力和抗振性能[1]。目前的舵面结构多采用蒙皮-骨架结构形式，蒙皮与骨架通过铆钉、螺钉或钎焊连接在一起，骨架一般是辐射梁式或网格式等相对规则的经验设计构型[2]。然而，在日益严苛的飞行载荷作用下，这种经验设计的结构构型无法满足高速飞行器的高刚度设计要求。与此同时，如何有效提升飞行器的颤振边界也成为亟待攻克的技术难题[3]

轻量化设计方面，近年来，随着结构拓扑优化理论的不断发展，国内外学者积极开展该理论在飞行器领域的研究与应用，在飞行器结构设计制造一体化方面取得了众多具有代表性的研究成果，推动了飞行器领域相关技术的飞速发展。王昕江等[4提出了一种基于拓扑优化的舵面结构轻量化设计方法，并验证了静气动弹性变形与强度。朱继宏研究团队[5将舵面作为独立部件，采用拓扑优化获取主传力路径，提取结构特征，通过尺寸参数优化对重构模型进行详细设计，实现结构减重。丁晓红研究团队[7-9]结合仿生优化思想，通过研究自然界分支系统的形成机理，提出了一种结构加筋分布优化设计自适应成长法，并应用于高速飞行器舵面结构设计中，得到树状分布的骨架宏观构型，在实现1阶固有频率提升的同时，达到轻量化设计的目的[10]。……