北京航空航天大学,北京,100191
纸质出版:2025
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王惠添, 马超, 殷莎. 装配式点阵材料的结构设计与多场景验证[J]. 航空制造技术, 2025,(22).
WANG Huitian, MA Chao, YIN Sha. Structural Design and Multi-Scenario Validation of Assembled Lattice Material[J]. Aeronautical Manufacturing Technology, 2025, (22).
王惠添, 马超, 殷莎. 装配式点阵材料的结构设计与多场景验证[J]. 航空制造技术, 2025,(22). DOI: 10.16080/j.issn1671-833x.2025.22.078.
WANG Huitian, MA Chao, YIN Sha. Structural Design and Multi-Scenario Validation of Assembled Lattice Material[J]. Aeronautical Manufacturing Technology, 2025, (22). DOI: 10.16080/j.issn1671-833x.2025.22.078.
点阵材料是一类微结构可人为设计的工程材料,具有优异的力学、声学、热学等多物理场调控能力,在智能结构领域展现出广阔的应用前景。尽管增材制造技术的发展显著提升了点阵材料的形状复杂度,但该技术在构建尺寸和制造效率上仍存在限制,不仅阻碍了大尺度复杂结构的一体化成型,更成为其工程化应用的关键技术瓶颈。为此,本文提出了一种基于标准单胞的装配式构造方法,通过模块化构建与空间拼接,实现复杂结构中大尺寸点阵材料的构型自由与制造可行性。在结构构型方面,采用八面体点阵单胞作为基本构件,并针对柔性与刚性材料体系分别设计了螺栓连接与仿生插接两种连接策略,实现了面向不同应用需求的模块化装配;柔性结构中集成线性驱动器,构建主动变形的机翼结构,实现了最大厚度调节范围为25 mm,最大表面倾角达12° 的局部变形控制;刚性结构中构建点阵夹芯驾驶舱原型,建立均质化有限元模型进行静力学分析,获得的弯曲刚度为2564.1 N/mm,扭转刚度为1409 N·m/deg。研究结果表明,该装配式点阵结构体系在保持轻质高性能的同时具备良好的装配灵活性与跨尺度适应能力,可为智能结构与飞行器轻量化部件的工程化落地提供有效的构型与制造方案。
Lattice materials are a class of engineered materials with artificially designable microstructures
with excellent multi-physics field manipulation capabilities in mechanics
acoustics
and thermodynamics
and exhibit broad application prospects in the field of smart structures. Although the development of additive manufacturing technology has significantly enhanced the shape complexity of lattice materials
its limitations in build size and manufacturing efficiency still impede the integrated fabrication of large-scale complex structures
which has become a key technical bottleneck for their engineering application. To address this
this paper proposes a prefabricated assembly construction method using standard unit cells
which enables configuration flexibility and manufacturing feasibility for large-scale lattice materials in complex structures via modular construction and spatial assembly. In terms of structural configuration
octahedral lattice unit cells serve as the basic components
with two connection strategies developed: Bolt joints for flexible material systems and bionic plug-in joints for rigid ones
enabling modular assembly for diverse application requirements. For flexible structures
linear actuators are integrated to construct an actively deformable wing structure
which achieves local deformation control with a maximum thickness adjustment range of 25 mm and a maximum surface inclination angle of 12°. For rigid structures
a lattice sandwich cockpit prototype is constructed
and a homogenized finite element model is established for static mechanical analysis
resulting in a bending stiffness of 2564.1 N/mm and a torsional stiffness of 1409 N·m/deg. The research results indicate that this assembled lattice structural system
while maintaining lightweight properties and high performance
possesses good assembly flexibility and cross-scale adaptability
thereby offering an effective configuration and manufacturing solution for the engineering application of smart structures and lightweight aircraft components.
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