Configuration design and topology optimization of a single wing for the hybrid unmanned aerial vehicle
ZHANG Qingsong1,2,3, JIA Shan1,2,3, CHEN Jinbao1,2,3, XU Yingshan4, SHE Zhiyong4, CAI Chengzhi1,2,3, PAN Yihua1
1. College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China; 2. Key Laboratory of Aerospace Science and Technology for Aerospace Entry Deceleration and Landing Technology, Nanjing 211106, China; 3. Key Laboratory of Deep Space Planetary Surface Exploration Agency, Ministry of Industry and Information Technology, Nanjing 211106, China; 4. Beijing Aerospace Technology Research Institute, Beijing 100000, China
Abstract：[Objective] The hybrid unmanned aerial vehicle (UAV) has become an important technical means in the UAV field because of its excellent lift-drag characteristics and endurance. The endurance of an UAV can be improved mainly by obtaining good lift and drag characteristics and reducing its weight. Using a modular UAV as the research object, this paper established a hybrid UAV configuration concept, mainly considering the stress change rule and the maximum fatigue life of the monomer UAV under aerodynamic force, and its lightweight design goals under the fatigue life and the maximum stress constraint. This paper conducted research on lightweight design mainly in three ways:1) According to the hybrid UAV concept, an overall configuration of "main body + monomer" is proposed and the full-text research object is provided. The monomer UAV is an important task-combined UAV unit, so the mechanical properties of every single part and the overall topology structure are emphasized. 2) In the incompressible unsteady three-dimensional continuous equation and Navier-Stokes (N-S) equation, momentum analysis is carried out on the aerodynamic characteristics of a single wing UAV in a full working environment, the regional flight parameters are clarified, and the maximum aerodynamic force is selected as the ultimate load, in the form of loading a sine function into the single wing. The monomer stress distribution of the maximum stress region of the wing-body is extracted. Combined with Fe-safe numerical analysis software, fatigue life analysis is performed, and improvements are proposed for sensitive areas. Based on the service life guarantee and the solid isotropic microstructure with the penalization (SIMP) method, a topological optimization analysis of a single wing, load-bearing frame is performed. 3) A monomer wing finite element model is established to verify the correctness of the topology optimization model. For a single wing, all the structural analyses of the static and dynamic analysis results verify the correctness of the above theoretical analysis. At the same time, in the topology analysis link, because each tolerance beam differs in weight, analysis was performed for each beam. In this paper, based on the classic SIMP topology optimization method, the topological calculation and analysis of the single wing's front beam, middle beam, rear beam, and middle rib show that the weight of each beam is reduced by 5%, 10%, 5%, and 15%, respectively, under the premise of invariable mechanical distribution. After obtaining the analysis results, the weight of the entire wing is reduced by 35%. an innovative topology optimization process is adopted to analyze the fatigue life of key parts before the wing is joined, ensuring the process optimization of the wing and the service life of key parts. The proposed method integrates key position optimization, topology optimization, and fatigue life analysis, avoiding separate post-assembly fatigue analysis of key positions, optimizing the whole analysis process, and improving the work efficiency of lightweight analysis. The wing topology optimization method under the fatigue life constraint proposed in this paper reduces the weight of a single UAV by 35% under the condition of constant force and improves the efficiency of wing lightweight analysis. The new analysis method provides technical support for subsequent UAV optimization analysis.
张青松, 贾山, 陈金宝, 徐颖珊, 佘智勇, 蔡成志, 潘一华. 组合体无人机单体机翼构型设计与拓扑优化[J]. 清华大学学报（自然科学版）, 2023, 63(3): 423-432.
ZHANG Qingsong, JIA Shan, CHEN Jinbao, XU Yingshan, SHE Zhiyong, CAI Chengzhi, PAN Yihua. Configuration design and topology optimization of a single wing for the hybrid unmanned aerial vehicle. Journal of Tsinghua University(Science and Technology), 2023, 63(3): 423-432.
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2023, Vol. 63 
