泡沫填充可刚化机翼承力性能分析
发布时间：2018-07-14 18:17
【摘要】：无人机技术在现代军事等领域发挥着越来越大的作用,要想进一步提高无人机高空长航时的飞行能力,需要对无人机进行轻量化设计。本文以太阳能无人机机翼的轻量化设计为研究背景,对聚氨酯泡沫填充可刚化机翼的承力性能进行研究,分析机翼结构的抗弯性能。本文通过在显微镜下观察得到硬质聚氨酯泡沫材料内部孔洞的真实结构,建立研究此类闭孔泡沫材料的Kelvin等效模型,并给出研究该模型的等效力学性能;对聚氨酯泡沫材料进行拉伸、压缩及三点弯曲试验,得到该泡沫材料的应力-应变关系等力学性能。利用ANSYS有限元软件对泡沫填充梁进行基于理论弹性参数与实测参数的数值模拟,并与用全站仪测得的梁弯曲试验的结果进行对比,模拟值与试验值吻合较好;使用VIC-3D非接触全场应变测量仪测得泡沫填充梁的振动频率,并进行数值模拟,模拟与试验结果符合。根据实际需求对机翼结构进行设计,按照设计的NACA0016翼型制作机翼模型,对制作的机翼模型进行弯曲试验,并与用ANSYS进行数值模拟的结果对比,对比结果比较接近;使用ANSYS中的Fluent流体软件对所设计的二维翼型进行气动性能分析,得到在一定飞行速度和攻角时翼型面上的压力和速度分布,并分析了气动分布载荷下机翼的弯曲性能。
[Abstract]:Unmanned aerial vehicle (UAV) technology is playing an increasingly important role in modern military and other fields. In order to further improve the flight capability of UAV in high altitude and long voyage, it is necessary to carry out lightweight design of UAV. In this paper, based on the lightweight design of solar UAV wing, the bearing capacity of rigid wing filled with polyurethane foam is studied, and the bending performance of wing structure is analyzed. In this paper, the real structure of pores in rigid polyurethane foam is observed under microscope, and the Kelvin equivalent model for studying this kind of closed cell foam is established, and the equivalent mechanical properties of the model are given. The tensile, compression and three point bending tests of polyurethane foam were carried out, and the stress-strain relationship of the foam was obtained. The finite element software ANSYS is used to simulate the foam filled beam based on the theoretical elastic parameters and the measured parameters, and the results are compared with the results of the beam bending test measured by the total station instrument. The simulation results are in good agreement with the experimental values. The vibration frequency of foam filled beam was measured by VIC-3D non-contact full-field strain measuring instrument, and the numerical simulation was carried out. The simulation results are in good agreement with the experimental results. According to the actual demand, the wing structure is designed. According to the NACA0016 airfoil model, the wing model is made, and the bending test is carried out. The results are compared with the results of numerical simulation with ANSYS, and the results are close to each other. The aerodynamic performance of the designed two-dimensional airfoil is analyzed by using fluent fluid software in ANSYS. The pressure and velocity distribution on the plane of the airfoil at certain flight velocity and angle of attack is obtained, and the bending performance of the wing under the aerodynamic distributed load is analyzed.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V279;O341
本文编号：2122555
[Abstract]:Unmanned aerial vehicle (UAV) technology is playing an increasingly important role in modern military and other fields. In order to further improve the flight capability of UAV in high altitude and long voyage, it is necessary to carry out lightweight design of UAV. In this paper, based on the lightweight design of solar UAV wing, the bearing capacity of rigid wing filled with polyurethane foam is studied, and the bending performance of wing structure is analyzed. In this paper, the real structure of pores in rigid polyurethane foam is observed under microscope, and the Kelvin equivalent model for studying this kind of closed cell foam is established, and the equivalent mechanical properties of the model are given. The tensile, compression and three point bending tests of polyurethane foam were carried out, and the stress-strain relationship of the foam was obtained. The finite element software ANSYS is used to simulate the foam filled beam based on the theoretical elastic parameters and the measured parameters, and the results are compared with the results of the beam bending test measured by the total station instrument. The simulation results are in good agreement with the experimental values. The vibration frequency of foam filled beam was measured by VIC-3D non-contact full-field strain measuring instrument, and the numerical simulation was carried out. The simulation results are in good agreement with the experimental results. According to the actual demand, the wing structure is designed. According to the NACA0016 airfoil model, the wing model is made, and the bending test is carried out. The results are compared with the results of numerical simulation with ANSYS, and the results are close to each other. The aerodynamic performance of the designed two-dimensional airfoil is analyzed by using fluent fluid software in ANSYS. The pressure and velocity distribution on the plane of the airfoil at certain flight velocity and angle of attack is obtained, and the bending performance of the wing under the aerodynamic distributed load is analyzed.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V279;O341
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，本文编号：2122555
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