【摘要】：無人機技術(shù)在現(xiàn)代軍事等領(lǐng)域發(fā)揮著越來越大的作用,要想進一步提高無人機高空長航時的飛行能力,需要對無人機進行輕量化設(shè)計。本文以太陽能無人機機翼的輕量化設(shè)計為研究背景,對聚氨酯泡沫填充可剛化機翼的承力性能進行研究,分析機翼結(jié)構(gòu)的抗彎性能。本文通過在顯微鏡下觀察得到硬質(zhì)聚氨酯泡沫材料內(nèi)部孔洞的真實結(jié)構(gòu),建立研究此類閉孔泡沫材料的Kelvin等效模型,并給出研究該模型的等效力學(xué)性能;對聚氨酯泡沫材料進行拉伸、壓縮及三點彎曲試驗,得到該泡沫材料的應(yīng)力-應(yīng)變關(guān)系等力學(xué)性能。利用ANSYS有限元軟件對泡沫填充梁進行基于理論彈性參數(shù)與實測參數(shù)的數(shù)值模擬,并與用全站儀測得的梁彎曲試驗的結(jié)果進行對比,模擬值與試驗值吻合較好;使用VIC-3D非接觸全場應(yīng)變測量儀測得泡沫填充梁的振動頻率,并進行數(shù)值模擬,模擬與試驗結(jié)果符合。根據(jù)實際需求對機翼結(jié)構(gòu)進行設(shè)計,按照設(shè)計的NACA0016翼型制作機翼模型,對制作的機翼模型進行彎曲試驗,并與用ANSYS進行數(shù)值模擬的結(jié)果對比,對比結(jié)果比較接近;使用ANSYS中的Fluent流體軟件對所設(shè)計的二維翼型進行氣動性能分析,得到在一定飛行速度和攻角時翼型面上的壓力和速度分布,并分析了氣動分布載荷下機翼的彎曲性能。
[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.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V279;O341

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本文編號：2122555