【摘要】：微型飛行器具有隱蔽小巧與機動性高等特點,因而存在極高的軍事價值。常規(guī)的氣動布局會使微型飛行器產(chǎn)生氣動力不足和穩(wěn)定性差等問題,而相同尺寸的飛行生物則不存在這些問題,從而仿生的微型飛行器成為了學(xué)者們在該領(lǐng)域的研究熱點。由于生物飛行具有低流場雷諾數(shù)、復(fù)雜拍動和可變形翼等特點,因此針對低流場雷諾數(shù)流場下的微型柔性翼空氣動力特性研究具有較大的意義。本文基于雙向迭代流固耦合算法,利用ANSYS Workbench中的Mechanical和Fluent模塊建立了針對微型柔性翼的雙向流固耦合數(shù)值計算方法。在此基礎(chǔ)上,針對低流場雷諾數(shù)流場中的微型柔性翼進(jìn)行了流固耦合數(shù)值模擬研究。主要的研究內(nèi)容和成果如下:針對微型柔性翼進(jìn)行了滑翔狀態(tài)下的數(shù)值模擬研究,得到了微型柔性翼在滑翔狀態(tài)下的結(jié)構(gòu)振動位移和氣動力系數(shù)隨時間的變化規(guī)律,進(jìn)一步針對結(jié)構(gòu)振動位移和氣動力系數(shù)進(jìn)行了幅頻特性分析,并研究了微型柔性翼剛度和流場雷諾數(shù)對結(jié)構(gòu)振動特性、氣動力特性和流場特性的影響。針對處于拍動狀態(tài)下的微型柔性翼開展了數(shù)值模擬研究,得到了一個拍動周期內(nèi)懸停拍動和前飛拍動微型柔性翼的氣動力系數(shù)隨時間的變化規(guī)律,結(jié)合拍動流場對比分析了懸停拍動和前飛拍動升阻力系數(shù)峰值和波動的成因。并分析了微型柔性翼剛度和拍動頻率對懸停拍動狀態(tài)的氣動力特性和流場特性的影響。
[Abstract]:Because of its small concealment and high maneuverability, micro-aircraft has high military value. The conventional aerodynamic layout will lead to the problems of poor aerodynamic force and poor stability, but the same size of flying organisms do not exist these problems, so biomimetic micro air vehicle has become the research hotspot in this field. Because biological flight has the characteristics of low Reynolds number complex flapping and deformable wing it is of great significance to study the aerodynamic characteristics of micro flexible wing in low Reynolds number flow field. Based on the bidirectional iterative fluid-solid coupling algorithm, a bidirectional fluid-structure coupling numerical method for micro flexible wing is established by using the Mechanical and Fluent modules in ANSYS Workbench. On this basis, the fluid-solid coupling numerical simulation of the micro flexible wing in the low Reynolds number flow field is carried out. The main research contents and results are as follows: the numerical simulation of the micro flexible wing in gliding state is carried out, and the variation of vibration displacement and aerodynamic coefficient of the micro flexible wing with time is obtained. Furthermore, the amplitude-frequency characteristics of the structural vibration displacement and aerodynamic coefficients are analyzed, and the effects of the stiffness of the micro flexible wing and the Reynolds number of the flow field on the vibration characteristics, aerodynamic characteristics and flow field characteristics of the structure are studied. A numerical simulation study was carried out on a micro flexible wing in a flapping state. The aerodynamic coefficients of the micro flexible wing with hovering and forward flapping during a flapping period were obtained. The causes of the peak value and fluctuation of hovering flapping and forward flapping resistance coefficient are analyzed in combination with the flapping flow field. The effects of the stiffness and flapping frequency of the micro flexible wing on the aerodynamic characteristics and the flow field characteristics of the hovering flapping state are 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】：2016
【分類號】：V224
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本文編號：2166016