硕士学位论文 仿生扑翼飞行器设计及空气动力特性研究 DESIGN AND AERODYNAMIC ANALYSIS OF A BIOINSPIRED FLAPPING WING AIR VEHICLE 周启生 哈尔滨工业大学 2012年12月
硕士学位论文 仿生扑翼飞行器设计及空气动力特性研究 DESIGN AND AERODYNAMIC ANALYSIS OF A BIOINSPIRED FLAPPING WING AIR VEHICLE 周启生 哈尔滨工业大学 2012 年 12 月
国内图书分类号：V276 学校代码：10213 国际图书分类号：621 密级：公开 工程硕士学位论文 仿生扑翼飞行器设计及空气动力特性研究 硕士研究生：周启生 导 师： 周超英教授 申请学位： 工程硕士 学科、专业： 机械工程 所在单位： 深圳研究生院 答辩日期： 2012年12月 授予学位单位： 哈尔滨工业大学
国内图书分类号：V276 学校代码：10213 国际图书分类号：621 密级：公开 工程硕士学位论文 仿生扑翼飞行器设计及空气动力特性研究 硕 士 研 究 生： 周启生 导 师： 周超英 教授 申请学 位： 工程硕士 学 科 、 专 业： 机械工程 所在单 位： 深圳研究生院 答辩日 期： 2012 年 12 月 授予学位单 位： 哈尔滨工业大学
Classified Index:V276 U.D.C:621 Dissertation for the Master Degree of Engineering DESIGN AND AERODYNAMIC ANALYSIS OF A BIOINSPIRED FLAPPING WING AIR VEHICLE Candidate: Zhou Qisheng Supervisor: Prof.Zhou Chaoying Academic Degree Applied for: Master of Engineering Specialty: Mechanical Engineering Affiliation: Shenzhen Graduate School Date of Defense: Dec,2012 Degree-Conferring-Institution: Harbin Institute of Technology
Classified Index: V276 U.D.C: 621 Dissertation for the Master Degree of Engineering DESIGN AND AERODYNAMIC ANALYSIS OF A BIOINSPIRED FLAPPING WING AIR VEHICLE Candidate: Zhou Qisheng Supervisor: Prof. Zhou Chaoying Academic Degree Applied for: Master of Engineering Specialty: Mechanical Engineering Affiliation: Shenzhen Graduate School Date of Defense: Dec, 2012 Degree-Conferring-Institution: Harbin Institute of Technology
摘要 摘要 扑翼飞行器是一种依靠翅膀扑动产生飞行动力的新概念飞行器。同许多新技 术的产生一样，它是应军事战略的需求，在近几十年飞速发展起来的。扑翼飞行 器有着特殊的空气动力学，在小尺度、低雷诺数下有出色的飞行能力，可微化的 空间大。由于其良好的隐蔽性和飞行性能，成为新一代无人侦察机的探索方向。 本文针对扑翼样机的设计，对扑翼飞行机理、扑翼机构和气动特性进行了连续系 统性的研究。 鸟类和昆虫是扑翼飞行器的原型。本文从仿生学角度研究了其翅膀的运动特 征，分析生物飞行的高升力机理，基于此原理说明扑翼飞行在不同姿态下所需的 条件，并结合固定翼空气动力学，对比分析研究的重点，同时探讨飞行器各部件 有关提升升力的因素。 机构是扑翼飞行器的核心部分，它直接决定扑翼的动作。本文依据蜂鸟和昆 虫的扑动，探索性的设计了两种多维扑动的扑翼机构：二维扑动机构和8字扑动 机构。两种机构都是单自由度，结构简单，通过运动学分析和轨迹仿真得出，仿 生扑动在运动上具有绝对优势和可行性。 空气动力分析采用8字机构的运动，应用ADNA的流固耦合功能和完全动网 格技术进行2D模拟。分析过程建立了几种不同的模型，结果表明前缘控制点的升 力最大，并且升力随弦长和频率的增加而增加，这对机翼的优化设计有前瞻性的 指导作用。 样机设计依托于前边的理论研究，主要工作是对机械结构和气动部件进行了 结构和工艺设计。由于尺寸和重量的限制，按照模块的功能要求选择了不同的材 料，并加工成样机，通过扑动实验测试表明，样机的各项设计参数符合要求，为 进一步的研究奠定基础。 关键词：扑翼飞行器：多维扑动：8字扑动：流固耦合：动网格 -1
摘要 -I- 摘要 扑翼飞行器是一种依靠翅膀扑动产生飞行动力的新概念飞行器。同许多新技 术的产生一样，它是应军事战略的需求，在近几十年飞速发展起来的。扑翼飞行 器有着特殊的空气动力学，在小尺度、低雷诺数下有出色的飞行能力，可微化的 空间大。由于其良好的隐蔽性和飞行性能，成为新一代无人侦察机的探索方向。 本文针对扑翼样机的设计，对扑翼飞行机理、扑翼机构和气动特性进行了连续系 统性的研究。 鸟类和昆虫是扑翼飞行器的原型。本文从仿生学角度研究了其翅膀的运动特 征，分析生物飞行的高升力机理，基于此原理说明扑翼飞行在不同姿态下所需的 条件，并结合固定翼空气动力学，对比分析研究的重点，同时探讨飞行器各部件 有关提升升力的因素。 机构是扑翼飞行器的核心部分，它直接决定扑翼的动作。本文依据蜂鸟和昆 虫的扑动，探索性的设计了两种多维扑动的扑翼机构：二维扑动机构和 8 字扑动 机构。两种机构都是单自由度，结构简单，通过运动学分析和轨迹仿真得出，仿 生扑动在运动上具有绝对优势和可行性。 空气动力分析采用 8 字机构的运动，应用 ADINA 的流固耦合功能和完全动网 格技术进行 2D 模拟。分析过程建立了几种不同的模型，结果表明前缘控制点的升 力最大，并且升力随弦长和频率的增加而增加，这对机翼的优化设计有前瞻性的 指导作用。 样机设计依托于前边的理论研究，主要工作是对机械结构和气动部件进行了 结构和工艺设计。由于尺寸和重量的限制，按照模块的功能要求选择了不同的材 料，并加工成样机，通过扑动实验测试表明，样机的各项设计参数符合要求，为 进一步的研究奠定基础。 关键词：扑翼飞行器；多维扑动；8 字扑动；流固耦合；动网格
Abstract Abstract Flapping air vehicle is a new concept aircraft which the fly power produced by flapping wings.Just like other new technologies,it has a rapid development in recent decades due to the military strategic demands.Ornithopter has different aerodynamics and excellent ability to fly in small-scale and low Reynolds number.Because of its good concealment and flight performance,it is widely researched in the next generation of UAV.This paper has systematically studied the principle of flapping flight,flapping mechanism and aerodynamics for the design ofprototype. Birds and insects is the model of flapping air vehicle.The high lift mechanism has analyzed based on the movement of their wings,and further explanation has made to tell the essential condition for flight under different fly gesture.Comparing these studies with fixed wing aerodynamic,the main problem that should be focus on was clearly. The elements that the parts ofaircraft about increasing lift have studied as well. Flapping mechanism is the core component which directly controls the movements of wings.This paper has designed two multidimensional flapping mechanisms which are two-dimensional and 8 flapping mechanism.The two bionic mechanisms are simply single freedom and have absolute advantages and feasibility according to the conclusions ofkinematics analysis and trace simulation. Aerodynamics analysis is based on the motion of8 flapping that has stud ied before. The main process is to simulate it in 2D unsteady incompressible condition by using ADINA fluid structure interaction module and full adaptive mesh.Several models for contrast were built and analyzed.The result after analysis shows that the lift would be increase by increasing the chord length and flapping frequency,and the leading edge control point produced more lift than other positions.All the conclusions would play a guide role in optimizing design process. Prototype design is based on the conclusions researched.The main work is to design the detail of structure and process of mechanical and aerodynamic system. Several materials were choose and analyzed according to the function of parts and limits of size and weight.The prototype has made and tested finally.All the parameters meet the requirements and the conclusions are good for a further research Keywords:flapping air vehicle,multidimensional flapping 8 flapping,fluid structure interaction,adaptive mesh
Abstract -IIAbstract Flapping air vehicle is a new concept aircraft which the fly power produced by flapping wings. Just like other new technologies, it has a rapid development in recent decades due to the military strategic demands. Ornithopter has different aerodynamics and excellent ability to fly in small-scale and low Reynolds number. Because of its good concealment and flight performance, it is widely researched in the next generation of UAV. This paper has systematically studied the principle of flapping flight, flapping mechanism and aerodynamics for the design of prototype. Birds and insects is the model of flapping air vehicle. The high lift mechanism has analyzed based on the movement of their wings, and further explanation has made to tell the essential condition for flight under different fly gesture. Comparing these studies with fixed wing aerodynamic, the main problem that should be focus on was clearly. The elements that the parts of aircraft about increasing lift have studied as well. Flapping mechanism is the core component which directly controls the movements of wings. This paper has designed two multidimensional flapping mechanisms which are two-dimensional and 8 flapping mechanism. The two bionic mechanisms are simply single freedom and have absolute advantages and feasibility according to the conclusions of kinematics analysis and trace simulation. Aerodynamics analysis is based on the motion of 8 flapping that has studied before. The main process is to simulate it in 2D unsteady incompressible condition by using ADINA fluid structure interaction module and full adaptive mesh. Several models for contrast were built and analyzed. The result after analysis shows that the lift would be increase by increasing the chord length and flapping frequency, and the leading edge control point produced more lift than other positions. All the conclusions would play a guide role in optimizing design process. Prototype design is based on the conclusions researched. The main work is to design the detail of structure and process of mechanical and aerodynamic system. Several materials were choose and analyzed according to the function of parts and limits of size and weight. The prototype has made and tested finally. All the parameters meet the requirements and the conclusions are good for a further research. Keywords: flapping air vehicle, multidimensional flapping, 8 flapping, fluid structure interaction, adaptive mesh