新构型倾转四旋翼飞行器总体方案设计与研究

发布时间：2018-05-15 19:51

本文选题：倾转旋翼机 + 多旋翼飞行器　；参考：《南京航空航天大学》2016年硕士论文

【摘要】：本文设计的新构型倾转四旋翼飞行器结合了多旋翼飞行器和固定翼飞机,是一种具有创新性的飞行器。其充分利用成熟稳定的多旋翼控制技术,兼备垂直起降/悬停和快速前飞的特点,能够在军民用领域完成一系列较为复杂的任务。首先,通过对多旋翼飞行器以及传统倾转旋翼机的发展与研究总结这两种飞行器的各自优缺点,针对设计要求提出该飞行器的不同构型方案,并进行分析比较,以确定合适的飞行器方案。其次,对确定的新构型倾转四旋翼飞行器进行总体参数设计,以选定合适的动力系统。接着进行气动布局设计,包括四旋翼模式、固定翼模式以及倾转过渡过程的气动布局设计,对各主要部件的参数进行设计,并确定飞行器焦点及重心参考位置,绘制三面图。然后,对各部件进行详细的结构设计,利用Patran/Nastran对机翼进行结构分析和强度校核,并对整机在不同状态下利用Fluent进行螺旋桨/机翼/机身的气动干扰分析,以及根据理论推导结合实际数据进行性能计算。最后,制作原理样机,调试后进行试飞验证,证明了本文设计的新构型倾转四旋翼飞行器飞行原理合理可行,为后期研制可用于军民用领域的飞行器打下了基础。
[Abstract]:The new type tilting four-rotor aircraft designed in this paper is a kind of innovative aircraft which combines multi-rotor aircraft and fixed-wing aircraft. It makes full use of mature and stable multi-rotor control technology and has the characteristics of vertical takeoff / hover and fast forward flight. It can accomplish a series of complex tasks in the field of military and civilian use. First of all, through the development and research of the multi-rotor aircraft and the traditional tilting rotor aircraft, the advantages and disadvantages of the two kinds of aircraft are summarized, and the different configuration schemes of the aircraft are put forward according to the design requirements, and the analysis and comparison are carried out. To determine the appropriate aircraft plan. Secondly, the overall parameters of the new configuration tilting four rotor aircraft are designed to select the appropriate power system. Then the aerodynamic layout design is carried out including four rotor mode fixed wing mode and tilting transition process. The parameters of the main components are designed and the focus and reference position of the center of gravity of the aircraft are determined and the three-sided diagram is drawn. Then, the detailed structural design of each component is carried out, the structure analysis and strength check of the wing are carried out by using Patran/Nastran, and the aerodynamic interference analysis of the propeller / wing / fuselage is carried out by using Fluent in different states. And according to the theoretical derivation combined with the actual data to calculate the performance. Finally, the principle prototype is made and flight test is carried out after debugging, which proves that the flight principle of the new configuration tilting four-rotor aircraft designed in this paper is reasonable and feasible, which lays the foundation for the later development of the aircraft which can be used in the field of military and civilian use.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V275.1

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