高速直升机总体技术方案及关键部件研究

发布时间：2018-05-01 13:43

本文选题：高速直升机 + 共轴双旋翼　；参考：《兰州交通大学》2015年硕士论文

【摘要】：常规直升机飞行速度相对较低、航程相对较小,这很大程度地限制了其应用和发展,因此提高其飞行速度和增大最大航程已成为直升机研究的重点和热点。发展和应用高速、长航时直升机,在军用和民用领域分别可有效地提升部队机动和战斗能力,可提高其应用经济性和时效性。论文依据其发展和应用需求,分别从总体技术方案、旋翼系统和操纵机构三个方面展开相关研究工作,主要工作包括:依据设计指标与需求以及主流高速构型,确定其总体技术方案。论文中的高速直升机方案以共轴反转双旋翼为主旋翼,尾部配备共轴反转螺旋桨作为辅助推进装置。根据设计指标与要求,分析高速直升机的飞行环境,建立高速直升机的初步外形,进行高速直升机的总体布局,分析高速直升机的控制面并确定了其发动机规格和主要参数等。对高速直升机功率需求进行分析,验证所确定的发动机是合理的,所确定的主要参数满足高速直升机的设计指标与要求。根据总体技术方案,对主旋翼系统进行设计与分析。基于动量-叶素理论,建立桨叶的微元升力、阻力和扭矩等,利用积分法对微元载荷在桨盘内沿展向和周向进行数值积分。对主旋翼系统的载荷进行了数值分析和求解,获得不同飞行状态下桨叶载荷在桨盘上的分布云图,其仿真结果可用于高速直升机主旋翼零部件的结构设计与分析。根据直升机的构型特点和总体方案中确定的主要参数,对主旋翼系统的桨叶和桨毂进行初步结构设计,并对其进行静强度分析。结合总体技术方案和旋翼载荷分析,对主旋翼操纵机构进行模块化运动学和静力学建模与分析。建立直升机在任意飞行状态下主旋翼操纵机构运动学模型,所建立的运动学模型可为主旋翼操纵机构机理建模和控制建模提供理论依据。建立主旋翼操纵机构的静力学模型,并在不同的飞行状态下对其静力学关系进行仿真分析,所建立的静力学模型可用于分析直升机在不同飞行状态下主旋翼操纵机构间的静力学关系,结合操纵机构动力学模型对操纵机构进行优化。基于清华大学实验室在研共轴式直升机,搭建直升机旋翼系统载荷和操纵机构载荷测量实验平台。载荷测量实验主要包括旋翼气动载荷测量、操纵机构拉杆载荷测量和旋翼转速测量三个方面,介绍实验系统的各部分硬件电路和上位机,并对下一步的实验内容进行规划,测得的载荷数据可用于旋翼系统和操纵机构的优化设计,具有重要的实用意义。
[Abstract]:The flight speed and range of conventional helicopter are relatively low, which limits its application and development to a great extent. Therefore, increasing its flying speed and increasing its maximum range have become the focus and hotspot of helicopter research. The development and application of high-speed and long-haul helicopters can effectively enhance the mobility and combat capability of troops in the military and civilian fields, and improve the economy and timeliness of their application. According to its development and application requirements, the thesis carries out related research work from three aspects: overall technical scheme, rotor system and control mechanism. The main work includes: according to the design indicators and requirements, and the mainstream high-speed configuration. Determine its overall technical plan. In this paper, the main rotor of the high speed helicopter is the coaxial reverse rotor and the tail of the helicopter is equipped with the coaxial reverse propeller as the auxiliary propulsion device. According to the design indexes and requirements, the flying environment of high-speed helicopter is analyzed, the initial shape of high-speed helicopter is established, the overall layout of high-speed helicopter is carried out, the control surface of high-speed helicopter is analyzed, and the engine specifications and main parameters are determined. The power requirement of high speed helicopter is analyzed to verify that the engine is reasonable and the main parameters can meet the design requirements of high speed helicopter. According to the overall technical scheme, the main rotor system is designed and analyzed. Based on the momentum-blade theory, the differential lift, resistance and torque of the blade are established, and the integral method is used to integrate the differential element load along the span and circumference direction of the propeller disk. The load of the main rotor system is numerically analyzed and solved, and the distribution of the blade load on the rotor disk under different flight conditions is obtained. The simulation results can be used in the structural design and analysis of the main rotor parts of the high-speed helicopter. According to the configuration characteristics of the helicopter and the main parameters determined in the overall scheme, the primary structural design of the rotor blade and hub of the main rotor system is carried out, and the static strength analysis is carried out. The modular kinematics and statics modeling and analysis of the main rotor steering mechanism are carried out based on the overall technical scheme and rotor load analysis. The kinematics model of helicopter main rotor operating mechanism under arbitrary flight condition is established. The kinematics model can provide theoretical basis for the mechanism modeling and control modeling of rotor control mechanism. The statics model of the main rotor manipulator is established, and its statics relationship is simulated under different flight conditions. The static model can be used to analyze the statics relationship between the main rotor manipulators under different flight conditions, and to optimize the manipulators combined with the dynamic model of the manipulators. Based on the research of coaxial helicopter in Tsinghua University laboratory, the experimental platform of helicopter rotor system load measurement and control mechanism load measurement is built. The load measurement experiment mainly includes three aspects: rotor aerodynamic load measurement, control mechanism pull rod load measurement and rotor speed measurement. The hardware circuit and upper computer of the experiment system are introduced, and the next experiment content is planned. The measured load data can be applied to the optimal design of rotor system and control mechanism, which is of great practical significance.
【学位授予单位】：兰州交通大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V275.1

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