无人地效翼船气动仿真与飞控系统研究

发布时间：2018-12-29 10:02

【摘要】：地效翼船(Wings In Ground Craft)是一种通常飞行于离海面/地面十分贴近状态,并借助此飞行状态下产生的“地面效应”而能实现超低空飞行能力的特种飞行器。但从全球地效翼船的控制技术发展现状来看,对于此类飞行于水汽介质间高速飞行的飞行器,目前因研发地效翼船的理论知识还不成熟,所以其应用领域得不到拓展。然而,在计算机技术不断发展的今天,计算流体力学也得到快速发展,同时利用空气动力学对地效飞行器进行研究也成为当今研究热点;利用这种方法,可以为地效翼船气动布局设计和运动学模型的建立提供理论参考。同时,飞行控制系统作为地效翼船的飞行控制核心,负责整个飞行过程中的信息采集、控制信息解算和数据通信等任务,因此,针对地效翼船设计一套稳定的、适合其飞行特点的飞行控制系统具有较高研究意义。首先,本文介绍地效翼船有关的空气动力学主要研究方法,以及常用于数值流体计算的FLUENT软件。文中选取俄罗斯先进的“里海怪物”号地效翼船为原型,利用三维建模软件CATIA进行三维重建,后将所得三维模型导入ICME软件中进行网格化,最后利用FLUENT数值软件对网格化模型进行气动参数计算。同时,当其在地面效应区域内航行时,其航行平台经常性变化,为实现长时间稳定航行,需要研制平稳、可靠的飞行控制系统。本文结合固定翼飞行控制系统设计的经验和气动数值数据,对地效翼船的飞行控制系统进行设计。接着,在硬件上采取飞行控制与任务管理功能分开管理理念,确定以双片系统芯片为核心的飞行控制系统构架的整体方案;采用两块TMS320 F2812微计算机芯片分别充当主协控制器,分别负责进行飞行控制和导航数据解算的实现。在此架构上建立主控模块、以及传感器模块、舵机模块以及接口模块、降低系统耦合度,模块化完成系统设计;在软件设计上同样遵循模块化设计理念,实现底层各单元模块的驱动设计,对捷联惯导姿态模块机航向角算法进行分析,完成姿态、高度等数据解析。最后,针对地效飞行器特点,利用PID控制器设计实时、稳定的控制系统,在MATLAB中利用SRO优化软件包对地效飞行器纵向和横侧向进行控制律仿真。仿真结果表明控制器设计的合理性,具有较好地应用意义。
[Abstract]:Ground effect wing ship (Wings In Ground Craft) is a kind of special aircraft which usually flies close to the sea surface / ground, and can realize very low altitude flight ability with the help of "ground effect" in this flight state. However, according to the current situation of the control technology of the global ground effect wing ship, the application field of this kind of aircraft flying in the water vapor medium is not expanded because the theoretical knowledge of the research and development of the ground effect wing ship is not mature at present. However, with the development of computer technology, computational fluid dynamics (CFD) has been developed rapidly. This method can be used as a theoretical reference for the aerodynamic layout design and kinematics model establishment of a ground-effect wing ship. At the same time, the flight control system, as the flight control core of the ground effect wing ship, is responsible for the tasks of information collection, control information calculation and data communication during the whole flight. Therefore, a stable set of flight control system is designed for the ground effect wing ship. The flight control system suitable for its flight characteristics is of great significance. Firstly, this paper introduces the main research methods of aerodynamics related to the ground effect wing ship and the FLUENT software which is often used in numerical fluid calculation. In this paper, the Russian advanced Caspian Monster is selected as the prototype, the 3D modeling software CATIA is used to reconstruct the 3D model, and then the 3D model is imported into the ICME software for gridding. Finally, FLUENT numerical software is used to calculate the aerodynamic parameters of the gridding model. At the same time, when it navigates in the ground effect area, its navigation platform changes frequently. In order to realize the long-term stable navigation, it is necessary to develop a stable and reliable flight control system. In this paper, the flight control system of the ground effect wing ship is designed based on the experience of the design of the fixed-wing flight control system and the aerodynamic numerical data. Then, the concept of flight control and mission management is adopted separately in hardware, and the overall scheme of flight control system architecture with dual-chip system chip as the core is determined. Two TMS320 F2812 microchips are used as main controller, which are responsible for flight control and navigation data solution. The main control module, the sensor module, the steering gear module and the interface module are established on this architecture to reduce the coupling degree of the system and complete the system design by modularization. The software design also follows the idea of modular design and realizes the driving design of each unit module in the bottom layer. The algorithm of heading angle of sins attitude module is analyzed and the attitude and altitude data are analyzed. Finally, according to the characteristics of ground effect aircraft, a real-time and stable control system is designed by using PID controller. The longitudinal and lateral control laws of ground effect aircraft are simulated by SRO optimization software package in MATLAB. The simulation results show that the controller design is reasonable and has good application significance.
【学位授予单位】：南昌航空大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V249.1;V279

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