【作者】 王莉；

【导师】 姜长生；

【作者基本信息】 南京航空航天大学 ， 模式识别与智能系统， 2004， 硕士

【摘要】 本文主要对贴地飞行时武装直升机的飞行控制系统进行深入的研究和探索，讨论了贴地飞行时气流扰动对直升机系统的影响，研究了H_∞鲁棒控制和动态逆控制在直升机飞控系统中的应用。主要的内容包括直升机飞行控制系统内外回路设计、直升机机动飞行的仿真、地形跟随的仿真以及OpenGL三维动画仿真等方面的内容。 由于直升机存在着较强的耦合性、不稳定性，呈现出较强的非线性，本文首先建立了直升机六自由度的小扰动耦合的运动模型。之后介绍了直升机遭受气流扰动的影响，并且建立了大气紊流和风切变的数学模型，为后面控制系统的设计提供了基础。 接着本文设计直升机姿态角速率指令(RCAH)、姿态角指令(ACAH)模态，按照时标分离的原则将直升机内环飞控系统划分为快慢回路，并分别采用H_∞和动态逆的方法设计控制器，使直升机的四个通道得到解耦。 随后在直升机外环回路进行设计，采用二次型状态调节器设计法设计速度控制回路。为了验证飞控系统的抗风扰动特性，引入风切变和紊流，仿真表明所设计的飞控系统对风扰动具有良好的鲁棒稳定性。并且选取几个典型的机动飞行科目进行仿真，结果表明达到ADS33D标准要求。 地形跟随系统的设计也是本文的一个重要内容，在这一章中，本文采用适应角法设计地形跟随系统，并提出了适应角法的改进方法。在典型地形情况下进行地形跟随仿真，并且为了真实模拟地形跟随，在控制通道加入风扰动，结果表明该飞控系统能够很好的抵抗风扰动，紧紧跟随最优轨迹飞行。 本文最后在VC环境下用OpenGL开发了直升机三维动画仿真平台，构造了三维地形和直升机模型，仿真了直升机做蛇形机动、急跃升／急跃降、地形跟随等机动飞行，通过逼真的视觉效果验证了飞控系统的正确性。更多还原

【Abstract】 The flight control system of attack helicopter and the influence of disturbance during NOE flight are studied in this dissertation. And the use of H∞ robust control and dynamicinversion schemes in flight control system are discussed. In this paper involved several aspects about the inner and outer loops design for helicopter flight control system, maneuver flight simulation for helicopter, terrain following simulation and 3D animation flight simulation system designed with OpenGL.Because model of helicopter is a highly coupled unstable nonlinear system, a group of six free-degree linear motion equations in combination with micro disturbance and couple are established firstly, and analyzed the infection of the disturbance to the helicopter and then mathematical Models of wind shear and turbulence are represented. This work supplied the basis for the design of the flight control system.Secondly, the modes of RCAH and ACAH are designed with H∞ robust control and dynamic inversion schemes. The controller is designed at two time scales. And the simulation shows the uncoupling of four loops is achieved with H∞ robust control anddynamic inversion schemes.Thirdly, the paper used linear quadratic state actuator scheme to design the velocity controlling loop. In order to test the anti-disturbance capability of the flight control system, the models of wind shear and turbulence are introduced to the flight control system. The result of simulation shows the flight control system has excellent anti-disturbance capability. Then several typical maneuvers are picked up to simulate, and the result shows that the control system can satisfy the design specification of ADS33D criteria .The design of terrain following system is another important part of the dissertation. The terrain following system is designed by adaptive angle method. But there are some problems in the system so the improved adaptive angle method is given. Then above the typical terrain and under the disturbance the terrain following system is simulated. The result shows the flight control system can withstand the disturbance and track the optimal trajectory.Finally, the thesis developed 3D animation flight simulation platform for helicopter using OpenGL in Visual C++. And the 3D terrain and helicopter model are constructed. The simulation of two typical maneuver (S maneuver flight and BopUp-BopDown) and terrain following shows that the fight control system of attack helicopter is improved by the realistic optical impact.更多还原