某型小展弦比飞翼式无人机控制律研究与建模仿真

发布时间：2018-06-15 22:58

本文选题：飞翼式无人作战飞机 + 飞行控制系统　；参考：《华中科技大学》2015年硕士论文

【摘要】：目前先进的无人作战飞机很多采用了飞翼布局,飞翼式无人作战飞机具有航程远、结构强度高以及隐身性能好等突出优势,但同时也具有稳定性差、操纵效率低下的缺点。本文以某型小展弦比飞翼式无人机为研究对象,分析其性能并以两种控制方法设计控制系统,仿真验证设计的可靠性并比较两种方法的优劣势。首先对算例无人机进行总体说明,在基本假设下建立非线性方程,并进行线性化及解耦。根据线性化后的方程,基于CFD仿真计算和风洞试验得到的气动数据,分析该型无人机的稳定性、操纵性和主要气动性能,进行模态分析,之后进一步讨论了航向操纵装置嵌入面布置在小展弦比无人机的影响。然后简要介绍了经典控制方法和鲁棒伺服LQR最优控制理论,用两种方法分别设计控制律,进而设计了整套飞行控制系统。在MATLAB/SIMULINK中搭建了本无人机的飞机模型,针对传感器噪声、环境等因素的影响尽可能进行模拟,仿真自主飞行过程并用三维动画模拟无人机的实时情况。通过航线上典型位置的阶跃响应曲线,对比分析两种控制方法,接着用蒙特卡罗方法进行拉偏仿真,验证了控制系统的可行性和鲁棒性。最后对全文进行总结工作,并展望可以进一步改进的不足之处以及能够深入研究的方向。
[Abstract]:At present, many of the advanced unmanned combat aircraft have adopted the wing layout. The flying wing unmanned combat aircraft has many outstanding advantages, such as long range, high structural strength and good stealth performance, but it also has the shortcomings of poor stability and low maneuvering efficiency. In this paper, a small aspect ratio flying wing UAV is studied, its performance is analyzed and the control system is designed by two control methods. The reliability of the design is verified by simulation and the advantages and disadvantages of the two methods are compared. The nonlinear equations are established under the basic assumptions, and the linearization and decoupling are carried out. According to the linearized equation, the stability, maneuverability and main aerodynamic performance of the UAV are analyzed based on the aerodynamic data obtained from CFD simulation and wind tunnel test, and the modal analysis is carried out. After that, the influence of the embedded surface of the heading control device on the small aspect ratio UAV is discussed. Then the classical control method and the robust servo LQR optimal control theory are briefly introduced. The control law is designed by two methods and the whole flight control system is designed. The aircraft model of the UAV is built in MATLAB / Simulink, which can simulate the sensor noise and environment factors as much as possible, simulate the autonomous flight process and simulate the real-time situation of UAV with 3D animation. Through the step response curve of typical position on the route, the two control methods are compared and analyzed, and then the simulation of pull deviation is carried out by Monte Carlo method, which verifies the feasibility and robustness of the control system. Finally, the paper summarizes the work, and looks forward to further improvement of the shortcomings and can be further research direction.
【学位授予单位】：华中科技大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V279;V249.1

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