文档介绍：南京航空航天大学硕士学位论文直升机振动主动控制自适应控制律设计研究姓名:孙洪杰申请学位级别:硕士专业:飞行器设计指导教师:顾仲权20070301南京航空航天大学硕士学位论文i摘要降低直升机飞行中机体的振动水平,一直是直升机研制过程中最为关键的问题之一。振动主动控制由于具有良好的适应性、灵活性以及大幅度减振的有效性,成为人们在寻求更为有效的减振途径的过程中,可以信赖的一项新技术。在原有硬件基础上,可靠有效快速的控制算法(控制律),能够快速抵达控制目标,减少计算量,提高工作效率。本文重点研究直升机机体的结构响应振动主动控制中,具有在线辨识能力的自适应控制方法。研究不需要识别误差通道的时间平均梯度法(TAG),并对其改进;研究通过改变控制器输出进行误差通道辨识与调节控制器参数的联合方程法并进行改进,与推广用于多输入多输出的情况;研究简单的基于误差通道在线辨识的自适应前馈控制,消除周期外扰在辨识中的不利影响,在线辨识误差通道IIR模型,以及与自适应前馈控制相结合的方法。针对以上三种方法,均对直升机机体振动主动控制进行了单输入单输出和多输入多输出的仿真研究,证实了方法的有效性。关键词:直升机,结构响应主动控制,时间平均梯度法,联立方程法,系统辨识,自适应前馈控制直升机振动主动控制自适应控制律设计研究iiAbstractReducing the vibration level of helicopter fuselage during flight is always one of the most key problems in the development of helicopter. Due to the excellent adaptability, flexibility and the efficiency in vibration reduction, active control system have e a new technology which can be relied on in seeking more efficient vibration methods. Based on original hardware, control law of reliability, efficiency and quickness can rapidly reach control objective, putation difficulty, raise control efficiency. In this paper, the main research is aimed at those control methods in which system can be identified among active control of structural responses on helicopter fuselage. Time Averaged Gradient Method without identifying error path is investigated and modified. The Simultaneous Equations Method which identifies error path and modifies control filter coefficients by changing output of control filter is investigated, and is generalized to Multi Input Multi Output system. Adaptive feedforward control based on online identifying error path, online identifying error path IIR model by clearing bad influence of disturbance, bine adaptive feedforward control method are investigated in the paper. The effectiveness of the mentioned methods which are used in active control of helicopter fuselage vibration, concluding single input single output control and multi input multi output control, are verified by the simulations. Key