本文首先介绍了飞行器振动研究方面的发展趋势。过去飞行器结构动力学主要研究弹性飞机在外载荷(力、运动)作用下的结构动力特性和响应。随着航空科学技术的发展,引进了飞行器结构变形对气动力的影响,发展成为气动弹性力学。现在又引进自动控制技术,不仅考虑了结构变形与空气动力的耦合,而且考虑结构系统与控制系统的耦合,发展成为受控气动弹性力学,或受控结构动力学。接着介绍了开环飞机结构动力学的研究内容,包括正问题、逆问题两大类。把已知输入(力、运动)加到已经估算出来的数学模型(如通过有限元素法求得)上,求得所需要的输出,叫做正问题。逆问题之一叫模态识别(或参数识别),即把已知输入加到飞行器上,通过实验测得输出,从而求出数学模型。另一是载荷识别,即根据算出或识别出来的数学模型,和在实际工作情况下测得的输出来确定输入。 本文最后在强调研究飞行器振动问题重要性的基础上,对振动环境问题的研究途径和方法提出了建议与看法。 This paper first introduces the development trend of aircraft vibration research. In the past, the structural dynamics of aircraft mainly studied the dynamic characteristics and response of the flexible aircraft under external loads (force and motion). With the development of aviation science and technology, the introduction of the deformation of the aircraft structure on the impact of aerodynamic, developed into aeroelasticity mechanics. Now the introduction of automatic control technology, not only to consider the structural deformation and aerodynamic coupling, but also consider the coupling of structural system and control system, developed into a controlled aerodynamic elasticity, or controlled structural dynamics. Then introduced the open-loop aircraft structure dynamics research content, including positive problems, inverse problems two categories. The known input (force, motion) is added to the mathematical model has been estimated (as determined by the finite element method), the required output, called the positive problem. One of the inverse problems is called modal identification (or parameter identification). That is, the known input is added to the aircraft and the output is measured experimentally to find the mathematical model. The other is load identification, which is based on the mathematical model calculated or identified, and measured in the actual work under the output to determine the input. Finally, on the basis of emphasizing the importance of studying the vibration problem of aircraft, the suggestions and opinions on the research approaches and methods of vibration environment are put forward.