论可折叠弹翼在展开过程中的冲击振动及冲击振动应力的试验分析方法，建立了通过位移模态预估冲击应力的方法。

封严蓖齿的气弹力对转子系统的稳定性起重要用用，本文建立了具有封严蓖齿的转子系统动力稳定性的分析方法。该方法利用传递矩阵法建立系统的主导方程，将封严蓖齿的气弹力以等致刚度及等致阻尼系数的方式引入转子系统的主导方程，用数值积分法解主导方程，求得系统的动力物性，根据扰动解判断系统的稳定性。本文所建立的分析软件，也可计算转子系统的不平衡响应、临界转速、这加不平衡响应等、文中对一模型转子进行了算例分析。

建立桨轴发动机整机动力响应的分析方法，用传递矩阵法建立发动机机匣、主燃气发生器转子、自由涡轮转子的综合动力学方程，并对耦合方程进行求解。此方法有效地考虑了主燃气发生器转子系统与自由涡轮转子系统的耦合效应。可分析主燃气发生器转子与自由涡轮转子系统的临界转速和不平衡响应，估计机匣系统的不平衡响应。

在瞬态响应，特别是突加不平衡响应计算中，发现阶跃响应很大。因此，采用常规的盘传递矩阵出现了问题。因为此时等项是不可忽略的。本文导出了考虑影响时，质点与盘的传递矩阵，井以一双转子航空发动机的转子——支承系统为例进行了突加不平衡响应计算，结果表明，改进后的传递矩阵有较好的适应性，克服了常规盘传递矩阵的弱点。文中所导出的传递矩阵也可用于转子系统的加速特性分析等。

建立了静子与转子部分的数学模型，提出了借实测的安装节动刚度。计算各主轴承到安装节的传递函数和转子系统的动力响应，进而预计发动机整机稳态动力响应的方法。附有一双转子航空发动机计算实例。

本文建立了航空发动机静于支承刚性的一种传递矩阵算法。该方法不仅可以计算出发动机静于支承刚性，也可以计算出发动机主支承到发动机安装节的传递函数。发动机静于支承剐性是发动机整机及转于系统动力特性分析所必须的数据，通常由实测法获得，然而在不具奋实测条件时，一种较有效的解析方法是必要的。本文对一实际发动机静子系统进行了分析计算，在实测飞机上发动机安装节处的动柔度矩阵的基础上，分析得出静子支承剐性和主支承到安装节的传递函数。

奉文进行了齿轮振动的粘弹阻尼控制研究，文中进行丁自由阻尼层结构的力学特性分析，进行了阻尼材料位置与彤状大小的优化研究，以最小的附加质量获得最佳的振动效果。本文还进行了蕞型齿轮的实验研究，结果表明，齿轮辐板振动的粘弹阻尼控制对齿轮的振动有相当满意的控制效果，表明这一方法是可行的，也是有进一步研究意义的。

TV-Holography system is used to measure the structure vibration and to perform experimental modal aslalysis. There are several kinds of structure that are very difficult to measure their dynamic response and modals by. general experimental modal analysis methods, such as structures with relatively large damping and structures with nonlinear behavior or structures with small dimension. Especially, the aeroengine blades are twisted and have variable section area. This causes much difficult to measure the vibration modal. The TV-Holography method can overcome this difficult and has very high precision. In this paper, the basic principle of the TV-Holography is introduced. Two kinds of structures are given as examples to describe the method used in this paper.

Many theoretical research papers are reported in resent years in the field of rotor vibration control. The theoretical research results are the bases tothe experimental investigation in Active Control of Rotor System. Aiming to realize the more applied active vibration control of rotor system, a new actuator, Controlled Squeeze Film Damping Bearing(CSFDB), is developed in this paper. The control principle of CSFDB is performed mainly with the aid of a specially designed electro-hydraulic servo system, which adjusts the axial position of the outer ring of the squeeze film bearing so that a desired film clearance is reached. In consequence, the stiff and damping natures of the whole rotor-bearing system is changed to ensure the stability and safety of system operation. The major research work of this paper can be roughly divided into following three parts: (1) Investigation on the vibration natures of CSFDB-rotor system. (2) Study on accelerate and decelerate vibration responses of CSFDB-rotor system. (3) Experimental investigation on the active vibration control scheme of CSFDB-rotor system. The experimental results reveal that the CSFDB developed in this paper is really effective to actively control the vibration of rotor systems and good prospect to be wildly used in modern industries.

In this paper, a method for analyzing the dynamic characteristics of a propeller-rotor system is derived by the transfer matrix method. The method can not only take the influence of the rotor case into account, but also deal with the coupling between the flee turbine rotor and the main gas turbine rotor. By this method, the critical speeds of both flee turbine rotor and gas turbine rotor can be calculated easily. Moreover, the dynamic response of the propeller-rotor system can also be alculated. Then through the transfer relationship, any dynamic point responses of the rotor system and the case can be predicted. A typical propeller-rotor system is analyzed in this paper. The results are satisfactorily close to the experimental results reported by some Institute. In this paper, a detailed introduction about this method, together with a detailed analysis about the results is presented.