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在气动弹性力学中，机翼振颤是一个非常典型的问题。Airfoil flutter is one of the important problems in aeroelasticity.

耦合结构动力学方程，建立了基于状态空间的跨声速气动弹性分析模型。Coupled with the structural equations, the models for transonic aeroelasticity in state-space are got.

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本文研究考虑气动弹性时飞行器的纵向稳定性问题。The longitudinal stability of elastic vehicles is studied with the effect of aeroelasticity considered.

大型民用飞机普遍具有大展弦比机翼的特点，其气动弹性问题尤为突出。There exist obvious aeroelasticity problem for the large-scaled civil aircraft with high aspect ratio wings.

研究静气动弹性问题一大关键是要解决流固数据耦合。Realizing data exchange to reflect coupling between fluid and structures is essential to solving static aeroelasticity problems.

振荡叶栅的非定常分离、粘性效应和跨音激波对失速颤振的影响成为当前气动弹性力学的主要难点。The main difficulty on the study of aeroelasticity lies in the effects of unsteady separation, shock and viscosity to the stall flutter.

但是这种新型的结构也带来了强度、气弹稳定性等问题，对此给出了一些分析结果和建议。However, this new structure also leads to some problems in strength and aeroelasticity , so some analytical results and suggestions are presented.

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本文研究了用于描述非定常气动力和气动弹性现象的一类积分-微分方程的辨识问题。In this paper, we studied identification of a kind of integro-differential equations to describe unsteady aerodynamics and aeroelasticity phenomenon.

为了消除飞行器的气动弹性与控制系统之间的互相影响，必须适当选择传感器的安装位置。In order to eliminate the interaction between aeroelasticity and flight control of vehicles, the positions of mounted sensors must be chosen properly.

高超声速飞行器设计上的特点带来了一系列的气动弹性新问题。There are many new problems of aeroelasticity which are introduced by the novel concepts and system characteristics in the design process of hypersonic vehicles.

而后就简化的非定常气动力数学模型提出了分析气动弹性对飞行器稳定性影响的方法。A method of analysis of the effect of aeroelasticity on the stability of elastic vehicles by using a simplified mathematical model of unsteady aerodynamic forces is proposed.

就简化的非定常气动力数学模型提出了分析气动弹性时飞行器稳定性的影响的方法。With simplified unsteady aerodynamic force mathematical model, method of analysis for the effects of aeroelasticity on the dynamic stability of elastic vehicles is established.

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将等效板模型推广应用到典型机翼结构的静力学、动力学以及静、动气动弹性分析中。Some typical numerical results are presented from application of the model to static analysis, dynamic analysis, static aeroelasticity and flutter analysis of a wing-box and a wing.

将等效板模型推广应用到典型机翼结构的静力学、动力学以及静、动气动弹性分析中。Some typical numerical results are presented from application of the model to the static analysis, dynamic analysis, static aeroelasticity and flutter analysis of a wing-box and a wing.