本文评述了几种已有的状态空间气动弹性模型，提出了改进意见。
In this paper a review, is made of the existing state-space aeroelastic models, some improvements are made, and a new state-space aeroelastic model is presented.
为研究高压输电塔线体系的合理化抗风设计，进行了气动弹性模型风洞试验。
An aeroelastic wind tunnel test was carried out to study the rational wind resistant design method for high-voltage transmission tower-line coupling system.
算例表明：本文提出的新的状态空间气动弹性模型是一种精度较高而阶数较低的模型。
The results show that the new state-space aeroelastic model is one which has higher accuracy and lower order.
设计制作了一外形和动力特性在一定范围内可调的超高层建筑多自由度气动弹性模型。
A super high rise buildings aeroelastic model, whose configuration and dynamics can be changed to some extent, has been designed and made.
并对CZ - 2、土星IB气动弹性模型在地面风荷载下的动态响应进行工程计算，与试验结果有良好的一致性。
The dynamic responses of aeroelastic models based on CZ-2 and Saturn IB under ground wind load are calculated. The results are in good agreement with the measured responses.
按照空气动力弹性相似准则，设计制作了某高压输电线路终端塔全塔气动弹性模型，并按响应相似原则模拟了柔性输电导线；
An aeroelastic model for a UHV power transmission tower and its conductors was designed according to the law of similarity and tested in an atmospheric boundary layer wind tunnel.
建立了大型水平轴风轮转子／塔架耦合系统的气动弹性模型，推导了转子／塔架耦合系统周期系数运动方程，给出了气动弹性稳定性分析方法。
The vibration modal analysis method and the influent factors of the natural frequency of the rotating rotor of horizontal axis wind turbine rotor blades were presented.
研究了机翼气动弹性系统的不确定性建模及其模型确认问题。
The problems of uncertainty modeling and model validation of a wing aeroelastic system are investigated.
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.
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.
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.
通过建立带受控振荡附翼的新概念旋翼气动弹性分析模型，研究了采用受控振荡附翼的直升机旋翼气动弹性特性及其在降低旋翼振动载荷方面的有效性。
The aeroelastic analysis of a helicopter rotor blade with the controlled oscillating trailing edge flap is presented by building an aeroelastic model of the new concept rotor blade.
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.
采用多项式迟滞非线性模型建立二元机翼气动弹性运动方程，并用数值积分法进行求解。
The dynamical equation of a two-dimensional airfoil with polynomial hysteresis nonlinearity in pitch is solved using Runge-Kutta time marching integration.
采用多项式迟滞非线性模型建立二元机翼气动弹性运动方程，并用数值积分法进行求解。
The dynamical equation of a two-dimensional airfoil with polynomial hysteresis nonlinearity in pitch is solved using Runge-Kutta time marching integration.
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