飞机机翼挂装翼尖导弹对机翼结构设计和结构分析提出了诸多全新课题，如结构的振动响应和气动弹性动响应。
Missile carrying on the wing tip causes the wing structure design and analysis to face many challenges, such as structural vibration response and aeroelastic response.
由于太阳能电池翼的大跨度，低刚度特点，加之太空中阻尼较弱，使得电池翼极易产生低频非线性的持续振动。
Due to the large span, small elasticity and feebleness damp in aerospace, the solar panel easily generates non-linear vibration with low frequency.
分析结果表明：操纵系统对旋翼桨叶扭转振动固有特性的影响是一个值得注意的问题。
The results obtained by these analyses show that the problem of the influence of control system on modal characteristics of the rotor blades torsional vibration is noticeable.
介绍了某直升机旋翼试验台的振动数据采集和预处理系统的设计和组成。
The design and the construction of a data acquisition and preprocessing system for a helicopter rotor test rig are described.
试验证明了PIV技术可以应用于被动振动非定常复杂流场的测量中，并对两维翼流体旋涡诱发振动响应进行了分析。
The experiment shows that the PIV technique can be utilized to measure the unsteady complex flow of passive vibration, and analyses the vortex-induced vibration.
提出对前向飞行的水平旋翼的振动进行补偿，可以大幅度提高合成距离像的质量。
And it is proposed that much improvement of the range profiles can be achieved by using the vibration compensation of the main rotor of the helicopter in forward flight.
当航速为零时，则是通过鳍在水平位置附近的上下振动来产生升力，与鸟类和昆虫的扑翼飞行相似。
When the speed of AUV is zero or low speed, lift is produced by the vibration of fin stabilizer at the horizontal position, which is similar to the flapping wing flight of insects and birds.
针对带有舵翼的水下航行器尾部结构模型，研究舵翼对水下航行器尾部的振动及声辐射的影响。
The vibration and sound radiation behaviors of the stern of submarine with rudder and vane are studied.
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.
连接架轴向载荷可以大幅提高太阳翼的侧摆振动频率；
The axial load in the tripod of the solar array can increase the swaying frequency largely.
同时作线性处理，计算一个简单模型的固有频率，为旋翼与机身藕合系统的振动特性和响应分析提供一种新模型。
The equations of couple rotor fuselage are linearized . An example is given and this paper provides a new model for analysis of coupled rotor fuselage dynamics.
同时作线性处理，计算一个简单模型的固有频率，为旋翼与机身藕合系统的振动特性和响应分析提供一种新模型。
The equations of couple rotor fuselage are linearized . An example is given and this paper provides a new model for analysis of coupled rotor fuselage dynamics.
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