翼载荷–飞行载重与机翼面积之比，由飞行员总重量除以滑翔机翼面积确定，滑翔机和所有装备都在飞行中承载。
WING LOADING – ratio of wing area to weight carried in flight. Determined by dividing glider's total wing area by the combined weight of pilot, glider and all gear that will be carried in flight.
起初给扑翼机接上一个直流电源之后，他们发现这个装置的有效载荷为1.5g，这大概可以勉强提起飞行所需的电池。
Having initially connected the ornithopter using a DC power source, they realized that the device could lift 1.5 grams of payload, which was roughly the mass of the batteries required for flight.
在实验中应用负载模拟器产生一种类似真实气流阻力的载荷，施加于弹翼（尾翼），使其能在与展开过程中受力相同的状态下工作。
A kind of load like real airstream is produced by load simulator in experiment , which is put on missile's wings to make them work on the same force situation as in the real spread process .
使用有限体积法计算了飞行时的气动载荷，分析了前缘切口和翼肋开孔对压强分布的影响；
The finite volume method was used to compute the aerodynamic load, and the effect of leading-edge cut and ribs on the pressure distribution was analyzed simultaneously.
本文介绍了直11型直升机旋翼系统动部件飞行载荷测量技术及方案。
This text introduces test technology solutions of Z11 flight load test of rotor system dynamic components.
论文结合实际的工程项目，以某型号直升机旋翼气动载荷模拟为研究内容，对加载系统的组成、系统数学模型进行分析和研究。
In this thesis, the aerodynamic load simulation of one type of helicopter airscrew is studied, and the system's structure and its mathematic model are analyzed.
建立由欧拉角所确定的扑翼飞行器的载荷计算方法和步骤，揭示出扑翼飞行器通过扑翼运动同时产生升力、推力的机理。
The evaluation methods and step of the loading for the FMAV are set up so that these Euler angles can be specified to provide wing motions that generate the lift and propulsion for the vehicle.
直升机旋翼系统动部件飞行载荷测量是全机飞行载荷测量的关键，也是直升机寿命可靠性工作的基础。
Helicopter flight load test of rotor system dynamic components is the key part of flight load test of the whole aircraft, and is also the basis of helicopter life reliability calculations.
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.
研究结果表明：旋翼的拉力大约增加4%，旋翼的下洗载荷相当于整个旋翼拉力的10%左右。
The results of research show that the rotor thrust increase 4% and the download force on the wing can be as large as 10 percent of the total rotor thrust.
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.
桨叶变距拉杆操纵载荷是旋翼设计的重要参数之一。
The pitch link loads of blade is one of the most important parameters in rotor design.
本文对翼尖小翼的飞行试验结果进行了分析，试图说明它对飞机的气动载荷、操稳特性及飞行性能的影响。
An analysis of flight test results was conducted to explain the effects of winglets on aerodynamic load, control-stability and performances.
本文对翼尖小翼的飞行试验结果进行了分析，试图说明它对飞机的气动载荷、操稳特性及飞行性能的影响。
An analysis of flight test results was conducted to explain the effects of winglets on aerodynamic load, control-stability and performances.
应用推荐