1) dynamic derivative
动导数
1.
Investigation on contain of the large amplitude test to the general dynamic derivative test;
大振幅实验对常规动导数实验包容性研究
2.
These values of dynamic derivatives can not be obtained from theoretical calculations , it must be obtained from wind tunnel tests .
此系统采用强迫振动法,利用正弦发生器,使模型产生单自由度的滚转、偏航、俯仰、升沉或平移振动,进而求得模型在各种姿态下的动导数,此数据可为研究飞行器在大攻角状态下的动态特性提供可靠的依据。
3.
On the basis of the mathematical model, the dynamic derivative of the aircraft at the different angles of the tailplane was analyzed using the technique of dynamic derivative simulation.
在非定常建模的基础上 ,采用动导数仿真 ,分析了不同平尾偏角时的动导数 ,结果表明 ,水平尾翼偏角主要对零动态阻尼所对应迎角有较大影响 ,随着舵偏角的增大 ,该迎角减
2) dynamic derivatives
动导数
1.
The influences of time lag dynamic derivatives on the evaluation of the spin time history of a modified airplane;
某改型飞机时差动导数对尾旋时间历程估算的影响
2.
The dynamic derivatives conception is used as the index for the vehicle stability,but it is looked as the function of angle of attack and Mach number to induced nonlinear characteristics.
采用自由振荡法数值模拟了平头、钝头外形的超声速俯仰振荡时间历程,并应用奇异分解线性最小二乘法辨识稳定性导数,得到动导数随马赫数和攻角非线性变化的规律。
3.
A high efficient computational method for supersonic/hypersonic dynamic derivatives is developed.
在此基础上进一步发展了一种适合于超音速、高超音速大迎角状态的飞行器动导数计算方法和程序。
3) dynamic stability derivative
动导数
1.
The wind tunnel test technique for dynamic stability derivatives of the model free to tumble at hypersonic speeds has been developed to meet the urgent needs for dynamic derivative measurements of aerospace vehicles at angles of attack of 0°～360° and for mechanism study of limit cycle oscillation phenomenon.
高超声速风洞模型自由翻滚动导数试验技术是为满足航空航天飞行器 0°～ 360°全攻角范围内的动导数测量及产生极限环振动现象的研究之急需而研制。
2.
In this paper,the test mechanism of dynamic stability derivative with angle of attack up to 30° and its measuring system are presented together with typical test results of a Standard Dynamic Model(SDM) in 1.
２ｍ风洞攻角达３０°的动导数试验装置与测量系统以及在１。
3.
The test mechanism of dynamic stability derivative with high angles of attack and its measuring system are presented together with typical test results of a Standard Dynamic Model(SDM) in 1.
２ｍ风洞大攻角的动导数试验装置与测量系统以及在１。
4) Aerodynamic derivative
气动导数
1.
The influence of aerodynamic force matrix on critical flutter state with aerodynamic derivatives of four different sections was studied.
采用集中气动力矩阵和一致气动力矩阵2种不同形式的气动力矩阵,并利用4种不同截面的气动导数研究了气动力矩阵对颤振临界状态的影响;采用理想平板的气动导数研究了各气动导数对颤振临界状态的影响。
2.
Aiming at improving the efficiency of wind tunnel test, we study the influence of aerodynamic derivatives C mδh , C mq , C mα and zα on the longitudinal dynamic characteristics of an airplane with a modern control system.
采用等效系统方法研究在失速迎角前大迎角区气动导数 Cmδh、Cmq、Cmα及 Czα 改变时对具有现代控制系统的战斗机纵向动态特性的影响。
5) flutter derivative
气动导数
1.
An improved stochastic subspace identification method for flutter derivatives of bridge decks
桥梁断面气动导数识别的改进随机子空间法
2.
Inter-relationships among flutter derivatives of thin plat model
薄平板模型气动导数之间的关系
3.
Effects of the asymmetry of equivalent stiffness and damping matrices on the identification of flutter derivatives of bridge deck are investigated by a series numerical simulation.
针对桥梁结构节段模型风洞测振试验中因风的作用而导致的系统刚度矩阵和阻尼矩阵的非对称性可能影响识别结果这一问题,利用状态空间法仿真薄平板模型在均匀风场中的自由衰减响应和紊流场中的抖振响应,分别采用特征实现算法(ERA)和随机子空间法(SSI),识别出均匀流场和紊流风场中的理想薄平板模型气动导数。
6) aerodynamic derivatives
气动导数
1.
Identification of aerodynamic derivatives for bridge sections by forced oscillation method;
强迫振动法提取桥梁气动导数研究
2.
Identification of aerodynamic derivatives for bridge sections by LSCE method
利用LSCE方法识别桥梁气动导数研究
3.
Numerical simulations for aerodynamic derivatives of trestle bridge deck
高架栈桥断面气动导数的数值识别
补充资料：因水火风动故地动
【因水火风动故地动】
经云：此阎浮提地，南北阔二万一千由旬，东西阔七千由旬，厚六万八千由旬。地下有水，厚八万四千由旬。水下有火，厚八万四千由旬。火下有风，厚六万八千由旬。风下有金刚轮，过去诸佛舍利，咸在其中。或有时大风忽动，火亦随动。火既动已，水复随动。水既动已，地即随动。故云因水火风动故地动。（梵语阎浮提，华言胜金洲。梵语由旬，华言限量，或四十里，或六十、八十里也。）
经云：此阎浮提地，南北阔二万一千由旬，东西阔七千由旬，厚六万八千由旬。地下有水，厚八万四千由旬。水下有火，厚八万四千由旬。火下有风，厚六万八千由旬。风下有金刚轮，过去诸佛舍利，咸在其中。或有时大风忽动，火亦随动。火既动已，水复随动。水既动已，地即随动。故云因水火风动故地动。（梵语阎浮提，华言胜金洲。梵语由旬，华言限量，或四十里，或六十、八十里也。）
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条