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1)  glottal excitation
声门激励
2)  acoustic exciation
声激励(声)
3)  ultrasonic irradiation
超声激励
1.
A round short tube membrane module with a dual-direction inflow and the ultrasonic irradiation technology is adopted to increase flux of air-gap membrane distillation of tap water and dilute saltwater.
采用双向入流的圆形短管膜组件,并将超声激励技术用于膜蒸馏系统,以提高空气隙膜蒸馏通量。
2.
Factors affecting the membrane flux were studied through the experiment made on a system of ultrasonic irradiation air-gap membrane distillation(AGMD).
通过在超声激励气隙式膜蒸馏系统上进行实验,研究了膜蒸馏通量的影响因素,结果表明:超声激励会使膜通量显著增大,最大膜通量达到110kg/(m2·h);提高料液流量可增大膜通量;减小间隙、增大温差,膜通量增加;随着盐溶液浓度增大,膜通量减小。
4)  ultrasonic excitation
超声激励
1.
The rotational two-degree freedom dynamics model of gear-lapping system of a spiral bevel gear with single backlash was established by considering ultrasonic excitation and transmission error excitation.
在综合考虑超声激励和齿面几何传动误差激励的情况下,建立了有间隙的两自由度周向振动的弧齿锥齿轮研齿动力学模型,得到了齿面间动态研磨力的计算公式。
5)  sound excitation
声激励
1.
Cavity flows both with and without sound excitation are studied by solving the 2 D time dependent Reynolds averaged Navier Stokes equations using explicit predictor corrector difference algorithm of Mac Cormack.
采用显式MacCorma-ck二步预估校正有限差分格式,求解二维雷诺平均非定常Navier-Stokes方程;并用Cebeci-Smith代数紊流模型作适当修正来模拟紊流效应,对有、无前缘声激励两种情况的空腔流场作了数值模拟,计算的振荡频率及振荡幅值都与实验结果基本符合,并且较好地模拟出了声激励对流场的影响。
2.
The flow induced oscillation in a cavity exposed to external high speed flow and its suppression by means of sound excitation at the leading edge of the cavity are experimentally studied.
实验研究了矩形空腔在外部高速气流作用下诱导的空腔内流动振荡问题,以及从空腔前缘加入纯音声激励以抑制空腔内流动振荡的技术。
6)  acoustic excitation
声激励
1.
An investigation on the effect of the acoustic excitation on flow asymmetry over a slender revolution body at high angles of attack in compressible flows;
可压缩流中声激励对细长体大迎角流动非对称性的影响研究
2.
Application of support vector machine(SVM) on aircraft structure stress analysis subjected to acoustic excitation;
支持向量机在航空结构声激励应力分析中的应用
3.
By employing regression analysis, the simulation models of total vibration acceleration and total stresses with respect to total sound pressure as well as the simulation models of total stresses with respect to total vibration acceleration of an aircraft flap under acoustic excitation were given.
利用回归分析方法,建立声激励下飞机襟翼振动总加速度和总应力对总声压的仿真模型,及总应力对振动总加速度的仿真模型。
补充资料:声门
1.两片声带当中的开口。声带静止不发音时呈V字形。
说明:补充资料仅用于学习参考,请勿用于其它任何用途。
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