查询词典 transonic aerodynamics

In the computation of aerodynamic forces, the present work is based on the work of Morino et al., but the following aspects are improved:(1) In computing the steady transonic aerodynamic load, the steady transonic nonlinear integral equation is solved by relaxation-iteration method in this thesis, instead of solving the time dependent transonic nonlinear integral equation, so that the computing time is saved greatly;(2) The influence coeifficients represented by volume integral are transformed to surface integral by using the Gaussian Theorem, so the analytical form of these coeifficients can be obtained and this leads to be more convenient to analyse and compile computer program;(3) The shock capturing method is used in every time step in present work, no shock moving term is added in the integral equation, so that it is more convenient and simpler to treat.

在气动力计算方面，本文基于Morino等人的工作，作了如下几方面的改进：（1）在计算定常跨音速流场（作为非定常绕流计算的初场）时，本文采用松驰迭代法直接求解跨音速定常非线性积分方程，而不是采用时间相关法求解非定常非线性积分方程，这样大大节省了计算机时；（2）将以体积分形式出现的影响系数化为面积分，并获得解析公式，这样便于分析和编写程序；（3）对运动的激波，本文通过在每一个时间步长上采用激波捕捉法而得到，而不是在积分方程中附加激波运动项，因而处理起来简单方便得多。

With the design method described and design standard proposed in this thesis, a transonic NLF wing has been designed. Calculation shows that this NLF wing has, even in case of full turbulent boundary layer flow, good transonic aerodynamic characteristics.

本文结合民机预研项目，根据后掠机翼层流流动的特点和已有的经验提出了自然层流机翼的设计准则，用本文的三维机翼设计方法设计了一个跨音速自然层流机翼。

Through deduction of hydraulics principle and calculation of aerodynamics and hydraulics,this paper defined the principle of intake equipment and the calculating method of water dynamics and aerodynamics,and hereby designed siphonic intake equipment and took a full scale experience.

通过对滗水器的水力学原理推证，以及对气体动力学和水力学计算，确定了滗水器的原理及水、气动力学计算方法，并据此设计了虹吸式滗水器，同时经生产性试验证实，其效果良好

To overcome the bad effect resulting from the nonlinearity time-variability and uncertainty on autopilot system performance during the motion process of aerodynamics missile, and to further improve the flight quality of missile, the autopilot system and used control method are researched. Firstly the integrant structure of system is discussed; then baaed un introducing the traditional PID method, controllers for missile attitude motion are designed respectively using fuzzy self-turning PID method and neural network self-adaptive PID method; at last a simulation experiment is finished. By comparing the simulation results that the designed controllers have good qualities is showed, and the feasibility and validity of applying fuzzy control and neural network into automatic control of aerodynamics missile is confirmed, and the base that other nonlinear control theory can be combined with the traditional control for missile to further improve the performance of missile control system is established.

为了克服飞航导弹运动过程中的非线性、时变性和不确定性对自动驾驶仪系统性能的不良影响，进一步提高导弹的飞行质量，对自动驾驶仪系统及其采用的控制方案进行了研究；首先对系统的整体结构进行了分析，然后在介绍经典PID方案的基础上，分别采用模糊自调整PID方案和神经网络自适应PID方案设计了导弹姿态运动控制器，最后进行了仿真实验；仿真结果的对比展示了所设计控制器良好的品质，验证了将模糊控制和神经网络应用于飞航导弹自动控制中的可行性和有效性，为其它非线性控制理论与导弹传统控制相结合以进一步提高导弹控制系统的性能奠定了基础。

The fiber are successfully used in the practical noise control. The model of aerodynamics in the course of the intermittence exhaust is simplified into exhaust problem of two stage series cylinder. Digital calculation program which can really imitate aerodynamics characteristics in the exhaust process is established. A simple formula which can be used for calculating the volume of the silencer expansion chamber is established.

作者指出间歇性排气过程的空气动力模型可简化为两级气缸串联的排气问题，编制的数值计算程序真实地模拟了排气过程中的空气动力学特性，建立了消声器膨胀消声室体积大小计算的表达式。

So in this paper, the micro-turbofan engine, which has several ten kilogram thrust level, moderate difficulty, low pressure ratio and single rotor, is studied in three ways which contain overall aerodynamics arrangement analysis and structure feasibility research, optimizing of aerothermodynamics circulation, overall aerodynamics design ane flying performance simulation.

本文对于数十公斤推力量级的、工程技术难度适中的、低增压比的一种单叶轮微型涡扇发动机，进行了总体气动布局分析和结构可行性研究，热力循环优化设计，总体气动设计及飞行特性模拟这三个方面的研究。

This paper deals with the numerical methods for transonic flows around airfoil and wing, and its applications.

本论文研究翼型和机翼跨音速定常流的数值方法及其应用方面的问题，主要的工作是

To adopt antiphase evaporation transonic method and high speed agitation method to prepare Semustine Magnetic Liposome, to carry out the exosyndrome with TEM, image analysis system and energy spectrometer, to test the envelopment rate of semustine in the liposome.

采用反相蒸发超声法加高速搅拌制备纳米司莫司汀磁性脂质体，用透射电镜、图像分析系统和能谱仪对其进行表征，HPLC法检验脂质体中司莫司汀的包封率。

Antiphase evaporation transonic method and high speed agitation method was adopt to prepare semustine PVP magnetic liposome.

加入聚乙烯吡咯烷酮作为磁性粒子包裹剂制备水基磁流体，采用反相蒸发超声法加高速搅拌制备司莫司汀聚乙烯吡咯烷酮磁性脂质体。

The Fe3O4 magnetic nanoparticle is a good carrier to prepare medical magnetic liposome. The adoption of antiphase evaporation transonic method and high speed agitation method can prepare nanometer Fe3O4 magnetic liposome.

Fe3O4纳米粒子是制备医用磁性脂质体的良好载体，采用反相蒸发超声法加高速搅拌可制备纳米级Fe3O4磁性脂质体。

I was up all night because I was in pain, she said.

我整夜，因为我在疼痛，她说。

A crow caws /craoks.

乌鸦叫。 51-论文网