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ground test     
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  地面试验
     Based on ground test data,empirical equations of parameter calculation and error determination for liquid rocket engine are set up.
     以地面试验数据,建立了液体火箭发动机参数计算和误差确定的经验公式,在导弹飞行试验中,对发动机参数计算起到重要的作用。
短句来源
     The Intelligent System for Aeronautical Ground Test
     航空地面试验的智能系统
短句来源
     Recent Development of Aeroengine Ground Test Technologies and Our Countermeasures
     航空发动机地面试验技术的近期发展及我们的对策
短句来源
     AN INTRODUCTION TO SOFTWARE DYNAWORKS ON SPACECRAFT GROUND TEST DURATION OPTIMIZATION
     航天器地面试验时间优化软件(DYNAWORKS)的介绍
短句来源
     Application of VXI Bus in Field of the SRM Ground Test
     VXI总线系统及在固体发动机地面试验中的应用
短句来源
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  地面测试
     The Application of VXI Bus Technology to Aerospace Ground Test System
     VXI总线技术在航天地面测试系统中的应用分析
短句来源
     The Study of Methods for Designing Interface of Ground Test of Solid state Data Storage on Craft
     机载固态数据存储器地面测试接口设计方法的研究
短句来源
     In this article, the author explains that through RS, GIS and GPS core techniques, as well as ground test with synthetic investigation method, they have completed background investigation of ecological environment along Yanhe River, whose coverage is about 10 015 797 km 2, and have established 1900~2000 year ecological environment dynamics monitoring system by using ETM/TM satellite data and airborne to ground observation data.
     以遥感 (RS)、地理信息系统 (GIS)、全球定位系统 (GPS)为核心技术 ,采用 ETM/ TM卫星数据、航空机载对地观测数据 ,结合地面测试和综合调查方法 ,完成了延河流域面积 10 0 15 .797km2的生态环境本底调查 ,建立了 1990~ 2 0 0 0年的生态环境动态监测系统。
短句来源
     Compared with use the real RW in ground test, the RWESD has the characteristic of economical, controllable, undestructive and reliable, especially it can be used in different satellite ground test by change the inner parameters, it is high efficiency and low cost.
     与采用真实飞轮进行地面试验相比,飞轮电模拟器具有经济性、可控性、无破坏性、可靠性等优点,尤其是可以通过调整其内部参数改变飞轮电模拟器的输出特性,应用于不同型号卫星的地面测试中,提高飞轮电模拟器的使用效率,降低成本。
短句来源
     The integrative test system of missile based on ARINC 429 bus is composed of ground measuring and testing computer and mission computer in missile, and the software includes ground test program and test program built-in missile.
     基于ARINC429总线的导弹综合测试系统由地面测试计算机和弹上任务计算机构成,软件包括地面检测及弹上内置测试程序。
短句来源
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  地面实验
     Regulation and ground test of 100W microwave plasma thruster
     100W微波等离子推力器的调试与地面实验
短句来源
     Network System of Ground Test System for Dual-arm Free Flying Space Robot
     自由飞行空间机器人地面实验平台网络系统
短句来源
     Hardware Unit of Ground Test System for Dual-ARM Free-flying Space Robot
     自由飞行空间机器人地面实验平台硬件系统
短句来源
     To achieve real-time communication between workstations of the ground test system for dual-arm free flying space robot, simulating a dual-arm free flying space robot captures a target satellite, real-time network supervise system based on TCP/IP protocol has been developed.
     为了实现自由飞行空间机器人地面实验平台系统中各工作站之间的实时通讯 ,模拟自由飞行空间机器人操作目标卫星的过程 ,开发了基于TCP/IP协议的网络实时监控系统。
短句来源
     The ground test system for dual-arm free-flying space robot is introduced.
     介绍了双臂自由飞行空间机器人地面实验平台系统。
短句来源
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  地面试车
     The Thrust Measurement System of the Ground Test Bed of the W~2P1 Micro-turbojet Engine
     W~2P1微型涡喷发动机地面试车台推力测量系统
短句来源
     Adaptive thresholds algorithm for fault detection of liquid rocket engine in ground test
     液体火箭发动机地面试车故障检测的自适应阈值算法
短句来源
     A STATISTIC APPROACH TO FAULT DETECTIONOF LIQUID ROCKET ENGINE IN GROUND TEST
     基于数据统计的液体火箭发动机地面试车故障检测算法
短句来源
     Then, the real time fault detection and alert system for rocket engines in ground test was developed based on LabWindows/CVI.
     然后,从健康监控系统的功能和要求出发,基于LabWindows/CVI实现了发动机地面试车的实时故障检测与报警系统。
短句来源
     The thrust measurement system of the ground test bed of the W2P1 micro-turbojet engine is introduced. This system includes the ground test bed of the W2P1 engine, the thrust measarement system (thrust measuring system and thrust calibration system), the calibration equipment of hy-draulic loading and its calibration method.
     介绍了W~2P1微型涡喷发动机地面试车台推力测量系统,包括W2P1发动机试车台架,推力测量系统(推力测力系统、推力校正系统)、液压加载校准装置及其校正方法。
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  ground test
April 21, 2000 is the 30th anniversary of the first ground test of the thermionic reactor-converter of the Topaz nuclear power system, which gave Russian science and technology deserved authority and leadership.
      
During ground test and calibration, the LENA imager was found to respond to neutral atoms with energies well above its nominal energy range of 10-750?eV, up to at least 3-4?keV, owing to sputtering interactions with its conversion surface.
      
Four Landsat images taken simultaneously to the ground campaigns were processed to obtain several vegetation indexes calculated for each ground test plot.
      
When comparing the image sensor alignment parameters in the orbital test and a ground test, both values matched well.
      
A unified thermal analysis (temperature/heat flux prediction) of the sounding rocket aerothermodynamic environment is presented using flight data which are transmitted to ground test station.
      
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Y-2 is the first light helicopter of China's own designs, with initial success in flight test. It was jointly designed and developed by Nanking Aeronautical Institute, Northwest University of Engineering and Factory № 331 to meet the reguirements of reconnaissance, Patrol and CommunicationThis paper makes a brief review of its development, giving information and analysis with special emphasis on the design features, ground tests, the major dynamic problems encountered and the approaches to them,...

Y-2 is the first light helicopter of China's own designs, with initial success in flight test. It was jointly designed and developed by Nanking Aeronautical Institute, Northwest University of Engineering and Factory № 331 to meet the reguirements of reconnaissance, Patrol and CommunicationThis paper makes a brief review of its development, giving information and analysis with special emphasis on the design features, ground tests, the major dynamic problems encountered and the approaches to them, And the results of flight tests.

Y—2是我国第一架自行设计并初步试飞成功的小型直升机。它由南京航空学院、西北工业大学和国营三三一厂共同研制,预定执行侦察,巡逻和通讯联络任务。本文简要地回顾了研制过程,着重就结构设计特点、地而试验、主要动力学问题的解决和初步飞行试验结果作了简单介绍与分析。

This paper presents an analytical method for calculating the flow field and performance of supersonic ejector nozzle. The calculations involve the real sonic line at the exit of the primary nozzle, the inviseid primary flow field, the correction for viscosity effect and the pumping, and thrust characteristics.In order to bring calculated results into agreement with experimental data, the real sonic line, instead of the plane sonic line, is taken as the initial base line of calculation. The real sonic line is...

This paper presents an analytical method for calculating the flow field and performance of supersonic ejector nozzle. The calculations involve the real sonic line at the exit of the primary nozzle, the inviseid primary flow field, the correction for viscosity effect and the pumping, and thrust characteristics.In order to bring calculated results into agreement with experimental data, the real sonic line, instead of the plane sonic line, is taken as the initial base line of calculation. The real sonic line is obtained by joining the points of intersection of constant flow angle lines in the throat region with Mach lines at the lip of the primary nozzle.First, the inviscid primary flow field of the nozzle is calculated and then corrected to account for the viscosity effect. The method of correction for viscosity effect proposed in this paper replaces the original geometric coordinates of the ejector shroud with corrected geometric coordinates, which are obtained by superimposing on the original geometric coordinates the displacements of the mixed region and the boundary layer. On the basis of the corrected coordinates, the actual primary flow field and pumping performance of the nozzle are then calculated. The proposed method proves to be quite simple and accurate.Calculations were performed on a "320" digital computer, and model tests on a ground test facility. The analytical and experimental results are found to be in fairly satisfactory agreement.

本文介绍了超音速引射喷管的流场和性能的理论计算方法.它包括如下的计算:主喷管出口的真实音速线,非粘性主流流场,粘性影响的修正,抽吸特性和推力特性. 为了使计算结果更符合实验数据,采用真实音速线而不是平面音速线作为计算的初始基准线.真实音速线是由主喷管喉部区域的等角度线与从主喷管唇部发出的马赫线的交点得出的.首先,计算喷管的非粘性主流流场,然后考虑粘性修正.本文采用的粘性修正方法是用修正的外罩几何坐标代替原有的外罩几何坐标.前者是将混合区和附面层的位移厚度叠加到原有的外罩几何坐标上而得到的.按照修正过的坐标计算喷管真实流场,抽吸特性等.该修正方法相当简单而且足够准确. 计算是在数字计算机“320”上完成的,并在地面设备上做了模型实验.理论和实验结果基本一致.

In this paper, several types of inlet are designed for a certain aircraft and the results of ground tests on their models are discussed.According to the features of the aircraft inlet (side inlet, square entrance, Large L/D and structure limitation, etc.), the paper illustrates the selecting principles of parametres in respect of entrance area, throat area, lip geometry parametre, the passage near the throat, and the area distribution in subsonic diffuser. It analizes the effect of these parametres on...

In this paper, several types of inlet are designed for a certain aircraft and the results of ground tests on their models are discussed.According to the features of the aircraft inlet (side inlet, square entrance, Large L/D and structure limitation, etc.), the paper illustrates the selecting principles of parametres in respect of entrance area, throat area, lip geometry parametre, the passage near the throat, and the area distribution in subsonic diffuser. It analizes the effect of these parametres on the inlet performance. These principles also apply to transonic or subsonic inlets.It follows from the test that the best type of these inlets is the type Ⅳ, the parametres of which are as follows. Mt= 0.75, CR=1.20, a/b= 2.84 and n = 2.25. The total pressure recovery can reach 0.908 and DCeo is equal to about -0.22 on ground state. This will not only satisfy the requirements of the Spey engine which is associated with the inlet of the aircraft, but also catch up with and surpass the level of the same types of aircraft at home and abroad.

本文针对某飞机的要求,设计了几种进气道方案,并对其地面模型的试验结果作了讨论。 文章根据某飞机进气道的特点(两侧进气,近似方形进气口,进气道长度对进气道出口直径比L/D较大以及由于总体结构的限制,使进气道形成左右、上下较大的转弯等),阐述了进气道进口面积,喉道面积,唇口几何参数,喉道附近通道部分和亚音扩压段面积分布等参数的选择原则。文章还分析了上述这些参数对进气道性能的影响。本文对进气道有关设计参数所提出的设计原则对一般的跨、亚音速进气道也是适用的。 从几种方案的试验结果得出:喉道M数为0.75,唇部收缩比为1.20,内型面的椭圆长短轴比a/b=2.84,超越椭圆指数n=2.25,内通道面积分布为第Ⅳ方案的进气道性能最好。在地面起飞状态,进气道的总压恢复系数σ可达0.908,周向总压畸变指数DC_(60)为0.22左右。该指标满足了与该机进气道配用的斯贝发动机要求,并达到和超过国内外同类机种的地面性能水平。

 
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