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aircraft systems
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  飞机系统
     The CAI course ware of the aircraft hydraulic system was exploited based on VB6.0 platform and applied to the teaching and experimental teaching of the core specialized course—Aircraft Systems. It has achieved good results.
     基于VB6.0平台开发了飞机液压系统CAI课件,并运用于专业核心课程《飞机系统》的教学与实验教学,达到了良好的效果。
短句来源
     O-rings are widely used for sealing in aircraft systems. Strict quality control in O-ring production process is a criticle factor for implementing the sealing safety in aircraft systems.
     飞机各系统的密封性主要是靠橡胶O形圈来保证的,因此,严格控制橡胶O形圈的质量是实现 飞机系统密封安全的关键。
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     This thesis is a survey of Civil Aviation English, an ESP (English for Specific Purpose) English, especially with the highlight on the lexical characteristics of the professional language used in the two major aircraft systems, Boeing and Airbus.
     本论文对专门用途英语 (ESP) ——民航英语进行研究, 特别是对波音和空客飞机系统描述的专业语言进行词汇特征的研究。
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     MAINTENANCE REFORM FOR HOME-MADE CIVILIAN AIRCRAFT SYSTEMS AND EQUIPMENTS
     国产民用飞机系统和成品的维修改革
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     As aircraft systems become increasingly complex and the radio frequency spectra becomes more extensive,it is necessary to adopte a new approach to analysis of electromagnetic interference (EMI) in aircraft.
     由于飞机系统日趋复杂,使用的无线电频谱越来越宽,对机上电磁干扰的分析必须采用新的方 法。
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  “aircraft systems”译为未确定词的双语例句
     APPLICATION OF ADAPTIVE CONTROL TO AIRCRAFT SYSTEMS
     自适应控制在飞机控制中的应用
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     MODEL FOR ASSESSING OPERATIONAL RELIABILITY OF REPAIRABLE AIRCRAFT SYSTEMS AND ITS APPLICATION
     航空机载可修产品外场可靠性评估模型及其应用
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     Technology of radar absorbing materials (RAM) is one of the important stealth technologies,and widely applied in stealth weapons,especially stealth aircraft systems.
     雷达吸波材料(RAM) 技术是隐身技术中的重要技术之一,并且在隐身武器,尤其是隐身飞行器系统设计中得到广泛应用。
短句来源
     The technology of radarwave absorbing material (RAM) is one of the most important stealthy technologies,and is widely applied in stealthy weapon,especially in stealthy aircraft systems.
     雷达吸波材料 ( RAM)技术是隐身技术中的重要技术之一 ,并且在隐身武器 ,尤其是隐身飞行器系统设计中得到广泛应用。
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     This paper describes results of reliability verification for a ceratin typ e of aircraft for initial field verification in China,it also gives check and a nalysis on the basic reliabilit y of aircraft systems and main airborne equipmen t,points out the problems a vailable and puts forward the solutions to them.
     介绍了国内首次参与外场验证的某型飞机的可靠性验证情况,对飞机各系统和主要机载设备的基本可靠性进行了考核与分析,指出了存在的问题。
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  相似匹配句对
     APPLICATION OF ADAPTIVE CONTROL TO AIRCRAFT SYSTEMS
     自适应控制在飞机控制中的应用
短句来源
     Aircraft Security Enhancement Systems of Airbus
     加强飞机安全保障——空中客车增强型驾驶舱门及其他相关安全系统简介
短句来源
     systems such as n(?)
     系统与n(?)
短句来源
     CAM systems.
     CAM系统间彼此交换产品数据提供了基础。
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     AIRCRAFT MAINTENANCE
     飞机维修
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  aircraft systems
Unfortunately, most models of aircraft systems typically describe only the linear dynamics.
      
We've got high-quality hyperspectral data now with aircraft systems, and global coverage from hyperspectral satellite systems is on the way.
      
Unfortunately, most models of aircraft systems typically describe only the linear dynamics.
      
Verified functionality of unmodified aircraft systems and partial verification of initial aircraft modifications to include performance of the BMC4I.
      
The latter two configurations would be applicable to aircraft systems, while water could be used for ground-based machines.
      
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Aerodynamic coefficient identification for time-varying aircraft system has been studied. Usually, the time-varying system identification is quite difficult. On the basis of practical measurement in flight tests and by analyzing trend of the coefficients in aircraft time-varying differential equations, it is possible to transform the individual time-varying coefficient into a known function multi- plied by an unknown constant. These unknown constants are referred to as undefined coefficients....

Aerodynamic coefficient identification for time-varying aircraft system has been studied. Usually, the time-varying system identification is quite difficult. On the basis of practical measurement in flight tests and by analyzing trend of the coefficients in aircraft time-varying differential equations, it is possible to transform the individual time-varying coefficient into a known function multi- plied by an unknown constant. These unknown constants are referred to as undefined coefficients. With the aid of the Newton-Raphson method extended to the time-varying coefficient differential equations the undefined coefficients can be evaluated by iteration calculation. In this way the complicated time-varying aircraft identification can be carried out.In order to verify this calculation the aerodynamic coefficients of an aircraft have been evaluated by the data taken from one of its unsteady flight, and the reliability of aerodynamic coefficients obtained from this identification has been discussed. The calculation results matched very well the test data and made a contribution to the improvement of aircraft fight tests.

本文研究了变系数飞行器系统气动系数的辨识算法。变系数系统的辨识计算通常是非常困难的。本文依据飞行试验中实际测量,通过对飞行器变系数微分方程组中系数变化趋势的分析,转方程中变系数为一个变化规律已知的函数与未知常数的乘积,把这些未知常数当作待定系数,然后推广Newton-Ra-phson法到变系数微分方程组中,通过迭代法求这些待定系数,这样就使得复杂的变系数飞行器系统的辨识计算得以实现。为了证明这种算法的有效性,本文从飞行器的一次不稳定飞行的测量数据,计算了该飞行器的气动系数,并讨论了辨识计算所得气动系数的可信度,计算结果与实际符合较好,在改进飞行器的飞行试验中起了一定作用。

An aero-engine can be regarded as a subsystem of the aircraft system. It is obvious that engine performances, weight and dimensions have a strong effect on the aircraft flight performances. For a given flight mission, the optimal engine scheme must be able to meet the flight requirements with the greatest possibility. From the viewpoint of system engineering, a method for integrated selection of the optimal engine cycle parameters and the control scheme is proposed, which takes the matching...

An aero-engine can be regarded as a subsystem of the aircraft system. It is obvious that engine performances, weight and dimensions have a strong effect on the aircraft flight performances. For a given flight mission, the optimal engine scheme must be able to meet the flight requirements with the greatest possibility. From the viewpoint of system engineering, a method for integrated selection of the optimal engine cycle parameters and the control scheme is proposed, which takes the matching and interaction between the engine and the aircraft. A rapid method for predicting turbojet or turbofan engine off-design performances was adopted and an empirical formula estimating the engine weight was developed.An optimization of an augmented engine scheme meeting the requirements of a modification has been accomplished as an example. The results show that the optimum cycle parameters and the control scheme are quite different if the mission, the requirements of modification or the technical constraints are varied. Therefore, the integrated selection of engine cycle parameters is of great importance.

航空发动机是飞机的动力装置,它的性能、重量、尺寸都对飞机性能有显著影响。本文从系统工程的观点出发,综合考虑飞机、发动机性能的相互影响和匹配,提出了以最好地满足飞机飞行任务为目标,选择发动机最佳循环参数和调节计划的一体化方法。 本文的应用实例是歼击机动力改型时优选加力发动机的最佳设计方案。计算结果表明:飞机飞行任务不同、改型要求不同、约束条件不同,发动机最佳方案的类型、循环参数和调节计划也完全不同。因此,一体化选择方法具有重要实际意义。

The effects of external combined resistance (total resistive value,3-30 Cm H2O·L-1·S) on respiratory flow rate,mask cavity pre sure swing (p) and respiratory discomfort were studied in 114 pilots unde- light physical loading conditions ( 250 Kg·m·min-1).The experimental data of 17 physiological and psychophysical variables were analysed by correlation,stepwise regression and probit analysis.The results showed that p or extra respira-tory work per unit ventilation ( W/L ) might be selected as an objective index...

The effects of external combined resistance (total resistive value,3-30 Cm H2O·L-1·S) on respiratory flow rate,mask cavity pre sure swing (p) and respiratory discomfort were studied in 114 pilots unde- light physical loading conditions ( 250 Kg·m·min-1).The experimental data of 17 physiological and psychophysical variables were analysed by correlation,stepwise regression and probit analysis.The results showed that p or extra respira-tory work per unit ventilation ( W/L ) might be selected as an objective index for respiratory discomfort,with p being more applicable in practical work.The probit analysis reveals that 90% of pilots breathing through aircraft oxygen system should experience no respiratory discomfort,if the p does not exceed 6.1 Cm H2O,or W/L not exceed 0.047 Kg·m·L-1 and that 90% should experience a lesser than mild degree of discomfort,if the P does not exceed 7,9 Cm H2O,or W/L not exceed 0.061 Kg·m·L-1 The significance of our findings for revising current physiological standard of aircraft system is discussed.

以114名飞行人员为被试者,观察了在轻度体力负荷(250kg·m·min~(-1))下,外加呼吸阻力(3~30CmH_2O·L~(-1)·S)对呼吸气体流率和面罩腔压力变化以及主观感觉的影响。采用相关分析、逐步回归分析方法,筛选出能反映阻力影响的客观生理指标,并以概率单位分析方法确定对外加阻力的容许水平。结果表明:面罩腔压力波动幅度((?))和每L通气所需的额外呼吸动(W/L),均可作为反映呼吸不适感觉程度的客观生理指标;但以前者更为适用。如果(?)不超过6.1CmH_2O,或W/L不超过0.047kg·m·L~(-1),则90%的人将不会产生呼吸不适感;如果(?)不超过7.9CmH_2O,或W/L不超过0.061kg·m·L~(-1),则90%的人将只可能产生中等以下程度的不适感。文中还就航空供氧装备阻力标准修订工作进行了讨论。

 
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