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驾驶员
相关语句
  pilot
    THE PILOT MATHEMATICAL MODEL FOR PREDICTING AIRCRAFT HANDLING QUALITIES
    估算飞行品质用的驾驶员数学模型问题
短句来源
    INFLUENCE OF CONTROL RATE OF STICK ON PILOT INDUCED OSCILLATION
    操纵速率对驾驶员诱发振荡的影响
短句来源
    STUDY ON THE RELATIONS BETWEEN PILOT MODEL PARAMETERS AND FLYING QUALITIES
    驾驶员模型参数与飞行品质关系的研究
短句来源
    IDENTIFICATING THE PARAMETERS OF PILOT STRUCTURAL MODEL
    驾驶员结构模型参数辨识
短句来源
    A Method for Evaluating the Modelling Accuracy of Pilot
    驾驶员模型建模精度分析方法研究
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  “驾驶员”译为未确定词的双语例句
    A STUDY OF THE PILOT-ASSISTANT DISPLAY SYSTEM USING PREVIEW PREDICTIVE TECHNIQUES
    预见预测驾驶员辅助显示系统的研究
短句来源
    Comparison of Neural Network Model and Freguency Domain Quasi-Linear Model for Human Pilots
    驾驶员神经网络模型与频域拟线性模型的比较研究
短句来源
    Study on POP Simulation for the Avionics Integrated Fire Control System
    航空电子综合火控系统驾驶员操作程序(POP)仿真
短句来源
    Secondly, two maneuver control models are discussed, and control algorithms of typical maneuvers are implemented based on the models.
    建立了基于驾驶员操纵特点和矢量指向的两种机动控制方法,并利用这两种机动控制方法实现了典型空战机动的控制算法。
短句来源
    It is usefull to construct the control systems of BW-1 VSA and to predict the flight safety of BW-1 VSA.
    这些分析对于构造 BW-1的控制系统布局,预言 BW-1飞行试验安全和驾驶员应采取的对策是十分必要的.
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  pilot
In addition, the transient response was detected from the motor setup to smooth running within 10 s, 15 s, 20 s and 25 s respectively, and the characteristic of the transient flux is under pilot study.
      
Comparing the pilot results measured by previous methods, the relative error of the characteristics predicted by simulation is less than 30%.
      
With regards to the fuel cycle, a 100 t/a PWR spent fuel reprocessing pilot plant and a 500 kg/ a MOX fabrication plant are under construction.
      
The features of the opposed multi-burner (OMB) gasification technology, the method and process of the research, and the operation results of a pilot plant and demonstration plants have been introduced.
      
Through analyses of some pilot scale MTD-FGD tests, it can be concluded that in the MTD-FGD reactor, the sulfate reaction of sorbent particles is generally kinetically controlled.
      
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The analysis of the pilot-induced oscillation is carried out in general by usingthe simulated methods or flying tests. For the need of the design calculations, however, the writer through consulting the related references provides twotheoretical methods, i.e. the frequency response and root-locus methods.At first, the equation of the airplane longitudinal motion, the equation of the control system motion with full-power or no-power, and the related transfer functions are given in this paper.And then, based on...

The analysis of the pilot-induced oscillation is carried out in general by usingthe simulated methods or flying tests. For the need of the design calculations, however, the writer through consulting the related references provides twotheoretical methods, i.e. the frequency response and root-locus methods.At first, the equation of the airplane longitudinal motion, the equation of the control system motion with full-power or no-power, and the related transfer functions are given in this paper.And then, based on the closed-lrop dynamic models of the combination of the airplane and control systems, the frequency response of the elevator deflection to stick force input is calculated and the root-locus is plotted. Thus, the tendency of the pilot-induced oscillation may be analylized.In addition, some simplified criterions of the longitudinal pilot-induced oscillation are presented. Some primary influence factors, especially the effect of bobweight in control systems are discussed.

驾驶员诱发振荡问题的分析,一般通过模拟试验或飞行试验进行。但为了设计计算的需要,本文参考有关资料,提出两种理论分析方法,即频率法和根轨迹法。 文中首先给出飞机的纵向运动方程、助力及非助力操纵系统方程以及有关传递函数,然后根据飞机与操纵系统组合的闭环动力学模型,计算舵偏角对杆力输入的频率反应或绘制根轨迹曲线,从而可以分析飞机的诱发振荡趋势。 此外,还介绍了几种纵向驾驶员诱发振荡的简化判据。并对主要影响因素,特别是对操纵系统配重的影响进行了讨论。

In order to meet the needs for studying PIO(Pilot-Induced Oscillation) and take serious influence of control system nonlinearity(e. g. clearance and friction, etc. ) on PIO into account, a dynamic structure diagram (see Fig. 2) and an analog structure diagram (see Fig. 3) in longitudinal motion of pilot-control-airframe with nonlinearity have been derived, and a new method which further ap-proa ches to the actual case has been provided for studying PIO problem. Moreover computations have been carried out on...

In order to meet the needs for studying PIO(Pilot-Induced Oscillation) and take serious influence of control system nonlinearity(e. g. clearance and friction, etc. ) on PIO into account, a dynamic structure diagram (see Fig. 2) and an analog structure diagram (see Fig. 3) in longitudinal motion of pilot-control-airframe with nonlinearity have been derived, and a new method which further ap-proa ches to the actual case has been provided for studying PIO problem. Moreover computations have been carried out on a DMJ-3A analog computer for three cases as examples, i. e. the moment arm at normal state(short arm), the moment arm at trouble state(long arm), and the moment arm still at trouble state (long arm) without pilot's correction, for a fighter flying at low level and high speed. The results are shown in Fig. 4, Fig. 5 and Fig. 6. It is obvious that they coincide with the actual flight and thereby it is proved preliminarily that the structure diagram and the analog structure diagram(i. e. the computation method for PIO) proposed are not only reliable, but also of value in pra-tical analysis and use. The results obtained also demonstrate that the phenomenon of the longitudinal oscillation with big amplitude for a fighter at low level and high speed is the problem of PIO.In order to get a clear understanding of influence of pilot on the pilot-airplane system, different pilot's transfer functions have been adopted to compute the pilot-airplane system on DMJ-3A analog computer. The results obtained prove that the mathematical model of pilot exerts a great influence on pilot-airplane system(see Fig. 7).

本文根据PIO问题研究的需要,考虑到操纵系统非线性(间隙和摩擦等)对PIO问题影响的严重性,推导了包括非线性环节在内的,驾驶员-操纵系统-飞机本体组合系统的纵向动态结构图,并用DMJ-3A电子模拟计算机,以某歼击机低空大速度正常状态(力臂处于小臂)和故障状态(力臂处于大臂)为例进行了模拟计算。计算结果与飞行实践是一致的。从而初步说明作者提出的结构图(即PIO计算方法)既是可信的,也是具有实际分析使用价值的。

The longitudinal feedback coefficients of a stability augmentation system (SAS) for a sample aircraft were selected in the light of the condition that the normal acceleration response at the pilot's position approximated to zero. With the aid of references [2] and [3] the improvement in riding qualities of the airfrarne/SAS system due to the selected coefficients were evaluated. The dynamic characteristics of the airframe/SAS system were also analyzed.The results demonstrate that the riding qualities are desirable...

The longitudinal feedback coefficients of a stability augmentation system (SAS) for a sample aircraft were selected in the light of the condition that the normal acceleration response at the pilot's position approximated to zero. With the aid of references [2] and [3] the improvement in riding qualities of the airfrarne/SAS system due to the selected coefficients were evaluated. The dynamic characteristics of the airframe/SAS system were also analyzed.The results demonstrate that the riding qualities are desirable when the control anticipative parameter of the airframe/SAS, system approaches to 9.81/lx, and the operating range of the SAS is limited to the elevator displacement less than 10% of the max.displacement.It is necessary to take into account the lift due to the elevator deflection in the analysis of the dynamic characteristics of the airframe/SAS system, if the tail area is large enough in comparison with the wing area such as 0.2.

根据驾驶员位置处法向加速度反应近似为零的条件,选择了算例飞机的纵向增稳器返馈系数。按文献[2、3],估算了乘坐品质的改善情况,且分析了飞机和增稳器组合的动态特性。结果表明:当飞机和增稳器组合的操纵期望参数(CAP)值接近9.81/ι_x时,可满足乘坐品质要求。同时,增稳器的工作范围在平尾总偏角的10%以内。如果平尾的面积相对机翼面积较大,例如,则在分析飞机和增稳器组合的动态特性时,必须考虑升降舵偏转引起的升力项。

 
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