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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 multiburner (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 MTDFGD tests, it can be concluded that in the MTDFGD reactor, the sulfate reaction of sorbent particles is generally kinetically controlled.

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 The analysis of the pilotinduced 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 rootlocus methods.At first, the equation of the airplane longitudinal motion, the equation of the control system motion with fullpower or nopower, and the related transfer functions are given in this paper.And then, based on... The analysis of the pilotinduced 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 rootlocus methods.At first, the equation of the airplane longitudinal motion, the equation of the control system motion with fullpower or nopower, and the related transfer functions are given in this paper.And then, based on the closedlrop 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 rootlocus is plotted. Thus, the tendency of the pilotinduced oscillation may be analylized.In addition, some simplified criterions of the longitudinal pilotinduced 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(PilotInduced 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 pilotcontrolairframe with nonlinearity have been derived, and a new method which further approa 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(PilotInduced 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 pilotcontrolairframe with nonlinearity have been derived, and a new method which further approa ches to the actual case has been provided for studying PIO problem. Moreover computations have been carried out on a DMJ3A 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 pratical 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 pilotairplane system, different pilot's transfer functions have been adopted to compute the pilotairplane system on DMJ3A analog computer. The results obtained prove that the mathematical model of pilot exerts a great influence on pilotairplane 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DMJ3A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。   << 更多相关文摘 
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