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Some problems of flight vehicle control that date back to the 1950s and gave rise to the theory of adaptive control and, in the 1960s and 1970s, selfadjusting automatic pilots were discussed.


Effects of the NOinducing β1adrenoblocker nebivolol on the blood rheology and lipid profile were studied in pilots regularly exposed to factors of flying work contributing to the development of endotheliocyte dysfunction.


Prognostic value of studying personality traits of civil aviation pilots


The analysis of psychological features in pilots with a history of attempted suicide showed a neurotic type of maladaptation formed on the basis of the domination of hyposthenic traits in the personality structure.


By using a few pilots in every OFDM symbol, both channel estimation and multiuser detection can be simultaneously obtained by iteration.

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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... 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 pilot644彩的新版网站induced oscillation are presented. Some primary influence factors, especially the effect of bobweight in control systems are discussed.  jiashiyuanyoufazhendangwentidefenxi,yibantongguomonishiyanhuofeixingshiyanjinxing。danweileshejijisuandexuyao,benwencankaoyouguanziliao,tichuliangzhonglilunfenxifangfa,jipinlvfahegenguijifa。 wenzhongshouxianjichufeijidezongxiangyundongfangcheng、zhulijifeizhulicaozongxitongfangchengyijiyouguanchuandihanshu,ranhougenjufeijiyucaozongxitongzuhedebihuandonglixuemoxing,jisuanduopianjiaoduiganlishurudepinlvfanyinghuohuizhigenguijiquxian,congerkeyifenxifeijideyoufazhendangqushi。 ciwai,haijieshaolejizhongzongxiangjiashiyuanyoufazhendangdejianhuapanju。bingduizhuyaoyingxiangyinsu,tebieshiduicaozongxitongpeizhongdeyingxiangjinxingletaolun。  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 pilot644彩的新版网站controlairframe 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... 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 pilot644彩的新版网站airplane system(see Fig. 7).  benwengenjupiowentiyanjiudexuyao,kaolvdaocaozongxitongfeixianxing(jianxihemocadeng)duipiowentiyingxiangdeyanzhongxing,tuidaolebaokuofeixianxinghuanjiezaineide,jiashiyuancaozongxitongfeijibentizuhexitongdezongxiangdongtaijiegoutu,bingyongdmj3adianzimonijisuanji,yimoujianjijidikongdasuduzhengchangzhuangtai(libeichuyuxiaobei)heguzhangzhuangtai(libeichuyudabei)weilijinxinglemonijisuan。jisuanjieguoyufeixingshijianshiyizhide。congerchubushuomingzuozhetichudejiegoutu(jipiojisuanfangfa)jishikexinde,yeshijuyoushijifenxishiyongjiazhide。  Cockpit temperature condition,is one of common and important factors which have influence on pilot's efficiency.A mathematical model of the cockpit temperature control system(CTCS)has been established on the basis of theoretical analysis and experimental data.According to the theory of automatic control the dynamic and static characteristics of CTCS have been calculated and simulated by means of an electronic computer.The effects of each parameter on the dynamic characteristics of CTCS have been studied... Cockpit temperature condition,is one of common and important factors which have influence on pilot's efficiency.A mathematical model of the cockpit temperature control system(CTCS)has been established on the basis of theoretical analysis and experimental data.According to the theory of automatic control the dynamic and static characteristics of CTCS have been calculated and simulated by means of an electronic computer.The effects of each parameter on the dynamic characteristics of CTCS have been studied systematically,and a quite good combination of parameters is provided.Finally,improvement of CTCS has been investigated and the results of calculation and analysis are presented.  644彩的新版网站zuocangwenduzhuangtaishiyingxiangfeixingyuangongzuoxiaolvdejingchangxinghezhuyaoyinsuzhiyi。woguomuqianyanzhiheshiyongdedaduoshufeiji,zuocangwendudongtaixingnengcha。benwenzaililunfenxiheshiyandejichushangjianlilezuocangwenkongxitongdeshuxuemoxing;jiezhudianzijisuanjibingyunyongzidongkongzhililunjisuanhemonilewenkongxitongdedongjingtaitexing;xitongdifenxilegecanshuduixitongdongtaixingnengdeyingxiang,bingjichuyizujiaohaodecanshuzuhe;tantaolexitongdegaijinfanganbingjichujisuanhefenxijieguo。   << 更多相关文摘 
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