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击中
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  hit
     The heart was hit with a rate of 5.56%.
     心脏被直接击中的机率为 5.56% ;
短句来源
     According to the result of the tests,group T was subdivided into hit right patients(group T_1) and hit wrong patients(group T_2),and BIS,the latency of Na and Pa of MLAEP and the amplitude from Na to Pa were compared.
     T组根据测试结果再分为击中目标词病人(T1组)和未击中目标词病人(T2组),作BIS与MLAEP中Na、Pa潜伏期和Na至Pa的波幅(ANa-Pa)比较。
短句来源
     Indexes which were sensitive even in SD21 included total sleepy degree of subjective assessment, reaction time of ERP behavior, latency of SW, amplitude of P300, latency of P300, hit number of LCT and amplitude of N200. And the last three ones were also sensitive to different lengths of SD.
     对SD敏感的指标有:LCT总击中数、困倦程度、ERP行为狈u试的反应时、N200的 Ap、P300的 L和 Ap及 SW的 L,其中 LCT的总击中数、N200的 Ap和 P300的 L不仅对 SD敏感,而且不同 SD时间之间有显著差异。
短句来源
     A time-to-digital converter with the multiple hit capacity is described using a ECL random access memory (RAM) E859. It is able to process up to≤128 hits per signal wire for 8 wires of the drift chamber with full scale time range 2.56μs and time resolution 10ns, which corresponds to space resolution~210μm.
     利用ECL的随机存取存贮器(RAM)E859作了一个具有多次击中能力的时间一数字变换线路. 可用于漂移室8根丝的漂移时间的读出,每根丝具有≤128次击中的能力,全量程为2.56微秒,时间分辨为10纳秒,这相应于对漂移室空间分辨的贡献~210微米.
短句来源
     To realize the hit testing of Configuration System with the uncertain model of spacial data
     参考空间数据的不确定模型实现图形系统的击中测试
短句来源
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  hitting
     HITTING PROBABILITIES OF SUPER-BROWNIAN MOTIONS WITH BRAN-CHING MECHANISM ψ(x,λ)=γ(x)λ~(1+β)
     分支特征为ψ(x,λ)=γ(x)λ~(1+β)超布朗运动的击中概率(英文)
短句来源
     In this paper, we investigate the super Brownian motions with the branching mechanism given by ψ(x,λ)=γ(x)λ 1+β (0<β≤1) and give some results of hitting probabilities of these processes.
     本文研究了分支特征为 ψ( x,λ) =γ( x) λ1+β( 0 <β≤ 1 )的超布朗运动 ,给出了这类超过程关于球内及球外区域的击中概率
短句来源
     In group T,there were 8 patients of hitting 18 target words,while 3 patients in group C(hitting) 5 target words(P<0.05).
     C组19例中有3例击中目标词5个,T组20例中有8例击中目标词16个(P<0.05)。
短句来源
     In order to identify the space heavy ions hitting loaded-seeds, the solid-state nuclear track detector (SSNTD) CR-39 was used as a part of a “sandwich” detecting system. By means of measurements of ion range R and etched rate V of CR-39, a slope (dR/dV-1) was acquired.
     为鉴别击中搭载水稻种子的空间重离子,一种固体核径迹探测器(SSNTD)CR-39被用作“三明治”式探测系统的一部分,通过测量离子在CR-39中的射程R和蚀刻率V,就可得到斜率(dR/dV-1)。
短句来源
     ① Results of inner-group analysis: In the group of MCI, the hitting rate (0.41±0.15) of target words in word free recall task was significantly higher than that of interfering words (0.31±0.12, P < 0.01), suggesting that there existed semantic priming effect in the patients with amnestic MCI as completing this task.
     ①组内分析结果:自由联想任务中的目标词击中率显著高于干扰词击中率,轻度认知损伤组眼(0.41±0.15),(0.31±0.12),P<0.01演,对照组眼(0.45±0.11),(0.33±0.10),P<0.01演,提示在完成此项任务时存在语义性启动效应;
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  “击中”译为未确定词的双语例句
     At doseranges of 0.5—2.5 Gy,the dose-survival curve was fitted to a single target model:S=exp(—D/D_0),leather dose D_0=0.515±0.014 Gy.
     初步结果表明,在0.5—2.5 Gy的剂量范围内,CHL 细胞的剂量-存活曲线符合单次击中单靶模型:存活分数 S=exp(—D/D_0),平均致死剂量D_0=0.515±0.014 Gy。
短句来源
     The mutagenetic effect curve model is S=e -λD ,and the mutagenetic curve is Y =-0 940e 1 29x , r =0 9533( r 0 01 =0 765).
     随着照射剂量的增加 ,木霉孢子存活率急剧下降 ,剂量效应曲线符合一次击中模型S =e-λD; 诱变效应方程为 :Y =-0 940e1 2 9x,r=0 953 3 (r0 0 1=0 765)。
短句来源
     The primary results show that the intrinsic time resolution of ETOF with Tyvek paper wrapping is between 70—90ps.
     实验结果显示使用Tyvek纸包装,闪烁体在安装PMT的一端有45°斜面,电子击中在TOF模块不同位置其本征时间分辨在70—90ps范围内.
短句来源
     Programmable Optical Hit-Miss Transformation and Its Application in Pattern Recognition
     可编程光学击中击不中变换及其在模式识别中的应用
短句来源
     According to Marmarou, severe closed brain injury was made by dropping 450g copper rod from a height of 1.5m, 18mm in diameter.
     按照Marmarou方法,用重450g,直径18mm的铜棒从1.5m高度自由落下击中大鼠头部,造成大鼠重型闭合性颅脑创伤。
短句来源
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  hit
Among them, the embryos of three seeds were hit at least once, and mutants with significant changes in agronomic traits were only found in later generations of these seeds.
      
In the 1960s, the researchers of Harbin Institute of Technology (HIT) attempted to do relevant research on natural language processing.
      
With more than 40-year's effort, HIT has already established three research laboratories for Chinese information processing, i.e.
      
This paper gives an introduction to the achievements on NLP in HIT.
      
For the initial conditions from this domain, the system is guaranteed to hit a trajectory with given index of exponential stability.
      
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  hitting
For minimization and maximization of the kinetic energy of a body hitting a fixed visco-elastic obstacle with the energy calculated at the instant of body detachment from the obstacle, the optimal control laws in the impact phase were obtained.
      
The method is based on the principles of quantum electrodynamics that make it possible to compute probability amplitudes of hitting the receiver by photons emitted by the source.
      
A cloud of low-velocity reflected particles formed inside the inverted cones and prevented the oncoming particles from hitting the surface of the model.
      
An electrostatic system enabling a 15-fold decrease of the cross section of an ion beam (electrostatic funnel) with a simultaneous beam reversal before hitting a detector is described.
      
Mixed volumes and the probability of hitting in convex domains for a multidimensional normal distribution
      
更多          
  roquet
Eight microsatellite loci in the Caribbean lizard, Anolis roquet
      
Anolis roquet behaviorally regulates its body temperature, but its congener A.
      
roquet and that different enzyme classes would contribute disproportionately to this interspecific difference.
      
The roquet series occupy the southern islands, as far north as Martinique, while the bimaculatus series are distributed northwards from Dominica.
      


This paper continues previous work and completes the design of the rocket's orbits which can hit the moon. In this paper, the relations between the initial conditions and the positions on the moon's sphere of influence are imperoved, based on the double two-body problem. Further, the effects of other disturbing factors (solar and planetary gravitation, drag of atmosphere etc,) on successfully hitting the moon, except lunar gravitation and first order terms of the terrestrial field of gravitation are discussed....

This paper continues previous work and completes the design of the rocket's orbits which can hit the moon. In this paper, the relations between the initial conditions and the positions on the moon's sphere of influence are imperoved, based on the double two-body problem. Further, the effects of other disturbing factors (solar and planetary gravitation, drag of atmosphere etc,) on successfully hitting the moon, except lunar gravitation and first order terms of the terrestrial field of gravitation are discussed. The results show that these factors can be neglected. In the last part, the deflections which are produced by the errors of initial values are studied, from which,the allowable maximum errors of the initial values are calculated.

本文继續从前的工作,把击中月球的火箭軌道設計完成。在这里进一步完善了以双二体問題为基础的进口位置和初始条件之間的关系。然后討論了除地球引力場一阶項和月球摄动以外的其它因素对击中月球的影响,討論証明这些因素是可以忽略的。最后研究了初始数据的誤差对击中月球产生的偏差,从而估計出各初始数据可容許的最大誤差。

This paper discusses the problem of distribution of points on the moon's surface intersected by the orbits of several kinds of lunar rocket, based on the planar and space double two-body problem. First we obtained the ingress-region on the moon's sphere of influence in which the orbits with different initial veloceties can hit the moon vertically, slantingly and tangentially. Then we get the distribution of hitting points on moon's surfaceof these orbits; hence we determine the forbbiden regions on the moon's...

This paper discusses the problem of distribution of points on the moon's surface intersected by the orbits of several kinds of lunar rocket, based on the planar and space double two-body problem. First we obtained the ingress-region on the moon's sphere of influence in which the orbits with different initial veloceties can hit the moon vertically, slantingly and tangentially. Then we get the distribution of hitting points on moon's surfaceof these orbits; hence we determine the forbbiden regions on the moon's surface of hitting orbits with different initial velocities. The result of calculation shows that: the magnitude of forbbiden region mainly depends upon the magnitude of initial velocity, when the initial velocity increases, then the magnitude of forbbided region increases monotonically; in the case of ascending orbits, the position of forbbiden region is at the posterior part (opposite to the direction of lunar motion) of the invisible half of the moon's surface; in the case of descending orbits, the position of forbbiden region is at the posterior part of the visible half of the moon's surface. Consequently, the anterior part of the invisible half of the moon can be hitten by ascending orbit; and every point on the moon's surface can be hitten by an ascending or descending orbit with specified initial velocity.

本文以平面和空間的双二体問題为基础,研究了几种类型的击中月球火箭的軌道在击中月球时同月面交点的分布問題。得到了几种不同初始速度能垂直击中,傾斜击中以及切向击中月球的軌道在月球作用范圍边界上的进口范圍。然后得出这些軌道在月面上击中点的分布情况;从而得出不同初始速度的軌道在月面上击中的禁区。从計算結果可看出:禁区大小主要同初始发射速度有关,速度愈大則禁区也愈大;禁区位置对上升軌道而言,在月球背面的后部(同月球运动反方向的部份),对下降軌道而言,在月球正面的后部;因此,用上升軌道也可以击中月球背面的一部份(前部),用适当的初始速度和軌道类型(上升或下降),可以击中月面上任何一点。

The purpose of this investigation is to study the possibility and condition for a lunar probe to hit or to fly over, at close range, any given region on the surface of the moon. We limit the ballistic speed of the vehicle to 11.2 km/sec and require that the height at the last burn out point should be about a few hundred kilometres. Six definite regions on the surface of the moon are considered as the objectives of these flights. Four regions lie on the great circle where the orbital plane of the moon cuts the...

The purpose of this investigation is to study the possibility and condition for a lunar probe to hit or to fly over, at close range, any given region on the surface of the moon. We limit the ballistic speed of the vehicle to 11.2 km/sec and require that the height at the last burn out point should be about a few hundred kilometres. Six definite regions on the surface of the moon are considered as the objectives of these flights. Four regions lie on the great circle where the orbital plane of the moon cuts the lunar surface. They are designated as the "near", "remote", "east", and "west" points. For these points, only trajectories in the orbital plane of the moon have been considered. The other two regions, namely, the poles of the aforesaid great circle, are called the "north" and "south" points respectively. In the preliminary survey of the possible trajectories, the approximate method of assuming the earth-moon space as divided into two by a sphere of action of radius 66000 km around the moon has been employed. The trajectory may then be considered to consist of several sections, each one of which is determined by the laws of two-body problem. From considerations on the permissible angular momentum of the orbit, it has been possible to derive limiting values for the velocity of hitting and the angle of incidence in the case of impact trajectories. For reconnaissance trajectories, we try to find out the allowable perilunar distance and velocity as well as how close may the perilunar point of the trajectory be brought to the surface of the moon. From preliminary investigation by the approximate method of sphere of action, we have come to the following conclusions: A. For impact trajectories: 1) To hit either the near or the remote point, the vehicle must be approaching the moon from the east side. With velocity of impact somewhere in the range 160—180km/min, the probe may hit these points at an angle of incidence of 30° or greater. 2) Vertical impact is possible only at the east point with the velocity of hitting at slightly less than 160 km/min. 3) The west point may be hit by a lunar probe, but only at grazing incidence. 4) The trajectories for hitting the north and the south points could be mirror images of each other. These points may be hit at an angle of incidence of about 60°, at a speed of less than 160 km/min. B. For reconnaissance trajectories: 1) Over the near and the remote points, there is a whole series of symmetrical orbits in which the vehicle would be sure to return to the neighbourhood of the earth. When the perilunar velocity is about 100 km/min, the distance of close approach to the centre of the moon may be no more than 5000 km. We can make the trajectory come in contact with the surface of the moon, if we allow the perilunar velocity to be increased to 160 km/min. 2) With perilunar distance over 30000 km, it is possible for the vehicle to fly horizontally over the east point of the moon. Such reconnaissance flight is possible over the west point, but the vehicle has to be so low that the orbit becomes identical with the impact trajectory grazing the west point. 3) When the perilunar point of the orbit may be permitted to deviate about 45° from the zenith of the east or the west point, we can still have reconnaissance trajectories that will bring the vehicle back to the neighbourhood of the earth. 4) When we consider only trajectories whose motion inside the sphere of action is in a plane perpendicular to the earth-moon direction, we could have symmetrical orbits with horizontal flight over the north or the south point at a distance of about 24000 km from the centre of the moon. With permissible values at the moon for different definite points, the path of the vehicle is traced backward in time to verify if it did pass by the vicinity of the earth with reasonable speed. If so, the position and velocity of the vehicle near the earth are taken as the initial values at the last burn out point, and the impact or reconnaissance trajectory is computed once again. In such computations the attractions of both the moon and the earth are taken into account by the method of numerical integration. The trajectories thus obtained are listed in Tables 5, 6, and 7.

在月球表面上考虑了六个定点,它们是自道面内的近、远、东、西四点和此外的南北两点。为了要找到可以实现用火箭击中和航测这六点的轨道,我们以在月面定点上可以容许的初值为轨道出发点,倒推出火箭在地球附近时的位置和速度。月面定点上的初值是依据火箭大约在地面上200公里高空以第二宇宙速度发射的假定选取的。所用方法是按作用范围和简单的角动量和能量守恒的原理来考虑的。计算结果表明,火箭从地面上以通常的高度和速度发射能够击中这六个定点:东点可以垂直击中,西点只能切向击中。航测这六个定点,都可以找到有去有回的轨道,航测远、近、南、北四点还可以有对称的轨道。航测远、近点可以和月面接近到任意距离,航测其他各点,距离便要远些,约为二、三万公里。

 
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