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.

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.

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.

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.

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.

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.

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.

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

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.

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.

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.