This paper improved these methods based on the requirements 0There are two methods for conventional orbital control: one is algebra method which deals with the problems by optimization based on orbit geometry characteristics The first method is applied when we adopt impulsive control, but in the multiobjective cases the method has its limitation.

The differences in orbital morphologies due to different potentials is slighting, however, given a certain potential, for clusters that have perigalactic distance smaller than 1 kpc, some orbits may exhibit a chaotic behavior.

With the phase plane analysis method, we obtain the general relativity motion equation in the gravitational field of the extreme charged black hole, and we plot the picture of the orbital phase plane and analyze the orbital stability.

We also construct the ideal of definition of such an orbital variety up to taking the radical.

The hydrophobic parameter, dipole element, frontier molecular orbital energy gap and hydration energy of these hydrocarbons were calculated with the PM3 semi-empirical quantum chemistry method.

Penicillium expansum, a Resident Fungal Strain of the Orbital Complex Mir, Producing Xanthocyllin X and Questiomycin A

It was demonstrated that the fungus Penicillium expansum 2-7, a resident strain of the orbital complex Mir, which became dominant at the end of a long-term space flight, formed biologically active secondary metabolites (antibiotics).

These elements can find use in the problems of departure and transfer to the parking orbit, as well as in the problems of orbital transfers.

For use in cosmogonical investigations,a detailed calculation of the angular momenta of various bodies in the solar system is made,making use of latest data. A_(1P) denotes the orbital angular momentum of a planet about the center of mass of the sun- planet system,A_(1⊙) denotes the orbital angular momentum of the sun about the same center of mass.A_(1P)+A_(1⊙)=A_1.These three quantities are calculated according to formulae (2),(3),(4), and the results are given in Table 1.In this table A_(1P) includes...

For use in cosmogonical investigations,a detailed calculation of the angular momenta of various bodies in the solar system is made,making use of latest data. A_(1P) denotes the orbital angular momentum of a planet about the center of mass of the sun- planet system,A_(1⊙) denotes the orbital angular momentum of the sun about the same center of mass.A_(1P)+A_(1⊙)=A_1.These three quantities are calculated according to formulae (2),(3),(4), and the results are given in Table 1.In this table A_(1P) includes the orbital angular momentum of the planet's satelfites about the center of mass of the sun-planet system.

The general perturbations on this minor planet by the action of JUPITER and SATURN were computed by Bohlin's method and the orbital corrections were made by Tietjen method. Finally,after the orbital corrections were made by means of Eckert's method,the following average residuls have been obtained:|Δα|=196 and |Δδ|=218.

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 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.