After a series of maneuvers November 4, the station went on the flight path to the Moon and on 8 November reached the environs of the Moon, where at a distance of 500 km from the surface was included brake motor, resulting in the station moved to a transitional circumlunar orbit resettlement 504 km, aposelene 7502 km and an orbital period of 11 hours. Then on 9 November, after adjustment of the pericenter of the orbit was lowered to 200 km. On November 13, the station was transferred to the circular working circumlunar orbit with altitude of 100 km (1,838.10
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On August 29, 2009 ISRO announced that radio contact with the satellite was lost. By the time of the loss of communication with the satellite, it stayed in orbit 312 days (0,27.10
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Indian space research organization claims that her device will be in lunar orbit for another 1000 days. The lack of data on the orbital parameters after braking satellite Chandrayaan-1 does not allow the calculation of the constant C. However, determining the average value for other satellites, using equation (3) to confirm or refine the prediction of the lifetime of the satellite "Chandrayan-1.
The average value of the constant C it is advisable to calculate on three.satellites: "the lunar Prospector", "Smart-1" and "Kaguya". It is of 2.16.10
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With regard to satellite "Chandrayan-1, the calculation showed that the total time spent in orbit until the fall on the surface of the Moon is 644 days including 332 days after loss of communication with the satellite.
The deviations of the estimated time from the actual for other satellites are given in table 1. In the case of a satellite, the lunar Prospector" observed the coincidence of two values: 0.157.10
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4. The influence of gravimagnetism on planetary and satellite distance
Let us consider the problem of the connection between phenomena gravimagnetism with the regularity of planetary and satellite orbital distances. Here it is appropriate to remind once again about the ideas of M. Faraday, who introduced the concept of the gravitational field, managing the planet in orbit. The sun generates a field around itself, and the planets and other celestial bodies feel the influence of the field and behave accordingly."
Unlike the Moon, the Earth has its own rotation around its axis. This rotation may distort the lines of tension from Sinα = 1 to Sinα = 0, that is, braking force in a rotating central bodies can have a very small value.
It can be assumed that the rotation of the Earth causes deformation of the surrounding gravitational field, and this oscillatory motion, in which are formed of concentric layers with different orientation vector gravimagnetic tension. When the orientation is close to concentric (Sinα 0) the motion is without braking and energy consumption, i.e. elite or permitted orbits. If the orientation of the vector gravimagnetic tension is close to radial, as in the case of the Moon, the braking is happened and the satellite moves to the bottom of the orbit lying with less potential energy.
In some works [11, 12] it is shown that planetary and satellite orbital distance r is expressed by the equation similar to equation Bohr quantization of orbits in the atom:
r = n
2
k, (4)where n is an integer (quantum) number, k is a constant having a constant value for the planetary and each satellite system.
The k values calculated for planetary and satellite systems, are presented in table 2. For different systems, while maintaining consistency within the system, the value of k varies within wide limits [13]. For the planetary system it is 6280.10
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Seemed interesting to find such a mathematical model, which would be in the same equation was combined planetary and satellite systems. In this respect fruitful was the idea expressed by H. Alfvén [14], that the emergence of an ordered system of secondary bodies around the primary body whether it be the Sun or a planet, definitely depends on two parameters initial body: its mass and speed" It has been shown [13] that when the normalization constant k in the complex, representing the square root of the product of the mass of the central body for the period of its rotation (MT)of
0.5
0.5
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Thus, in a mathematical model expressing the regularity of planetary and satellite distances should include the mass of the central body and the period of its rotation, two factors (mass movement) determining the occurrence of gravimagnetic forces in the system.
Further, in the synthesis equation, it seemed natural, should include the gravitational constant G. By a large number of trial calculations, it was found that equation (mathematical model) that combines planetary and satellite systems, is the expression:
r = n
2
(GMT/C)0.5
, (5)where n is the number of whole (quantum) numbers, C is a constant having the dimension of velocity, cm/s, see table 2.
Table 2. The values of the constants k and C
Consider in more detail and compare the constants C, included in gravimagnetic equation (1), (3) and equation (5). In both cases, the constants have the same dimension cm/s and approximate nearer value. The average value of the constants included in equations (3) and (5) respectively of 2.16.10
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The overstated value of a constant, calculated according to equation (5) is connected with the incorrect definition of the period of rotation of the gas-liquid
central bodies for example, the rotation period of the Sun at the equator is equal to 25 days, and at high latitudes 33 days. It is clear that the inner layers and the entire body as a whole rotate at a higher speed. In accordance with the formula (5) this will lead to a lower constant value C.
The most accurate values are constants C values calculated for solid planets Earth and Mars, the period of rotation of which is determined accurately. The average value of the constants for these two planets is equal 2,48.10
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Thus, with a high degree of reliability can be argued that the constant C in equations (1), (3) and (5) are identical and express the same process gravimagnetic interaction of masses. In the first case the interaction is not rotating Moon and rotating around it satellites, in the second rotating central bodies (the Sun, planets) and their orbital bodies.
The results about gravimagnetism braking when the orbiting bodies driving around a non-rotating Central body the Moon are in good agreement with the known data that celestial body which does not have its own rotation around its axis (Mercury) or low speed (Venus), do not have satellites. In contrast, satellites of rotating central bodies are braking poorly, especially when moving in orbits with a maximum shear strain of the gravitational field and, accordingly, with a peak concentric orientation of gravimagnetic power lines.
The bulk wave maximum deformation occurs at the equator and extends then in the equatorial plane. Captured satellites quickly decelerate and fall on the Central body. This explains the predominant position of the planets and satellites in the equatorial plane of a rotating central body. Here the greatest shear deformation and concentric orientation gravimagnetic field and the least resistance to movement of the orbital phone. For the same reason it is impossible the existence of polar satellites. Their orbit crosses the force lines at an angle close to 90°. Due to the high gravitational resistance, they quickly decelerate and fall.
A satisfactory explanation also receives the same direction of orbital motion with the rotation of the central bodies and synchronous rotation of the planets and the Sun.