cm/s is associated with significant orbital eccentricity at which the intersection of the gravity-magnetic power lines occurs at small angles and braking force in accordance with equation (1) is small. Therefore, the estimated flight time is significantly less than the actual, since the calculation was made according to the formula (3), in which the angle α was not taken into account.
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: 0.157.108 and 0,153.108 C. For "Smart-1" rated value is 12.5 % higher than the actual, for the "Kaguya" 15 % below the actual time of flight of the satellite. This coincidence of the calculated and observational data confirms the correctness of the made assumptions about the braking satellites of the moon due to gravimagnetic forces.
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 = n2k, (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 6280.108 cm, and the smallest satellite system Mars 1,25.108 cm, there are 5 000 times smaller.
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, the result is a constant value, see table 2. If the constant k is changed for the considered systems within 3.5 decimal orders of magnitude, normalized by k/(MT)0.5 value saves the apparent constancy, rather varies from 0.95.10-8 to 1.66.10-8
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 = n2(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 2.16.108 and 4,01.108 cm/s, We can assume that we are talking about the same dynamic gravitational constant, similar to the electrodynamics constant, i.e. the speed of light.
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 2,48.108 cm/s, which almost coincides with the average value of the constant C = 2,16.108 cm/s, calculated by the formula (3) for satellites "the lunar Prospector", "Smart-1" and "Kaguya".
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.
Conclusions
1. The assessment of the gravity-magnetic effect by braking of the satellites of the Moon "Luna-10", "the lunar Prospector", "Smart-1", "Kaguya" and "Chandrayan-1 is given. For the quantitative description of effect used equation gravimagnetic braking similar electrodynamics equation of the Lorentz force and the equation of momentum. The constant part of the equation braking, has a value of C = 2,16.108 cm/s. Estimated time flight of satellites on orbit "the lunar Prospector", "Smart-1" and "Kaguya" is different from the actual ± 14 %.
2. On the basis of gravimagnetism braking orbital bodies is obtained the empirical formula, which expresses the dependence of the orbital planetary and satellite distances from a number of whole (quantum) numbers, mass