To confirm advanced assumptions gravimagnetic braking bodies consider for example, at motion of satellites of the moon.
3. Gravimagnetic braking satellites of the moon
Starting with the first orbital flight of a satellite of the moon "Luna-10" [4, 5], which was launched on 3 April 1966, it became clear that the lunar satellites have abnormally high acceleration and the duration of their existence on the orbit is limited. Of all possible causes inhibition: perturbations due to the influence of the Sun and the Earth, the uneven distribution of mass, the presence of the moon, though very thin atmosphere, the impact of the solar wind focused [6] non spherical shape of the moon. It was shown that perturbations caused by the non centric gravitational field of the Moon is 5-6 times larger than the perturbations due to the Earth's gravitation, and the latter exceeded the solar 180 times.
The main reason for the occurrence of braking forces of the moon satellites may not be the uneven mass distribution, in particular the no spherical character of the Moon. Any algorithm for calculating the impact of uneven distribution of mass, the result depends on the mass of the satellite. The larger the mass, there is stronger interaction and the less the lifetime of satellites in orbit.
However, the available data do not support this conclusion. For example, the satellite Kaguya" had a lot 2371 kg, and the duration of his stay in orbit amounted to 539 days, while the lunar Prospector", having mass 158 kg, ceased to exist after 182 days. As will be shown below, the deceleration time of the Moon satellites does not depend on their mass.
The scheme gravimagnetic braking of the moon satellites is shown in Fig. 2. A satellite with mass m moves with velocity v, traversing radially spaced the force lines of the gravitational field G. The direction of the intensity vector occurring due to the motion of the satellite is perpendicular to the plane of the figure upwards. A satellite is braking by force f that causes the decrease of the orbital distances. By analogy with electrodynamics braking is accompanied by the gravitational radiation at a rate equal to the constant C in equation (1).
Fig. 2. Scheme gravimagnetic braking the lunar satellite: a satellite with mass m moves with velocity v, traversing radially spaced force lines G of the Moon gravitational field (M); the direction of the intensity vector gravimagnetic field arising due to the motion of the satellite perpendicular to the plane of the drawing up; a satellite is retarding force f that causes the decrease of the orbital distance.
Braking force satellite f in addition to equation 1 can be expressed by the equation of momentum:
ft = m(v
2
v1
), (2)where m is the satellite mass, t is the time of braking, v
1
2
t = (C/GM)
2
r3
(v2
v1
), (3)where t is the time of flight, C is a constant having the dimension of velocity cm/s, G is the gravitational constant 6,67.10
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1
2
Returning to the question of the effect of aspheric of the moon on the braking of its satellites, note that in equation (3) expressing the time of flight the satellites is no their mass. This confirms the previously made conclusion about the independence of the flight time from the mass of the satellite.
The constant C in equations (1) and (2) if you follow the accepted analogy with electrodynamics, by definition, is the speed of gravitational radiation. Thus, equation (3) can be used to calculate dynamic gravitational constant, i.e. the velocity of propagation of gravitational waves.
The constancy of the constants when calculating for different satellites will confirm the correctness of the methodological approach. Below is data for the calculation of the constants for the evolution of the orbits of the fife satellites of the Moon, including the Soviet satellite Luna-10", American satellite "the lunar Prospector", a satellite of the European space Agency's Smart-1", as well as Japanese and Indian satellites "Kaguya" and "chandrayan-1.
Consider the launch and flight of Sputnik "Luna-10". First, "Luna-10" was put into orbit an artificial satellite of the Earth. Then, using the upper stage, the speed of the station was reduced to 10.9 km/s. At that speed, the duration of the flight to the Moon was slightly less than three and a half days.
Then was the correction of the trajectory, after which the station entered the sphere of gravitational influence of the Moon.
At the final stage of the flight (800 km from the Moon) station has been previously appropriately focused and calculated point remote from the surface of the moon for 1000 km was included braking engine unit and the speed was reduced from 2.1 to 1.25 km/s, which provided the transfer station under the action of the attraction of the Moon with the span of the trajectory on selenocentric orbit with the following parameters: the greatest distance from the surface of the Moon 1017 km (apocenter 2,755.108 cm); smallest 350 km (pericenter putting on 2,088.108 cm); the average distance (the semimajor axis) 2,422.108 cm; average orbital speed 1,4229.105 cm/s; period of revolution around the moon 2 hours 58 minutes 15 seconds; the angle of inclination of the satellite's orbit to the plane of the lunar equator 71° 54. The mass of the spacecraft after separation from the booster was 1582 kg, the mass of the lunar satellite 240 kg
Artificial satellite of the Moon "Luna-10" there were active 56 days (0,0484.108 (s) having 460 revolutions around the Moon. After the batteries have been depleted, the relationship was terminated on May 30, 1966. Orbit at this time had parameters: minimum destruction of 378 km (pericenter 2,116.108 cm), the greatest destruction of 985 km (apocenter 2,723.108 cm and an inclination of 72.2 degrees. The average distance (the semi major axis) 2,420.108 cm. Average orbital speed 1,4235.105 cm/s.
Substituting the given data into the formula (3), find the value of the constant C = 3,694.10
8
Table 1. The calculation of the duration of the flight, the constants C and braking force to the satellites of the Moon.
Accordingly, the orbital velocity at the beginning of the highlighted portion of the orbit v
1
5
2
5
After moving into the area of the gravity of the Moon and the braking propulsion system on November 11, 2004 "Smart-1" has been translated into lunar orbit. The mass of the satellite 367 kg After number of maneuvers in the period from 28 February to July 18, 2005 the satellite was in free flight, that is, without the inclusion of the propulsion system. The orbital parameters at the beginning of this period: apocenter 4,6182.10
8
8
8
8
8
8
Orbital speed at the beginning and end of the free flight accordingly was 1,1984.10
5
8
8
8
Japanese satellite of the Moon "Kaguya" was launched on 14 September 2007 with the Japanese Baikonur Tanegasima using booster h-2A (H-2A) [9]. The mass of the satellite 3000 kg. To the orbit of the moon it was only appear on 4 October 2007. After separation of the two auxiliary satellites, test equipment and instruments basic core ("Main orbiter") mass 2 27 1kg December 2007 began their regular observations on polar circular orbit with altitude of 100 km (the distance from the center of 1,838.10
8
5
The time of the flight without the inclusion of the propulsion system lasted until June 11, 2009, that is 0,466.10
8
8
5
8
Indian space research organization (ISRO,) reported [10] about the launch of 22 October 2008 on a circumlunar orbit of his device
"Chandrayan-1 using developed in Indian rocket PSLVXL (PSLV Polar Satellite Launch Vehicle from Baikonur Satish Dhawan. Starting weight station was 1380 kg, weight station in lunar orbit 523 kg.
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
8
5
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
8
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
8
8
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
8
8
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
8
8
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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-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 = 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
8
8
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
8
8
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.