Verification of M.Faraday's hypothesis on the gravitational power lines. А. Т. Серков

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      Braking force satellite f in addition to equation 1 can be expressed by the equation of momentum:

      where m is the satellite mass, t is the time of braking, v₁ and v₂ are the velocities before and after braking. Combining equations (1) and (2) obtain a convenient expression for calculating the time of flight of the satellite:

      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^-8 cm3/G2, M is the mass of the Moon 0,735.1026 g, r – average orbital distance (the semi major axis) at the beginning of the flight, v₁ and v₂ are the initial and final orbital velocity, calculated at an average orbital distance.

      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 = 3,694.10⁸ cm/s Calculated data are presented in Table 1. Perform similar calculations for other travelers of the Moon.

      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 v₁ = 1,665.10⁵ cm/s and at the moment of falling v₂ = 1,680.10⁵ cm/s Substituting the above values in the formula 3, we get the value of the constants C = 2,25.108 cm/s, that is close in order of magnitude to the value of the constants calculated for the satellite "Luna-10. The satellite of the moon, Smart-1 (Smart-1: the acronym for Small Mission for Advanced Research in Technology) launched by the European space Agency September 30, 2003 [8]. Initially, it was launched into an elliptical low earth orbit typical of telecommunication satellites with the help of the rocket Ariane-5. Then the output on the lunar orbit was carried out using a low-power (thrust force of 0.07 N) ion propulsion and lasted 16 months.

      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 4,6182.10⁸ cm and the pericenter 2,2087.10⁸ cm. The average distance (the semi major axis) 3,4134.10⁸ cm After a flight during 0,121.10⁸s apocenter decreased to 4,4957.108 cm, and the pericenter increased to 2,3493.10⁸ cm. The average distance decreased to 3,4025.10⁸ cm.

      Orbital speed at the beginning and end of the free flight accordingly was 1,1984.10⁵ and 1,2004.10⁸ cm/s Substituting the obtained values of the average distance in the beginning of the period of free flight and orbital velocity at the beginning and end of the flight in the formula 1, we get the value of the constant C = 1,91.108 cm/s, which is close enough to the values previously given for satellites "Luna-10" (3,69.10⁸ cm/s) and the lunar Prospector" (2,25.10⁸ cm/s).

      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 1,838.10⁸ cm, orbital speed 1,6332.10⁵ cm/s).

      The time of the flight without the inclusion of the propulsion system lasted until June 11, 2009, СКАЧАТЬ