STUDY OF THE EARTH-MOON TRANSFER SPACE VEHICLE ON THE BASIS OF THE CUBESAT PLATFORM
The aim of this work is to theoretically substantiate the prospects for a CubeSat launch into deep space, as well as to determine the optimal direct ballistic flight of a spacecraft with minimal energy consumption from a low near-earth orbit to the libration point L1 of the Earth-Moon system on a given date of impact. In this work, all the necessary equipment for the proposed spacecraft has been selected and evaluated. Having made sure that the satellite of the CubeSat format can be used in deep space, the flight was considered in the traditional way - using an upper stage with chemical engines. So, in the work it was revealed that the spacecraft will reach the libration point in 9 days, which is much faster than a flight with low-thrust electric rocket engines. To describe a ballistic flight, it is necessary to consider the spacecraft motion in the gravitational field of the Earth and the Moon. Thus, it is necessary to solve the three-body problem. To solve the equation of motion in rectangular coordinates, it is necessary to use data on the position and velocity of celestial bodies in the considered coordinate systems. For this, mathematical models are used to calculate the ephemeris. In this work, the model DE-403 manufactured by JPL (Jet Propulsion Laboratory) is used, and all calculations are carried out in the mathematical package Mathcad. For an optimal flight, the Moon's inclination must be at its maximum. After a comparative analysis, it was revealed that the optimal launch date for the spacecraft will be March 2025, at which time the maximum inclination angle of the Moon's orbit is observed - 28.721.