CONTROL METHOD removing space vehicles into orbit a planet artificial satellite

摘要

Method for controlling breeding of spacecraft into orbit planet artificial satellite, comprising a spacecraft approaching a predetermined entrance passage into the atmosphere, particularly in the i-th, where i = 1, 2, ..., N, times the motion parameters of the spacecraft, namely : its speed - V, the tilt angle of the speed vector of the spacecraft to the local horizon for the trajectory of its motion - θ, the radius - vector - r, atmospheric density - ρ, wherein the determination of spacecraft motion parameters is carried out on site in motion weatherp e planet providing entry of the spacecraft into the atmosphere with the value γ roll angle about 0 rad, and the value of the angle of incidence of the spacecraft about α, corresponding to the maximum value of aerodynamic control of the spacecraft, the control amount of the spacecraft γ roll angle to departure from the atmosphere, in determining the velocity spacecraft apocenter transition elliptical orbits - vulgaris implementation supply characteristic velocity accelerating pulse - ΔV in elliptical transition apocenter the orbit of the spacecraft to form the orbit with the given parameters, characterized in that the i-th, where i = K, K + 1, ..., R + M time points on a plot of the aerodynamic deceleration predicted at the time of the spacecraft from the atmosphere of the planet values ​​of the velocity of the spacecraft - vulgaris angle velocity vector to the local horizon for spacecraft trajectory - θpri motion of the spacecraft on the remaining parts of the flight in the atmosphere of the planet respectively with the magnitude of spacecraft roll angle γ equal