The control method motion of the spacecraft during landing in a predetermined area of ​​the surface of the planet

摘要

a spacecraft motion control method when landing in a predetermined area of ​​the planet's surface, comprising: a spacecraft input implementation into the atmosphere with the angle of attack α, corresponding to the maximum value of aerodynamic K, in the measurement current spacecraft values ​​of motion coordinates at the instants t, where i = 1,2, ..., n, in the process of the descent in the atmosphere, namely: V- spacecraft flight speed, θ- angle velocity vector of the spacecraft to the local horizon, ε- angle between projection vector of the spacecraft velocity and local local horizon parallel, r- distance between the center of the planet and the center of mass of the spacecraft, φi λ- geocentric latitude and longitude of the spacecraft sub-satellite point, respectively, ρ- density atmosphere at a height of spacecraft flying in determining η - the angle between the projection of the vector of the spacecraft velocity and vertical local horizon plane input apparatus in the atmosphere, ψ - the angular distance between the current position subsatellites th point of the spacecraft and the machine input plane into the atmosphere, establishing spacecraft γ roll angle determined according to the relation: gdeη - the angle between the projection of the velocity vector of the spacecraft to the local horizon and vertical spacecraft entrance plane into the atmosphere; ψ - angular distance between the current position of the spacecraft sub-satellite point and the entrance plane of the spacecraft into the atmosphere; K. balancing aerodynamic efficiency, determined by the angle of attack α; = 3.141593 ..., T wherein