Electric propulsion transfer orbit control method for geostationary orbit spacecraft

Abstract

The invention relates to a geostationary orbit spacecraft electrical propulsion transfer track control method. The method comprises the following steps: determining initial conditions, a carrier rocket transmitting a geostationary orbit spacecraft to a first initial orbit, and determining a Kepler radical of the first initial orbit; establishing a first initial orbit kinetic equation by means of the Kepler radical, reducing the orbit inclination angle of the first initial orbit through a thrust azimuth alpha and performing rounding to obtain a second initial orbit, and obtaining transfer time tf1 and a propellant consumption amount mfuel1; fixing a thrust accelerated speed in a second preset plane, transferring the second initial orbit through a thrust azimuth beta to a geostationary orbit, and obtaining transfer time tf2 and a propellant consumption amount mfuel2; calculating total time tf=tf1+tf2 of a geostationary orbit transfer process and a propellant consumption amount of the transfer process; and by taking minimization of the geostationary orbit total time tf as a design object, optimizing the thrust azimuth alpha at a first initial orbit phase to obtain an optimal geostationary orbit transferring scheme.

Description

technical field [0001] The invention relates to the field of orbital spacecraft control, in particular to a method for controlling an electric propulsion transfer orbit of a geostationary orbital spacecraft. Background technique [0002] Compared with the traditional chemical propulsion system, the electric propulsion system has the advantages of high specific impulse, precise adjustment of thrust and high control precision. Among them, the specific impulse of the electric propulsion system (now more than 3800 seconds) is much higher than that of the traditional chemical propulsion system (generally around 300 seconds), so that the propellant required by the electric propulsion system to complete the same space mission will be greatly reduced. The reduction is of great significance for improving the payload ratio of spacecraft, reducing launch costs, and improving the life of spacecraft in orbit. However, compared with the chemical propulsion system, the thrust of the elect...

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Problems solved by technology

However, when solving two-point boundary value problems, the indirect method faces numerical difficulties such as small convergence domain, difficulty in guessing the initial value, and sensitive boundary conditions. The optimality of results, etc.

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