Use of an Electric-Reactive Engine in the Mode of Discrete Activations to Support the Working Orbit of a Small Spacecraft for Remote Earth Sensing

Abstract

The object of the research is a model of a small spacecraft for remote sensing of the Earth, located in a low near-circular orbit. An analysis is being made of the possibility of using an electric jet engine to maintain the radius of the working orbit of a spacecraft over a long time interval (5–7 years). It is assumed that the power plant of a small spacecraft is not capable of supporting the continuous operation of an electric jet engine throughout the entire orbit. The time of continuous operation is several minutes on orbit correction orbits. The range of change in the values of the ballistic coefficient of a small spacecraft depending on the orientation of the satellite during the flight is estimated. It is shown that the predicted time for reducing the average orbit height by 10–15% without correction does not exceed two years. With two or three switching on of the electric jet engine per day, it is possible to maintain the working orbit of the spacecraft in the condition of the Earth’s upper atmosphere, corresponding to low and medium levels of solar activity. With an increase in solar activity (respectively, the compaction of the Earth’s upper atmosphere at the studying height), a greater number of engine starts per day is required. The results obtained can be used in the design of motion control systems for a small Earth remote sensing spacecraft using an electric jet engine.