Motion control of the spacecraft with a low thrust engine during flight to near-Earth asteroids

Abstract

This work aims to simulate the flight of a spacecraft with an electric propulsion system to the near-Earth asteroid 2011ES4. A control law was formed that ensures the minimum fuel consumption when the engine is running without shutdowns. The simulation of the flight of the spacecraft to the point of the asteroid’s orbit closest to the Earth is carried out. An additional study was also carried out, which simulates the flight of a spacecraft with a liquid-propellant engine. A comparison of the flight simulation results using two different propulsion systems was made. A comparison of the mass flow rate, the relative velocity between the spacecraft and the asteroid, and the flight times using these propulsion systems is made.