Magnetorquer control for orbital manoeuvre of low earth orbit microsatellite

A propulsion system is required in order for the spacecraft to be able to operate as a part of the constellation, and is used to carry out initial launcher injection corrections, spacecraft separation into their respective orbital slots, altitude maintenance and finally an end of life manoeuvre to remove the spacecraft from the operational system also these manoeuvres allow the satellite to alter its semi major axis and the eccentricity of the orbit. The propulsion system fires through the centre of gravity to perform orbit changes manoeuvres. This paper describes the magnetorquer attitude damping propulsion disturbances of low Earth Orbit microsatellite for orbit maintenance with the following points: (1) Mathematical modelling including attitude dynamics and magnetorquer control law, (2) Simulation results will be presented to evaluate the performance and design objectives and finally the conclusion.