Spacecraft Orbital maneuver Flight Dynamics Simulation and Verification

Abstract

During the spacecraft (SC) mission, some of orbital elements change during the flight, the need to study the spacecraft maneuvers become paramount importance need. A full mathematical model for the Spacecraft lifetime maneuvers is deduced, implemented in a simulation scenario with a GUI, and then desired simulation is verified during the different operations' phases such as orbit transfer, propagation, maintenance and deorbiting. In the current article, an interpretation of the carried-out model will be introduced to match a real case of mission analysis as possible for newly designed satellite. Two types of orbits (inclined and Sun synchronous Orbit SSO) are investigated for the SC mission analysis over the whole lifetime phases. The investigation is carried out using two types of power systems (electrical and chemical) using the same propellant tank model with capacity 60 kg. A numerical comparison was concluded for both studied power systems.