Trajectory design and flight dynamics of a solar-sail propelled CubeSat class spacecraft targeting Mars and its moons

Solar radiation pressure is a very significant aspect of any space mission, both in terms of perturbations and propagation, such as in the case of solar sailing. Because traditional spacecraft consume considerable amounts of fuel and are expensive, there has been an increase in interest in solar sails, which is an affordable and easier way to navigate through space, using only the momentum of photons from the Sun. This study aims to further develop the mission designed to reach Mars with a solar sail powered CubeSat spacecraft. To make the mission as realistic as possible, detailed orbital analyses of several Mars orbiter missions are performed and the trajectories are implemented into the script, also including the orbits of the moons of Mars, Phobos and Deimos. Additionally, the orbital design and analysis necessary to make it possible to fly by Mars and the Martian moons are performed. The analyses carried out in this study highlighted the advantages of solar sailing, showing the possibility of an interplanetary mission without chemical engines. A more accurate model of solar radiation pressure is implemented with the use of an SPAD file, allowing us to observe the differences among various SRP models. The cannonball model is implemented in this study for a more realistic approach to solar radiation pressure. Furthermore, several FOSS software, such as GMAT, Horizons and Mathematica are used for analyses, plotting and simulations, which are discussed in detail. This study aims to act as a guide for future interplanetary solar sail powered missions.