Combined System–Trajectory Design for Geostationary Orbit Platforms on Hybrid Transfer

What is it about?

The design of satellites and the path they follow is usually separate. In this work, a novel method is proposed for a combined design of the satellite systems and the trajectory as many aspects of their individual design are intertwined. Transfer of satellites from a Low Earth Orbit to Geostationary Orbit is traditionally done by using conventional rocket systems that burn liquid propellants. A recent development is the accomplishment of such transfers using electric rockets (ion propulsion). The former accomplishes fast transfer while weighing a lot. The latter accomplishes slow transfer while weighing very less. This work proposes a hybrid solution in which chemical propulsion (conventional) is used to bring the spacecraft halfway and then electric propulsion is used the rest of the way. By combining these, a balance between weight and time of flight can be achieved. The combined system-trajectory design proposed in this work focuses on increasing the mass of the useful instruments that the satellite would bring to its final destination. Thus, all aspects of the design, which include the propulsion, system that supplies power, the parameters that influence the transfer path, etc., are optimized to achieve the goal. The work provides a range of solutions for customizable target useful masses.

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