AMAT: MARTA – MAny Revolution Transfer Algorithm

This figure, created using the MAny Revolution Transfer Algorithm (MARTA) within the AMAT software, shows how a spacecraft can gradually transfer from a Geostationary Transfer Orbit (GTO) to a Geostationary Orbit (GEO) using Solar Electric Propulsion (SEP), a highly fuel-efficient propulsion technology that produces a small but continuous thrust.
Rather than performing a few large engine burns, the spacecraft continuously adjusts its orbit over many revolutions around Earth. The many coloured curves illustrate the gradual evolution of the trajectory, from the initial orbit after launch (shown in red) to the final operational orbit (shown in blue).

Although the figure appears complex, it represents a practical mission planning problem: how to reach the desired orbit while minimising fuel consumption, transfer duration, and operational constraints.

Tools like AMAT can thus support mission analysts by modelling trajectory variations such as this and identifying the most efficient transfer strategy. This type of analysis directly influences mission design decisions: it helps engineers estimate transfer times, determine propulsion system requirements, assess spacecraft resources and evaluate trade-offs between cost, performance and mission objectives. The resulting trajectory becomes a key element of the overall mission architecture and can ultimately affect launcher selection, spacecraft design, and operational planning.