Abstract
Inclination change manoeuvre is widely performed to correct the inclination to the desired value. However, inclination manoeuvres studied or performed so far assumed that the thrust profile is constant maximum. In fact, for inclination change manoeuvre, the satellite position in orbit affects the Δi/Δt efficiency and the manoeuvre will be best performed at nodes. This research investigated the optimum profile thrust for inclination change manoeuvre for small inclination changes only on a case study of LAPAN-A4 satellite. The optimisation involved several methods: using GMAT software and using genetic algorithm which is divided further into general and special perturbation. The results showed a good agreement that the most optimum thrust profile for this case is a constant maximum thrust profile.
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