Circular orbit spacecraft control at the L4 point using Lyapunov functions

The objective of this work is to demonstrate the utility of Lyapunov functions in control synthesis for the purpose of maintaining and stabilizing a spacecraft in a circular orbit at the L4 point in the circular restricted three body problem (CR3BP). Incorporating the requirements of a fixed radius orbit and a desired angular momentum, a Lyapunov function is constructed and the requisite analysis is performed to obtain a controller. Asymptotic stability is proved in a defined region around the L4 point with the help of LaSalle's principle.