Geometric perspectives on fundamental solutions in the linearized satellite relative motion problem

Understanding natural relative motion trajectories is critical to enable fuel-efficient multi-satellite missions operating in complex environments. This paper studies the problem of computing and efficiently parameterizing satellite solutions for linearization about a closed chief orbit. By identifying analytic relationship between Lyapunov–Floquet transformations dynamics different coordinate systems, new means are provided rapid computation exploration types close-proximity available various applications. The approach demonstrated Keplerian with general eccentricities multiple representations. assumption enables an approach, leads geometric insights, allows comparison prior linearized solutions.