TITLE:
Data-Driven Nonlinear Control for Orbit Transfer: From the Earth to Moon and L4/5
AUTHORS:
Xianyang Chen
KEYWORDS:
Restricted Three Body Problem, Koopman Eigenfunction, Non-Linear System
JOURNAL NAME:
Modern Mechanical Engineering,
Vol.9 No.1,
January
17,
2019
ABSTRACT: From
the recent thirty years, scientists will never stop exploring the outer space.
To assist the development of travelling into the universe, I devote myself into
providing theoretical support and future indications for designing the optimal
orbit for satellite to travel in a Three-Body
System. This paper offers the optimal orbit for satellite to change path in the
earth-moon system. Also, it provides the path for the satellite to use the
least fuel to go to the L4 and L5 Lagrange points. These inspiring results are
obtained through several steps: to solve the problems caused by the non-linear
character of Three-Body System, I use Koopman eigenfunction to change the system into a
linear one. Data-driven method is adopted to find the most suitable Koopman
eigenfunction to apply control. The traditional LQR operator for linear system
is used to design the optimal orbit for the satellite.