Optimal guidance based on receding horizon control for low-thrust transfer to libration point orbits

摘要: Abstract This paper addresses the design and computation of a guidance law for transfer mission from an orbit near Earth to halo around libration point L2 in Sun–Earth system. The law, which is designed based on receding horizon control compensates launch velocity errors that are introduced by inaccuracies vehicle, solved using generating function method. During closed-loop entire mission, considered nonlinear optimal problem, evaluated obtain nominal reference trajectory. Using uncertainty model, spacecraft controlled proposed tracks Furthermore, original Riccati differential equation algorithm replaced equivalent convenient form function. high-efficiency solution avoids online direct integration equation, significantly increases computational efficiency problem. Numerical simulations bicircular four-body model demonstrate capabilities mission. In addition, method improves at least one order magnitude over backward sweep solving