Journal of Astronautics ›› 2017, Vol. 38 ›› Issue (10): 1041-1047.doi: 10.3873/j.issn.1000-1328.2017.10.004

Previous Articles     Next Articles

Indirect Optimization of Low Thrust Multi Revolution Orbit Transfers for Geostationary Orbit Satellites

SHEN Hong xin, LI Heng nian   

  1. State Key Laboratory of Astronautic Dynamics, Xi’an Satellite Control Center, Xi’an 710043, China
  • Received:2017-05-11 Revised:2017-08-10 Online:2017-10-15 Published:2017-10-25


A method for the optimization of geostationary orbit (GEO) satellite orbit transfer with all-electric propulsion is proposed. The Earth’s oblateness (J2) perturbation is included in the dynamic model. The time-optimal control law of the GEO satellites as well as the first order optimality necessary conditions, based on the Pontryagin’s maximum principle (PMP), are deduced. The resulting two-point boundary value problem is solved based on thrust continuation approach and by means of the Newton’s downhill method. Numerical simulations have demonstrated the effectiveness of the approach proposed, with performance increasing about 5% compared to the existing results. From the numerical results, some characteristics of the time-optimal transfer orbit element changes are drawn, which could provide reference for aerospace engineering.

Key words: Electric propulsion, Geostationary orbit satellite, Indirect method, Two point boundary value problem, Trajectory optimization

CLC Number: