Jeannette, H., Ben, D. William, D. and Colin, M. (2014) Sunjammer: Preliminary End-to-End Mission Design. AIAA/AAS Astrodynamics Specialist Conference, San Diego, California, USA, 4-7 August 2014.
http://dx.doi.org/10.2514/6.2014-4127

has been cited by the following article:

• TITLE: Solar Sail Equilibrium Orbits in the Circular Restricted Three-Body Problem with Oblateness

  AUTHORS: Ming Song, Xingsuo He, Yehao Yan, Dongsheng He

  KEYWORDS: Solar Sail, Restricted Three-Body Problem, Equilibrium Orbits, Oblateness

  JOURNAL NAME: Open Access Library Journal, Vol.3 No.5, May 31, 2016

  ABSTRACT: We investigate solar sail in the circular restricted three-body problem, where the larger primary is a source of radiation and the smaller primary is an oblate spheroid in the system. Firstly, the differential equations of motion for solar sail in the system combined effects of radiation and oblateness of celestial bodies are built. Then the positions of the solar sail collinear Lagrange points are calculated as mass ratio or oblateness changes in certain extent. Linearization near the collinear equilibria of the system is applied. A linear quadratic regulator is used to stabilize the nonlinear system. Three different cases of solar sail equilibrium orbits are studied each with different choices for the weight matrices. The simulations reveal that solar sail equilibrium orbits can be stable under active control by changing three angles, incident angle, cone angle and clock angle of the solar sail.