The successful launch of the first satellite around the collinear libration point—International Sun-Earth Explorer-3(ISEE-3), undrawed the prelude of the mission around the libration point. And now, along with the development of the technology of low thrust propulsion and the renaissance of the technology of the solar sail, it has received considerable attention that how to utilize the solar sail in the space mission around the collinear libration point. This paper bases on the Circular Restricted Three-Body Problem(CRTBP), and takes the traditional L1 point as example, studies on the halo orbit around the traditional L1 point, and discusses the solar sail artificial L1 point, analyses the variation of the position of the artificial L1 point with the lightness number of the solar sail, and then investigates the solar sail halo orbit around the artificial L1 point, and compares it with the halo orbit around the traditional L1 point, at the end, analyses the effect of the difference of the lightness number and the out-of-plane amplitude on the orbit, and the variation of the orbit period with the lightness number.
展开▼
