2011/03/08 by Xiang-Yuan Zeng, Xiangyuan Zeng, Hexi Baoyin +4 · 1 citation
Engineering · Physics and Astronomy · #Asteroid #Astro and Planetary Science #Earth's orbit #Ecliptic #Elliptic orbit #Halo orbit #Heliocentric orbit #Orbit (dynamics) #Solar System #Solar sail #Space Satellite Systems and Control #Spacecraft Dynamics and Control #Trajectory #astro-ph.SR
paper · pdf · doi:10.1088/1674-4527/11/7/011
19 pages, 14 figures, 2 tables. RAA 2011
arxiv created 2011/03/08 · openalex publication_date 2011/06/21 · arxiv updated 2015/05/27 · openalex created_date 2016/06/24 · openalex updated_date 2026/08/05
Advanced solar sailing has been an increasingly attractive propulsion system for highly non-Keplerian orbits. Three new applications of the orbital angular momentum reversal (H-reversal) trajectories using solar sails are presented in this paper: space observation, heliocentric orbit transfer, and collision orbits with asteroids. A theoretical proof for the existence of double H-reversal trajectories (referred to as 'H2RTs') is given, and the characteristics of the H2RTs are introduced before the discussion of the mission applications. A new family of H2RTs was obtained using a 3D dynamic model of the two-body frame. In a time-optimal control model, the minimum period H2RTs both inside and outside the ecliptic plane were examined using an ideal solar sail. Due to the quasi-heliostationary property at its two symmetrical aphelia, the H2RTs were deemed suitable for space observation. For the second application, the heliocentric transfer orbit was able to function as the time-optimal H-reversal trajectory, as its perihelion velocity is circular or elliptic velocity. Such a transfer orbit can place the sailcraft into a clockwise orbit in the ecliptic plane, with a high inclination or displacement above or below the Sun. The third application of the H-reversal trajectory was simulated impacting an asteroid passing near Earth in a head-on collision. The collision point can be designed through selecting different perihelia or different launch windows. Sample orbits of each application were presented through numerical simulation. The results can serve as a reference for theoretical research and engineering design.