A new method for solving reachable domain of spacecraft with a single impulse. (April 2018)

• Record Type: Journal Article
• Authors: Chen, Qi; Qiao, Dong; Shang, Haibin; Liu, Xinfu
• Is Part Of: Acta astronautica. Volume 145(2018)
• Page Start: 153
• Page End: 164
• Publication Date: 2018-04
• Subjects: Reachable domain -- Single impulse -- Orbital symmetry -- Orbital boundedness; Astronautics -- Periodicals; Outer space -- Exploration -- Periodicals; Astronautics; Periodicals; 629.405
• DOI: 10.1016/j.actaastro.2018.01.040
• Languages: English
• ISSNs: 0094-5765

Abstract

Abstract: This paper develops a new approach to solve the reachable domain of a spacecraft with a single maximum available impulse. First, the distance in a chosen direction, started from a given position on the initial orbit, is formulated. Then, its extreme value is solved to obtain the maximum reachable distance in this direction. The envelop of the reachable domain in three-dimensional space is determined by solving the maximum reachable distance in all directions. Four scenarios are analyzed, including three typical scenarios (either the maneuver position or impulse direction is fixed, or both are arbitrary) and a new extended scenario (the maneuver position is restricted to an interval and the impulse direction is arbitrary). Moreover, the symmetry and the boundedness of the reachable domain are discussed in detail. The former is helpful to reduce the numerical computation, while the latter decides the maximum eccentricity of the initial orbit for a maximum available impulse. The numerical simulations verify the effectiveness of the proposed method for solving the reachable domain in all four scenarios. Especially, the reachable domain with a highly elliptical initial orbit can be determined successfully, which remains unsolved in the existing papers. Highlights: A new approach is proposed to study the reachable domain of a spacecraft. The envelop of reachable domain is investigated by the maximum reachable distance. The analyses of the reachable domain are given with details in four scenarios. The proposed method is proved by simulations, especially for high-elliptical orbit.