Optimal orbit transfer of single-tether E-sail with inertially fixed spin axis  

作　　者：Alessandro A.Quarta Marco Bassetto Giovanni Mengali 

机构地区：[1]Department of Civil and Industrial Engineering,University of Pisa,Pisa I-56122,Italy

出　　处：《Astrodynamics》2024年第2期285-295,共11页航天动力学（英文）

摘　　要：This study analyzes the optimal transfer trajectory of a spacecraft propelled by a spinstabilized electric solar wind sail(E-sail)with a single conducting tether and a spin axis with a fixed direction in an inertial(heliocentric)reference frame.The approach proposed in this study is useful for rapidly analyzing the optimal transfer trajectories of the current generation of small spacecraft designed to obtain in-situ evidence of the E-sail propulsion concept.In this context,starting with the recently proposed thrust model for a single-tether E-sail,this study discusses the optimal control law and performance in a typical two-dimensional interplanetary transfer by considering the(binary)state of the onboard electron emitter as the single control parameter.The resulting spacecraft heliocentric trajectory is a succession of Keplerian arcs alternated with propelled arcs,that is,the phases in which the electron emitter is switched on.In particular,numerical simulations demonstrated that a single-tether E-sail with an inertially fixed spin axis can perform a classical mission scenario as a circle-to-circle two-dimensional transfer by suitably varying a single control parameter.

关 键 词：electric solar wind sail(E-sail) single conducting tether fixed inertial spin axis trajectory optimization circle-to-circle coplanar transfer 

分 类 号：O57[理学—粒子物理与原子核物理]