Optimal solar sail transfers to circular Earth-synchronous displaced orbits  

作　　者：Alessandro A.Quarta Giovanni Mengali Marco Bassetto 

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

出　　处：《Astrodynamics》2020年第3期193-204,共12页航天动力学（英文）

基　　金：This work is supported by the University of Pisa,Progetti di Ricerca di Ateneo(Grant No.PRA 201844).

摘　　要：The aim of this paper is to evaluate the minimum flight time of a solar sail-based spacecraft towards Earth-synchronous(heliocentric)circular displaced orbits.These are special displaced non-Keplerian orbits characterized by a period of one year,which makes them suitable for the observation of Earth’s polar regions.The solar sail is modeled as a flat and purely reflective film with medium-low performance,that is,with a characteristic acceleration less than one millimeter per second squared.Starting from a circular parking orbit of radius equal to one astronomical unit,the optimal steering law is sought by considering the characteristic acceleration that is required for the maintenance of the target Earth-synchronous displaced orbit.The indirect approach used for the calculation of the optimal transfer trajectory allows the minimum flight time to be correlated with several Earth-synchronous displaced orbits,each one being characterized by given values of Earth-spacecraft distance and displacement over the ecliptic.The proposed mathematical model is validated by comparison with results available in the literature,in which a piecewise-constant steering law is used to find the optimal flight time for a transfer towards a one-year Type I non-Keplerian orbit.

关 键 词：solar sail synchronous displaced orbit trajectory optimization 

分 类 号：P18[天文地球—天文学]