Propulsion System Sizing for Servicing Spacecrafts
The initial sizing of the propulsion system takes an important role in the preliminary design stage for space missions. The aim of this paper is to present an initial sizing method to evaluate the amount of propellant required for the on-orbit servicing spacecraft that can upgrade on-orbit satellites. Specially, one servicing spacecraft (SSc) is considered to be initially in the same direction as the target satellite in an adjacent orbit. The SSc then rendezvous with the target satellite and services it. An initial sizing method is presented with an approximate guidance method that the solution process composes analytic solutions for two thrust arcs and one Keplerian free-flight phase, and a homogeneous central field is utilized to approximate the Newtonian field in the boost-phase. It is shown that the approximate guidance method is simple and the precision of the solutions is admitted for the initial sizing.
Yinghong Qi Yanjun Xing Xibin Cao
Research Center of Satellite Technology Harbin Institute of Technology Harbin,Heilongjiang 150080 China
国际会议
深圳
英文
1263-1266
2008-12-10（万方平台首次上网日期，不代表论文的发表时间）