Proximity Operations of On-Orbit Servicing Spacecraft using an Eccentricity/Inclination Vector Separation
Proximity Operations of On-Orbit Servicing Spacecraft using an Eccentricity/Inclination Vector Separation
复制标题
使用偏心率/倾角矢量分离的在轨服务航天器的邻近操作
DOI：
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发表时间：
2011
期刊：
影响因子：
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通讯作者：
S. D’Amico
中科院分区：
文献类型：
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作者：
J. Spurmann;S. D’Amico
本文研究了一种能够实现这一要求的接近操作概念
This paper investigates a proximity operations concept able to realize the demanding
requirements for on-orbit servicing spacecraft, while providing an efficient collision avoidance
strategy and reduced propellant consumption. In contrast to a traditional rendezvous approach
where the evaluation of the collision risk is only based on considerations done in the orbital plane,
here a relative eccentricity/inclination vector separation concept is proposed which promises
improved flexibility, robustness and reduced inter-spacecraft separations at a minimal collision
risk. In this paper the novel proximity operations concept, originally developed for geostationary
satellites and already used to operate low Earth orbit formations, is adopted to support far and mid
range operations of on-orbit servicing non-cooperative vehicles. After addressing the effects of the
relevant differential perturbations, suitable nominal relative motion geometries are derived based
on a real-world navigation accuracy analysis. Radar tracking data and GPS navigation solutions
for the client and servicer satellites respectively are used to trade minimum safety separations and
characteristics of the rendezvous entry gate. Finally a fuel-efficient formation keeping and
reconfiguration strategy is designed based on analytical solutions of the proposed linear motion
model