Continuous maneuvers for spacecraft formation flying reconfiguration using relative orbit elements

被引：23

作者：

Di Mauro, G. ^{[1
]}

Bevilacqua, R. ^{[1
]}

Spiller, D. ^{[2
]}

Sullivan, J. ^{[3
]}

D'Amico, S. ^{[3
]}

机构：

[1] Univ Florida, Dept Mech & Aerosp Engn, ADAMUS Lab, 939 Sweetwater Dr, Gainesville, FL 32611 USA

[2] Sapienza Univ Rome, Dept Mech & Aerosp Engn, Via Eudossiana 18, I-00184 Rome, Italy

[3] Stanford Univ, Dept Aeronaut & Astronaut Engn, Stanford Space Rendezvous Lab, 496 Lomita Mall, Stanford, CA 94305 USA

来源：

ACTA ASTRONAUTICA | 2018年 / 153卷

关键词：

Spacecraft formation flying reconfiguration; Relative orbit elements; Relative motion control; FORMATION ESTABLISHMENT;

D O I：

10.1016/j.actaastro.2018.01.043

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

This paper presents the solutions to the spacecraft relative trajectory reconfiguration problem when a continuous thrust profile is used, and the reference orbit is circular. Given a piecewise continuous thrust profile, the proposed approach enables the computation of the control solution by inverting the linearized equations of relative motion parameterized using the mean relative orbit elements. The use of mean relative orbit elements facilitates the inclusion of the Earth's oblateness effects and offers an immediate insight into the relative motion geometry. Several reconfiguration maneuvers are presented to show the effectiveness of the obtained control scheme.

引用

页码：311 / 326

页数：16

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