Feedback control law of solar sail with variable surface reflectivity at Sun-Earth collinear equilibrium points

被引:34
作者
Niccolai, Lorenzo [1 ]
Mengali, Giovanni [1 ]
Quarta, Alessandro A. [1 ]
Caruso, Andrea [1 ]
机构
[1] Univ Pisa, Dept Civil & Ind Engn, I-56122 Pisa, Italy
关键词
Solar sail; Artificial equilibrium point; Sun's observation mission; Reflectivity control; TRAJECTORY DESIGN; ORBIT CONTROL; MISSION; MODEL; SYSTEM; IMPACT;
D O I
10.1016/j.ast.2020.106144
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
A solar sail generates thrust without consuming any propellant, so it constitutes a promising option for mission scenarios requiring a continuous propulsive acceleration, such as the maintenance of a (collinear) L-1-type artificial equilibrium point in the Sun-[Earth+Moon] circular restricted three-body problem. The usefulness of a spacecraft placed at such an artificial equilibrium point is in its capabilities of solar observation, as it guarantees a continuous monitoring of solar activity and is able to give an early warning in case of catastrophic solar flares. Because those vantage points are known to be intrinsically unstable, a suitable control system is necessary for station keeping purposes. This work discusses on how to stabilize an L-1-type artificial equilibrium point with a solar sail by suitably adjusting its lightness number and thrust vector orientation. A full-state feedback control law is assumed, where the control gains are chosen with a linear-quadratic regulator approach. In particular, the numerical simulation results show that an L-1-type artificial equilibrium point can be maintained with small required control torques, by using a set of reflectivity control devices. (C) 2020 Elsevier Masson SAS. All rights reserved.
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页数:13
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