TY - JOUR

T1 - Orbital Maneuvering in the Vicinity of Collinear Libration Points Using Light Pressure Forces

AU - Shymanchuk, D. V.

AU - Shmyrov, A. S.

AU - Shmyrov, V. A.

N1 - Publisher Copyright: © 2021, Pleiades Publishing, Inc.

PY - 2021/10

Y1 - 2021/10

N2 - Abstract: The controlled motion of a spacecraft with a solar sail in interplanetary space near the collinear libration points L1 and L2 of the Sun–Earth system is investigated. The equations of the circular restricted three-body problem and their modifications are used to describe the orbital motion. We present a technique for constructing the orbital motion control laws and provide an estimate of the controllability region when solving the problem of stabilization or long-term spacecraft keeping in the vicinity ofL1 and L2 . This technique is based on the solution of the control problem for a linearized model of the equations of orbital motion and the transfer of results to the nonlinear case. Such a technique for the construction of control laws extends the possibilities both in solving the problems of motion stabilization and in solving the problems of maneuvering in the vicinity of a collinear libration point. We estimate the controllability region for a spacecraft with a solar sail and present the trajectories of possible spacecraft motion that are provided by the solar sail orientation when flying from the vicinity of a collinear libration point. It is in these regions of space that the light pressure force can have a significant efficiency due to the relatively small magnitude of the gravitational force. As an example, we consider a model of a spacecraft with a solar sail whose sail area-to-mass ratio corresponds to the spacecraft from the implemented IKAROS project and is less than that of the CubeSat spacecraft from the implemented LightSail-2 project by an order of magnitude.

AB - Abstract: The controlled motion of a spacecraft with a solar sail in interplanetary space near the collinear libration points L1 and L2 of the Sun–Earth system is investigated. The equations of the circular restricted three-body problem and their modifications are used to describe the orbital motion. We present a technique for constructing the orbital motion control laws and provide an estimate of the controllability region when solving the problem of stabilization or long-term spacecraft keeping in the vicinity ofL1 and L2 . This technique is based on the solution of the control problem for a linearized model of the equations of orbital motion and the transfer of results to the nonlinear case. Such a technique for the construction of control laws extends the possibilities both in solving the problems of motion stabilization and in solving the problems of maneuvering in the vicinity of a collinear libration point. We estimate the controllability region for a spacecraft with a solar sail and present the trajectories of possible spacecraft motion that are provided by the solar sail orientation when flying from the vicinity of a collinear libration point. It is in these regions of space that the light pressure force can have a significant efficiency due to the relatively small magnitude of the gravitational force. As an example, we consider a model of a spacecraft with a solar sail whose sail area-to-mass ratio corresponds to the spacecraft from the implemented IKAROS project and is less than that of the CubeSat spacecraft from the implemented LightSail-2 project by an order of magnitude.

KW - controlled motion

KW - invariant manifold

KW - libration point

KW - maneuvering

KW - restricted three-body problem

KW - solar sail

UR - http://www.scopus.com/inward/record.url?scp=85125254311&partnerID=8YFLogxK

U2 - 10.1134/S1063773721100066

DO - 10.1134/S1063773721100066

M3 - Article

AN - SCOPUS:85125254311

VL - 47

SP - 710

EP - 719

JO - Astronomy Letters

JF - Astronomy Letters

SN - 1063-7737

IS - 10

ER -