TY - JOUR
T1 - Analytical propagation solution for planet-displaced orbit in the presence of third-body perturbations
AU - Zhou, Xingyu
AU - Qiao, Dong
AU - Li, Xiangyu
AU - Macdonald, Malcolm
N1 - Publisher Copyright:
© 2025 IAA
PY - 2025/4
Y1 - 2025/4
N2 - Planet-displaced orbits (PDOs) play an important role in space missions such as solar observation, gravitational wave detection, and near-Earth asteroid detection. To propagate the PDOs accurately and efficiently, this paper develops an analytical solution considering the Solar central gravitational force and the time-varying third-body perturbation of the corresponding planet. First, an approximated third-body perturbation model is established based on the planet displacement angle (PDA), which is found to be the core variable affecting the evolution of the orbit. The model can describe both secular and periodic terms of the third-body perturbation accurately. Then, based on the established third-body perturbation model, a two-step procedure is developed to iteratively derive the analytical orbit propagation solution of the PDO via the Picard iteration method. The analytical solution is successfully applied to propagate the orbit in an Earth-trailing orbit case: the Laser Interferometer Space Antenna (LISA). Simulation shows that the analytical orbit propagation solution can accurately predict the orbit in both the long-time and short-time cases. The relative error is less than 0.1% in 10 years. The proposed analytical solution can be potentially useful in designing and optimizing PDOs.
AB - Planet-displaced orbits (PDOs) play an important role in space missions such as solar observation, gravitational wave detection, and near-Earth asteroid detection. To propagate the PDOs accurately and efficiently, this paper develops an analytical solution considering the Solar central gravitational force and the time-varying third-body perturbation of the corresponding planet. First, an approximated third-body perturbation model is established based on the planet displacement angle (PDA), which is found to be the core variable affecting the evolution of the orbit. The model can describe both secular and periodic terms of the third-body perturbation accurately. Then, based on the established third-body perturbation model, a two-step procedure is developed to iteratively derive the analytical orbit propagation solution of the PDO via the Picard iteration method. The analytical solution is successfully applied to propagate the orbit in an Earth-trailing orbit case: the Laser Interferometer Space Antenna (LISA). Simulation shows that the analytical orbit propagation solution can accurately predict the orbit in both the long-time and short-time cases. The relative error is less than 0.1% in 10 years. The proposed analytical solution can be potentially useful in designing and optimizing PDOs.
KW - Analytical orbit propagation
KW - LISA
KW - Picard iteration method
KW - Planet displacement angle
KW - Planet-displaced orbits
KW - Third-body perturbation
UR - http://www.scopus.com/inward/record.url?scp=85215091543&partnerID=8YFLogxK
U2 - 10.1016/j.actaastro.2025.01.019
DO - 10.1016/j.actaastro.2025.01.019
M3 - Article
AN - SCOPUS:85215091543
SN - 0094-5765
VL - 229
SP - 149
EP - 160
JO - Acta Astronautica
JF - Acta Astronautica
ER -