TY - GEN
T1 - Fuel-Optimal Spacecraft Rendezvous Mission Planning Method Considering Orbital Perturbation
AU - Zhu, Jiukai
AU - Deng, Wudong
AU - Sun, Leixiang
AU - Guo, Yanning
N1 - Publisher Copyright:
© 2023 Technical Committee on Control Theory, Chinese Association of Automation.
PY - 2023
Y1 - 2023
N2 - A fuel-optimal spacecraft rendezvous mission planning method considering orbital perturbation is proposed to address the fuel consumption problem of spacecraft completing rendezvous missions. Firstly, considering the constraints of total mission time and desired position, a model of orbital perturbation spacecraft considering non-spherical and atmospheric drag is constructed, and the adaptation function of fuel consumption for single-loop Lambert transfer considering orbital perturbation is designed. Based on this fitness function, an improved particle swarm optimization algorithm is designed to determine the first applied impulse time, the second applied impulse time, and the rendezvous time in the rendezvous mission planning, and then solve the two applied impulse sizes with the minimum fuel consumption to complete the spacecraft rendezvous mission. Finally, simulation experiments with a set of spacecraft rendezvous missions are conducted to verify the practicality and effectiveness of the method.
AB - A fuel-optimal spacecraft rendezvous mission planning method considering orbital perturbation is proposed to address the fuel consumption problem of spacecraft completing rendezvous missions. Firstly, considering the constraints of total mission time and desired position, a model of orbital perturbation spacecraft considering non-spherical and atmospheric drag is constructed, and the adaptation function of fuel consumption for single-loop Lambert transfer considering orbital perturbation is designed. Based on this fitness function, an improved particle swarm optimization algorithm is designed to determine the first applied impulse time, the second applied impulse time, and the rendezvous time in the rendezvous mission planning, and then solve the two applied impulse sizes with the minimum fuel consumption to complete the spacecraft rendezvous mission. Finally, simulation experiments with a set of spacecraft rendezvous missions are conducted to verify the practicality and effectiveness of the method.
KW - Lambert transfer
KW - Orbital perturbation
KW - Particle swarm optimization algorithm
KW - Spacecraft rendezvous
UR - https://www.scopus.com/pages/publications/85175569144
U2 - 10.23919/CCC58697.2023.10239947
DO - 10.23919/CCC58697.2023.10239947
M3 - 会议稿件
AN - SCOPUS:85175569144
T3 - Chinese Control Conference, CCC
SP - 1714
EP - 1719
BT - 2023 42nd Chinese Control Conference, CCC 2023
PB - IEEE Computer Society
T2 - 42nd Chinese Control Conference, CCC 2023
Y2 - 24 July 2023 through 26 July 2023
ER -