TY - JOUR
T1 - Optimal Scheme of Pyramid Deorbit Sail in the Atmosphere and Solar Environment
AU - Zhang, Ruonan
AU - Zhang, Jingrui
AU - Yang, Keying
N1 - Publisher Copyright:
© 2024 Institute of Electrical and Electronics Engineers Inc.. All rights reserved.
PY - 2024
Y1 - 2024
N2 - –For the mitigation of space debris, post-mission disposal is deemed an essential measure in Low Earth Orbit (LEO). One possible way of doing this is to enlarge the effective area by using the membrane sail device, so as to enlarge the atmospheric drag (AD) and solar radiation pressure (SRP), and then accelerate the deorbit process. The effective membrane sail area is mainly affected by spacecraft attitude which exhibits different stable solutions in different altitudes. When descending, the space can be divided into the SRP dominated region, the mix region and the AD dominated region in which the mixed region is where the SRP and AD forces are comparable. Thus, for a deorbit mission in LEO, it is necessary to propose an optimal scheme to achieve rapid and stable deorbit process. In this paper, a precise dynamics model of the pyramid deorbit sail is established with the consideration of multi-source disturbances, orbit-attitude coupling and shielding effects. And then, an optimal deorbit scheme is proposed in the above-mentioned three regions to increase the deorbit efficiency. Specifically, in the AD and SRP dominated regions, analytical expressions are derived to evaluate the attitude stabilities and offer optimal configuration design solutions. In the mixed region, an optimal control system is designed with the objects of minimum maneuver as well as maximum deorbit efficiency. By using these configuration design and the attitude control methods, a fast and stable deorbit process can be achieved for LEO satellites.
AB - –For the mitigation of space debris, post-mission disposal is deemed an essential measure in Low Earth Orbit (LEO). One possible way of doing this is to enlarge the effective area by using the membrane sail device, so as to enlarge the atmospheric drag (AD) and solar radiation pressure (SRP), and then accelerate the deorbit process. The effective membrane sail area is mainly affected by spacecraft attitude which exhibits different stable solutions in different altitudes. When descending, the space can be divided into the SRP dominated region, the mix region and the AD dominated region in which the mixed region is where the SRP and AD forces are comparable. Thus, for a deorbit mission in LEO, it is necessary to propose an optimal scheme to achieve rapid and stable deorbit process. In this paper, a precise dynamics model of the pyramid deorbit sail is established with the consideration of multi-source disturbances, orbit-attitude coupling and shielding effects. And then, an optimal deorbit scheme is proposed in the above-mentioned three regions to increase the deorbit efficiency. Specifically, in the AD and SRP dominated regions, analytical expressions are derived to evaluate the attitude stabilities and offer optimal configuration design solutions. In the mixed region, an optimal control system is designed with the objects of minimum maneuver as well as maximum deorbit efficiency. By using these configuration design and the attitude control methods, a fast and stable deorbit process can be achieved for LEO satellites.
KW - Analytical stability analysis
KW - Configuration design
KW - Optimal deorbit scheme
KW - Pyramid deorbit sail
UR - http://www.scopus.com/inward/record.url?scp=85210276123&partnerID=8YFLogxK
U2 - 10.1109/TAES.2024.3504488
DO - 10.1109/TAES.2024.3504488
M3 - Article
AN - SCOPUS:85210276123
SN - 0018-9251
JO - IEEE Transactions on Aerospace and Electronic Systems
JF - IEEE Transactions on Aerospace and Electronic Systems
ER -