Formation control of multiple LEO nano-satellites using differential drag and lift
HU Yuan-dong
LU Zheng-liang
LIAO Wen-he
ZHANG Xiang
Abstract：A formation control method that uses aerodynamic forces is studied to solve the problem of insufficient orbit maneuverability of LEO Nano-satellite.An extension scheme for the multi-satellite formation is innovatively proposed based on windward attitude adjustment,in which the linear control is realized by partial linearization.The mapping rela-tionship between attitude angles and aerodynamic forces is studied,and it is linearized in a chosen region.The dynamic model of differential drag and lift coupling control is established with attitude angle as control input.Thereafter,the con-trollability and disturbance of this linear underactuated system is analyzed,and a feedback control law is designed by using the linear matrix inequalities(LMI)method considering input constraints.Finally,numerical simulations are conducted for a four-satellite formation with two configurations,and reveal that the accuracy of the stable control is up to±0.4 m.Thus,the feasibility of the proposed formation control scheme and the effectiveness of the control algorithm are verified.
Keywords：formation controlaerodynamic forcesdifferential drag and liftinput saturationlinear matrix inequali-ties(LMI)
Publication Date：2024-10-28
Online Publishing Date：2025-08-15(First online date of this platform, not the publication date of the document)
Pages：10( 1801-1810 )