Active control of flexible spacecraft in orbit based on partial differential equations.

ABSTRACT: Flexible spacecraft possess the ability to adapt to complex environments and use energy more efficiently, offering enhanced flexibility and stability in space missions, particularly in tasks with significant external disturbances such as deep space exploration and satellite attitude control. However, vibration suppression in flexible spacecraft remains a critical challenge. This study addresses the problem of vibration suppression in flexible spacecraft systems under external disturbances and input constraints. First, a partial differential equation (PDE) with boundary initial conditions is derived using Hamilton's principle, accurately describing the dynamic characteristics of the flexible structure. A backstepping controller based on the Nassbaum function and a disturbance observer is th

SUBMITTER: Zhang B 

PROVIDER: S-EPMC12422462 | biostudies-literature | 2025

REPOSITORIES: biostudies-literature