Modeling and Simulation of Attitude Dynamics for Out-of-Control Spacecraft with Multiple Combined Disturbances

Abstract

This paper investigates the attitude dynamic characteristics of uncontrolled spacecraft under multisource composite disturbances. Four typical symmetric and asymmetric structural satellites, namely cubic, cylindrical, panel, and thin-rod configurations, are selected. Based on Euler's dynamic equations and the theorem of conservation of angular momentum, the inertia models and attitude dynamic models under ideal conditions are established for these four typical configurations. On this basis, space environmental disturbances including atmospheric drag, Earth's magnetic field, gravitational gradient, solar radiation pressure, and space debris impact, as well as spacecraft component disturbance torques including energy dissipation and flywheel vibration, are introduced. Meanwhile, considering the influence of flexible appendages, an attitude dynamic model under composite disturbances is constructed. Numerical simulations are conducted by setting up three typical on-orbit scenarios, and the evolution characteristics of satellite attitude under multi-source coupled disturbances are analyzed. The results can provide theoretical support for space target monitoring and on-orbit service missions.