In order to solve the problem of attitude instability caused by space debris
impact on flat satellites during in orbit operation, this paper systematically
analyzes the attitude stability capability of typical flat satellites under the
disturbance of space debris impact angular velocity. Firstly, based on the
composition and open parameters of typical flat satellites, this paper sets the
research object and solves its size, centroid position, and moment of inertia
matrix around the centroid; Secondly, the attitude control system of the four
inclined flywheel was analyzed in detail, and a satellite attitude simulation
environment was established to determine the simulation variables. Thirdly,
based on the simulation scenario of satellite attitude control, the attitude
control effect of typical flat satellites with different initial angular
velocity disturbances was analyzed, which is not only applicable to single axis
initial angular velocity disturbance control, but also to multi axis systems
simultaneously affected by initial angular velocity disturbances. The analysis
results indicate that the satellite has poor disturbance control ability on the
X/Y axis of the system, but good control effect on the Z axis. Finally, based on
the results of attitude simulation analysis, the critical impulse of a typical
flat satellite solar panels under unstable conditions was calculated, and a
contour map of the critical impulse was drawn. The research results of this
article can provide theoretical support for the design of space protection and
attitude control systems for typical flat panel satellite re-entry
operations.