Studies on the Liquid Sloshing and Rigid-Liquid-Flexible Coupling Dynamics of Spacecraft

The numerical model of the rigid-liquid-flexible coupling system of the spacecraft is established, and the flexible appendages are simplified as Euler-Bernoulli beams. The staggered algorithm is adopted to simulate the coupling system, and the liquid module, the rigid body module, and the flexible appendage module are solved by two-step iteration. The coupling model is verified by comparing with previous results. Furthermore, the response of the rigid-liquid-flexible coupling spacecraft under orbital driving forces is studied, and it is found that in the condition of the simulation example, the sloshing of the liquid and the vibration of the flexible appendages influence each other, and there exists complex coupling mechanism between the liquid, the rigid body, and the flexible appendages.