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Simulation analysis of liquid sloshing separation in spacecraft with tank based on SPH method

The separation of spacecraft in orbit is based on multibody dynamics in a space microgravity environment, while liquid sloshing is studied based on complex nonlinear dynamics. In this study, the smoothed particle hydrodynamics (SPH) method was used to simulate liquid sloshing with a free surface in a spacecraft tank, and the separation dynamic model of the spacecraft and liquid fuel was established. Through the analysis of spacecraft separation dynamics and fluid–structure coupling dynamics, the problem of the influence of sloshing of the liquid in the fuel tank on spacecraft separation attitude was solved. The interference force and torque of liquid sloshing on the spacecraft can be obtained from the model fluid–structure coupling dynamics calculation. The separation attitude of spacecraft with liquid sloshing in the tank is different from that based on a rigid body assumption. The liquid levels affect the calculation results of spacecraft separation attitude, interference force, and torque. The analysis results provide a reference for the optimization design and separation safety design of the spring separation mechanism and improve the reliability of spacecraft attitude control design.