充液航天器变质量液体大幅晃动的SPH分析方法

SPH Method for Large-amplitude Liquid Sloshing with Variable Mass in Liquid-filled Spacecraft

本文基于非惯性系下的光滑粒子流体动力学(SPH)方法,在以虚粒子设置缓冲层的开口边界处理方法基础上,提出一种流出流量可控的出口边界处理方法,能够根据当前时刻航天器的姿态信息和充液比,计算该动力学时间步下变质量液体晃动对航天器产生的作用力和作用力矩,使得航天器系统动力学的闭环仿真成为可能。最后,通过与计算流体动力学(CFD)商业软件Flow-3d的计算结果进行对比,用不同工况下的算例验证了该变质量液体晃动动力学分析方法的有效性。

In this paper,based on the non-inertial smoothed particle hydrodynamics(SPH)which is a Lagrangian mesh-less method,a numerical method regarding outlet boundary conditions is proposed to limit the flux at the outlet boundary,which is an extension of the methods proposed to the treatment of open boundary conditions based on the buffer layers.According to the spacecraft attitude information and liquid-filled ratio at the current time,the SPH solver can calculate the sloshing force and moment exerted by variable-mass liquid against the spacecraft during the dynamic time step.The SPH solver can be embedded in the closed-loop dynamics simulation of the whole spacecraft.Finally,in order to verify the validity of the method,the results from the SPH method are compared with those obtained by a commercial computational fluid dynamics(CFD)software,Flow-3d for different sloshing cases.