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复杂充液航天器的晃动及其对控制系统的影响是当前空间高技术的重要问题。 本文首先由力学变分原理导出充液复杂系统的方程式,其中包括流体力学方程和相应的边界条件,以及弹性连续介质力学方程;特别是,考虑了强毛细作用力的影响。其次,考查了微重条件下带有隔板的贮箱内的液体晃动、带有网孔隔板腔体内的液体晃动和粘弹性隔板对抑制晃动的作用。另外,本文将分析带有多腔充液自旋卫星的姿态稳定性,以及晃动、液体涡旋、贮箱偏置,能量耗散和哥氏加速度对卫星运动的影响。最后,讨论了多体系统充液挠性空间飞行器的稳定性问题。 同时,本文给出了数值计算结果和某些试验结果,并与理论分析作了对比。
The rocking of complex liquid-filled spacecraft and its impact on the control system are important issues in the current high-tech space. In this paper, firstly, the equations of fluid-filled complex system are derived from the mechanical variational principle, including the hydrodynamic equations and the corresponding boundary conditions, as well as the elastic continuum mechanics equations; in particular, the influence of the strong capillary forces is considered. Secondly, the sloshing of the liquid in the tank with the separator under the condition of slight weight, the shaking of the liquid in the chamber with the mesh separator and the effect of the viscoelastic separator on the suppression of sloshing were examined. In addition, this paper will analyze the attitude stability of satellite with multi-cavity liquid-filled spin as well as the influence of sloshing, liquid vortex, tank bias, energy dissipation and Coriolis acceleration on satellite motion. Finally, the stability of multi-body system liquid-filled flexible spacecraft is discussed. At the same time, the numerical calculation results and some experimental results are given and compared with the theoretical analysis.