摘要
航天器在轨分离属于空间微重力环境下的多体动力学,而液体晃动属于复杂的非线性动力学,本文采用光滑粒子流体动力学方法(SPH方法)模拟航天器贮箱中带有自由表面的液体非线性晃动,建立了含贮箱液体晃动的航天器耦合分离动力学模型,通过航天器分离动力学及流-固耦合动力学分析,解决了贮箱燃料液体大幅晃动对航天器分离姿态的影响问题,给出了液体晃动对航天器产生的干扰力和力矩,对比了考虑液体晃动和假设贮箱液体为刚体得到航天器分离姿态的差异,不同液面高度对航天器分离姿态、干扰力和力矩的影响情况,分析结果为弹簧分离机构的优化设计和分离安全性设计提供参考,同时提高了航天器在轨姿态控制设计的可靠性.
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.
作者
刘汉武
张华
胡震宇
王金童
禹志
袁勇
LIU HanWu;ZHANG Hua;HU ZhenYu;WANG JinTong;YU Zhi;YUAN Yong(Aerospace Systems Engineering Shanghai,Shanghai 201109,China;Shanghai Key Laboratory of Spacecraft Mechanism,Shanghai 201108,China;Joint Laboratory of Planetary Terramechanics and Bionic Engineering,Shanghai 201109,China)
出处
《中国科学：技术科学》
EI
CSCD
北大核心
2021年第8期938-947,共10页
Scientia Sinica(Technologica)
基金
国家中长期科技发展规划重大专项工程资助项目。
