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本文以热响应法测量航天器微重力条件下贮箱推进剂剩余质量为背景,建立了航天器贮箱内外热环境耦合作用下的整体热分析模型,通过将航天器贮箱外部热环境视为第二类浮动热边界条件,实现贮箱气液两相分布下的热分析解耦计算,为热响应法提供精确的温度场计算方法。采用该方法,针对热响应法测量微重力条件下某航天器贮箱内部推进剂质量所需的温度场分布,通过数值仿真获得了空间在轨阶段,热响应法加热工作时贮箱内外热环境整体耦合下的温度场分布,并依据特定检测点的瞬态温度变化,反演得到了剩余推进剂的质量。研究发现采用热响应法测量推进剂质量时,贮箱温度场不仅受贮箱内部加热影响,在轨外部热环境也会明显影响贮箱壁面温度的均匀性。
In this paper, the thermo-responsive method is used to measure the residual mass of tank propellant under the microgravity condition of spacecraft. The global thermal analysis model under the coupling of the thermal environment inside and outside the spacecraft is established. By considering the external thermal environment of the spacecraft tank as The second type of floating thermal boundary conditions can realize the thermal analysis and decoupling calculation under the gas-liquid two-phase distribution of the tank, and provide an accurate calculation method for the temperature field for the thermal response method. The method is applied to measure the temperature field distribution of propellant in a spacecraft tank under the microgravity condition by means of the thermal response method. The numerical simulation results show that the thermal environment inside and outside the tank The overall temperature field distribution under coupling, and based on the transient changes in the temperature of specific detection points, the quality of the remaining propellants were retrieved. The results show that when using the thermal response method to measure the propellant mass, the temperature field of the tank is not only affected by the internal heating of the tank, but also the temperature of the tank wall.