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以航天发射场液氢加注系统阀门为研究对象,从仿真角度研究加注稳态过程中,阀门在不同失效程度时,压力和流量变化对加注系统的影响。
Taking the liquid hydrogen injection valve of space launch site as the research object, the influence of the pressure and the change of flow rate on the filling system during the steady-state filling process was investigated from the simulation point of view.