宇宙機液体推進システムを対象とした過渡推力変動予測モデルの検討

抄録

In this study, a dynamic response model of a propellant valve has been developed, to build a system-level integrated model that enables accurately prediction of transient thrust fluctuations of a spacecraft liquid propulsion system. The purpose of this study is to achieve a more accurate prediction of flow rate than before by taking into the account the effect of upstream pressure changes on the open-close response of the valve. The upstream pressure of the valve varies greatly due to the drop in tank pressure or crosstalk. By introducing the proposed model to a one-dimensional system analysis of the spacecraft propulsion system, the propellant flow rate of various operational conditions can be predicted with high accuracy. In order to validate the proposed model, a verification test in a simplified single pipe system of the spacecraft propulsion system was conducted. The prediction error of the flow rate to the thruster has been reduced from about 72.6 % in the conventional model to about 5.73 % in the proposed model.