Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : December 17, 2020 - December 18, 2020
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.
