液体推进剂晃动力效应传递函数模型及其应用

To predict and regulate the space vehicle’s undesirable coupling motion produced by tiny amplitude sloshing of liquid propellant, a transfer function model identification study is carried out based on the findings of numerical calculations. For an example of a horizontally placed kerosene tank in a vehicle, during the level flight in the re-entry phase, a force effect transfer function description model is established with the range of rotational motion of interest, based on which a sloshing suppression design is carried out to increase sloshing damping and weaken the impact of sloshing on flight. The findings show that the transfer function can capture the impacts of the liquid propellant sloshing force, which can be utilized to anticipate space vehicle flight characteristics and design sloshing suppression.