The Separation Dynamic Analyse Of The Satellite Considering The Propellant-sloshing

The 6-DOF rigid dynamic model has been generally applied in the dynamic analyses of the separation process of SL(satellite)/LV(launch vehicle) at present. However, the separation process is greatly affected by the propellant-sloshing. Most of the research is holding on the qualitative analysis in this field by now. At the background of launching Apstar--â…£by Long Mach-3B, the SL/LV separation process considering the propellant-sloshing of the tank of the satellites is analyzed in quantify for the first time in domestic. The main work of this dissertation is presented as follows:According to the requirements of the SL/LV interface, the mechanism and the electricity interface are designed. Then the separation equipment is primarily devised by the designed results of the interface and the separation demands.The equations of motion and Euler dynamic equations for combined SL/LV body are constituted. And the dynamic equations of propellant-sloshing in the pitch and yaw channel are established.The characteristics of near separation such as the collision boundary of the separation, the attitude angle, the rate of attitude angle and the separation velocity after separation are analyzed based on the design of SL/LV interface and the separation equipment.The analyzing results considering the propellant-sloshing are compared with that of using the rigid body model. The comparison indicates that the propellant-sloshing in the tank of the satellite has great effect on the separation attitude.It is innovative that the sloshing mass of the propellant is considered in the dynamic analyses in SL/LV separation process. The development of this paper is a good reference to the SL/LV separation analyses for the series of Long March Family of Launch vehicle of our country.