Analysis of CZ-3A 3.RD subclass residual propellant discharge plume

Along with quick development for aerospace technology, various space activities increased more and more. As a result space debris problems increasingly aggravate. Meteoroid and cosmic dust debris and artificial debris mainly constitute space debris. One of the main sources for space debris is the end class rocket's exploding on its orbit. At present, the space debris has seriously threatened space exploitation and space safety. It is imperative for each aerospace country to reduce space debris's quantity as far as possible during the space activity. In order to reduce the space debris' increase, one of the important measures is to discharge the end class rocket's residual propellant for eliminating the explode source. However, plume particles due to discharging may become tiny space debris, which possibly impinge on the satellite. Therefore, it is very necessary to research the end class rocket's residual propellant discharge and plume analysis. China has paid high attention to the space debris problem. In order to reduce the space debris, a discharge has been applied in the residual propellant of CZ-3A launch vehicle 3rd subclass cryogenic tank. In this paper, the flow inside pipeline of the residual propellant along CZ-3A launch vehicle 3rd subclass cryogenic tank discharge pipeline and discharge plume have been calculated.