A baseline system configuration of a reusablesounding rocket is presented. The vehicle adopts avertical take-off and vertical landing (VTVL)system to minimize ground support equipments(GSE) and turn-around time. An integratedpropulsion system which consists of four 2-ton-classliquid-hydrogen / liquid-oxygen (LH2/LOX)expander cycle engines, a gaseous-hydrogen /gaseous-oxygen (GH2/GOX) reaction controlsystem (RCS) and an auxiliary power unit (APU)are introduced in order to simplify groundoperations and reduce turn-around time. The vehicleis designed to meet the requirements of carrying100kg payload on a round trip to 120km andrepeating the mission within 24 hours.
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