Preliminary Design of the Hybrid Air-launching Rocket for Nanosat

Abstract

Air-Launching is an effective method that can launch the 'Nanosat' for low launching cost. In this study, the preliminary design of the air-launching micro rocket was performed. Mission and trajectory optimization was performed and the propulsion system was designed based on the mission design. A supersonic air launching rocket with total weight of 830.95 kg, the payload weight of 3.56 kg and the propulsion system length of 5.89 m has been designed.