DocumentCode
3387164
Title
Preliminary Design of the Hybrid Air-launching Rocket for Nanosat
Author
Jae-Woo Lee ; Kyung-Ho Noh ; Yung-Hwan Byun ; Bong-Kyo Park
Author_Institution
Konkuk Univ., Seoul
fYear
2007
fDate
26-29 Aug. 2007
Firstpage
290
Lastpage
295
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.
Keywords
aerospace propulsion; optimisation; rockets; hybrid air-launching rocket; optimization; propulsion system; Aerodynamics; Costs; Design optimization; Payloads; Process design; Propulsion; Rockets; Satellites; Space technology; Vehicles;
fLanguage
English
Publisher
ieee
Conference_Titel
Computational Science and its Applications, 2007. ICCSA 2007. International Conference on
Conference_Location
Kuala Lampur
Print_ISBN
978-0-7695-2945-5
Type
conf
DOI
10.1109/ICCSA.2007.16
Filename
4301157
Link To Document