Aerothermodynamics Research For Long-march Reusable Launch Vehicle Vehicle
- Paper number
IAC-07-D2.5.09
- Author
Dr. Tao Du, China Academy of Launch Vehicle Technology, China
- Coauthor
Dr. Yong Yang, China Academy of Launch Vehicle Technology, China
- Year
2007
- Abstract
In order to strengthen Chinese innovative technology competence of launch vehicle continuously and meet market needs in the future, CALT must take account of system architectures and technologies for Reusable Launch Vehicle (RLV), which is one of the choices after the new generation Long March (LM) launch vehicles in the future. The first generation LM RLV will be rocket-powered, vertical taking-off, horizontal landing, partially reusable two-stage-to-orbit (TSTO). The ultimate goal of LM launch vehicles is single-stage-to-orbit (SSTO). Aerothermodynamics, especially for orbiter glided entry, is the one of the main key technologies for RLV. According the request of the first generation partially reusable LM RLV, carry out research on the key Aerothermodynamics problems, which include reusable aerodynamic configure, glided re-entry aerothermodynamics characteristic, wind tunnel experiment technologies and numerical simulation technologies, flight demonstration technologies and aerodynamic database management technologies. Based on these work, provide the winged-body aerodynamic shape which meets system request and flight mission; research the complicated aerodynamic phenomena and improve the ability of predicting aerodynamic characteristic; advance the high capability ground wind tunnel experiment technologies and numerical simulation technologies; utilizing modern database technologies to build aerodynamic data management database for RLV and form the aerodynamic design data book for RLV ultimately.
- Abstract document
- Manuscript document
IAC-07-D2.5.09.pdf (🔒 authorized access only).
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