Computer Science – Performance
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.929t&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Computer Science
Performance
Scientific paper
To meet the ever-expanding requirements of satellite customers, a new generation launch vehicle of Long-March (LM) family is being studied according to theprinciples of low-cost, high-reliability, and maximum flexibility. With reducing prelaunch processing times, the launch system will strengthen the capability of providing international commercial launching services in the future. The new generation launch system is constructed with some standard modules, while featuring two types of newly developed engines and three new modules with non-toxic, non-polluting propellant. Based on the three modules, 5-m module powered by two 50-ton-thrust engines which burn liquid hydrogen (LH2) and liquid oxygen (LO2), 3.35-m module powered by two 120-ton-thrust engines which burn LO2 and kerosene (KO), and 2.25-m module powered by one 120-ton-thrust engine, first can combine into a serial large-scale launch vehicles with 5-m-dia common core. By modified the modules, next combine into medium launch vehicles with 3.35-m-dia core and a small launch vehicle with 2.25-m-dia core. Then a new group of launch vehicles will be formed to accommodate a wide range of performance requirements, which provide a capable of delivering payloads ranging from 1.5-14 ton to geosynchronous transfer orbit (GTO) and up to 25 ton to low earth orbit (LEO). This paper will highlight the design principles, system concept and serial configurations for the new generation launch system.
Cheng Tangming
Tang Yihua
Wang Xiaojun
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