Current situation at space transportation system market is characterized by increased volume of payload injections into geostationary orbit and also into low and middle near-Earth orbits [1]. Taking into consideration the segment of civilian satellite with mass 10 to 200 kg and cost less 200 million dollars and tendency of space market makers to employ existent launch vehicles (LV) and medium range launch vehicles intended for ejecting 2 to 10 tons payload, in it interesting to examine new configurations of LV nose fairing [1]. The main feature of this tendency is possibility to inject various type satellites or a number of single-line satellites into low and middle orbits. That is why it is interesting to study nose fairing with volume enlarged through increased reference diameter, which exceeds midsection diameter of LV first stage [1,2]. As it is noted in the work [2], it is interesting to study such type nose fairing for LV and boosters like "Soyuz", Proton", "Atlas", "LM", GSLV.
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