Abstract
The results of analyzing ways of improving the total thrust impulse for the launching rocket boosters under severe limitations of overall dimensions are presented. Comparative performance evaluation of the launching boosters manufactured by the classical single-nozzle and multi-nozzle configurations is given. It is shown that the use of the multinozzle configuration with the out-of round asymmetrical nozzles is rational.
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Alemasov, V.E., Dregalin, A.F., and Tishin, A.P., Teoriya raketnykh dvigatelei (Theory of Rocket Engines), Glushko, V.P., Ed., Moscow: Mashinostroenie, 1990.
Gubertov. A.M., Mironov, V.V., Borisov, D.M., et.al., Gazodinamicheskie i teplofizicheskie protsessy v raketnykh dvigatelyakh tverdogo topliva (Gasodynamic and Thermophysical Processes in Solid-Propellant Rocket Engines), Koroteev, A.S., Ed., Moscow: Mashinostroenie, 2004.
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Original Russian Text © A.O. Kochetkov, 2009, published in Izvestiya VUZ. Aviatsionnaya Tekhnika, 2009, No. 3, pp. 67–69.
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Kochetkov, A.O. Efficiency of a launching booster multinozzle configuration for rockets with out-of-round asymmetrical nozzles. Russ. Aeronaut. 52, 357–360 (2009). https://doi.org/10.3103/S1068799809030167
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DOI: https://doi.org/10.3103/S1068799809030167