Conceptual Design Optimization Method of Vertical Launch and Landing Reusable Rockets
According to the multiple constraint coupling problem of conceptual vertical launch and landing reusable rockets,the composition configuration was analyzed by studying the configuration,the propellants and the propellant configuration.A preferred solution was proposed which was a two-stage single cored configuration,with hydrogen/oxygen and Lox/methane propellants,and multiple small or medium thrust engines.Moreover,the 5/7/9 parallel engines were selected as the optimal configurations.The launch and transportation capacity were estimated using Zioukovsky formula.In addition,the launch and transportation capacity were optimized,with first and second stage ratio an optimization variable,which yielded the basic launch and transportation capacity for variant diameter of rocket,propellants,and propellant configurations.By considering the slenderness ration,the fea-sible conceptual design of two-stage single cored,odd parallel engines vertical launch and landing reusable rockets were yielded.
space launch and transportation systemrocketliquid oxygen/keroseneliquid oxygen/methanereusablevertical launch and landing
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NSTL
万方数据
维普
