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ISSN Online: 2379-1748

7th Thermal and Fluids Engineering Conference (TFEC)
SJR: 0.152 SNIP: 0.14 CiteScore™:: 0.5

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Clarivate CPCI (Proceedings) Scopus
May, 15-18, 2022 , Las Vegas, NV, USA


Get access (open in a dialog) pages 15-24
DOI: 10.1615/TFEC2022.aer.040784


With the onset of commercialization in aerospace industry, an effective methodology for launch vehicle configuration design has become extremely relevant. Launch vehicle configuration design is a complex process where interlinking of various subsystems like propulsion systems, structural elements, control components, avionics etc. from multi-disciplinary agencies is a crucial task. To design an effective launch vehicle, it is imperative to carry out an integrated vehicle level optimization rather than attempting a series of sub-system level optimizations. Integrated Stage Cycle Analysis (ISCA) is a tool developed to carry out a configuration design of launch vehicles effectively by combining engine cycle analysis, stage parametric estimations and basic mission studies. The tool aims at deriving a micro-launcher configuration that is optimal at the system level rather than one configured with optimal sub-systems, which may or may not lead to a system level optimality. The current paper details a formulation of ISCA code and a case study demonstrating the utility of the tool in developing a micro-launcher with constraints specific to Indian launch sites and scenarios. The micro-launcher under study is configured with a payload capability of 150 kg to a 200 km Low-Earth Orbit (LEO) and is assumed to be a two stage, all LOX-LCH4 launcher powered by Gas-Generator cycle engines. The ISCA tool is extensively used to estimate the sensitivity of launcher payload fraction to changes in various system parameters including engine chamber pressure, engine mixture ratio, tank material selection etc. before finalizing the optimal configuration.