Configuration Design Studies of a LOX-LCH4 Booster Engine and Stage for a Futuristic Indian Launcher
Creators: name:  K. MOHAN 
name:   F. BIN ABDUL HASIS 
name:   V. SASIDHARAN 
name:   N. V 
name:   S. KUMAR C 
name:   J. N 
Publisher: name: Proceedings of  the 9th European Conference for Aerospace Sciences. Lille, France, 27 June - 1 July, 2022
Year: 2022
Subjects: PROPULSION PHYSICS
LIQUID ROCKET ENGINE
SYSTEMS
NEW DEVELOPMENTS

description: A wave of changes triggered by the emergence of successful private space launch provider agencies is sweeping across the global space industry. Heritage based selection of system parameters and design methodologies for development of new launch vehicles are being supplemented by novel ideas and bold decisions on launch vehicle configurations. While the space agencies are shifting over from the historical \"most efficient\" designs to the rather novel \"most effective\" designs, configuration design studies on futuristic launch vehicle gains more importance. The study reported herewith attempts to configure a high thrust liquid rocket engine using a set of novel software tools developed to bridge the gap between the historically used launcher configuration tools and the current level of technological advancements. The study was carried out using a hypothetical reference launcher, the staging of which was derived using a theoretical staging optimization code. To make the study comprehensive and challenging, a 4 stage launcher configuration with LOX-LCH4 propellant combination propelling all stages was used as reference launcher. The booster and intermediate stages were proposed to share the propulsion elements including the engine while the terminal stage was assumed to be a unique stage with a different stage architecture. The Booster stage and engine configuration was then derived with an aim of meeting the required payload assuming the terminal stage performance to be fixed at a predefined value. A novel toolkit, Integrated Stage Cycle Analysis (ISCA) tool which combines the engine cycle analysis, stage parametric estimation and basic mission analysis was used for the study. A baseline engine and stage configuration was derived such that all major challenges and additional requirements from the stage faced during clustering of the engines in booster stages are met primarily by the engine itself. A few novel ideas in stage and engine sub-systems are also proposed to ensure that the stage being developed is in par with the state of the art technologies available globally. The baseline configuration was then analyzed using the ISCA tool for finalizing the engine and stage parameters. The sensitivity of launcher payload capability to changes in various stage parameters was mapped and used to determine the parameters to be critically analyzed. The parameters were then iterated in combinations to arrive at a feasible solution were the payload requirements of the launcher could be met with the lowest development and realization challenges. The current paper describes the study in detail and compares the design philosophies, methodologies used and results obtained with futuristic launcher stage configurations proposed by global space agencies [3] [2] [1] [4] . References [1] C. Bonhomme, A. Iannetti, D. Tchou-kien N. Girard, N. Ravier, and E.Edeline. Prometheus: European next generation liquid rocket engine. IAC-17-C4.1.2, 68th International Astronautical Congress, Adelaide, Australia. [2] A. Iannetti, D. Tchou-kien N. Girard, C. Bonhomme, N. Ravier, and E. Edeline. Prometheus, a lox/lch4 reusable rocket engine. 7th European Conference for Aeronautics and Space Sciences (EUCASS), 2017. [3] James H. Morehart. A survey of lng-fueled rocket engine evelopment activity - non u.s. AIAA Propulsion and Energy 2021 Forum, 2021. [4] P.Simontacchi, R. Blasi, E. Edeline, S. Sagnier, N. Ravierand, A. Espinosa-Ramos, J. Breteauand, and Ph. Altenhoefer. Prometheus: Precursor of new low-cost rocket engine family. 8th European Conference for Aeronautics and Space Sciences (EUCASS), 2019.