Configuration Studies on An Electric Pump Fed Upper Stage Rocket Engine
Creators: name:  K. MOHAN 
name:   F. BIN ABDUL HASIS 
name:   V. SASIDHARAN 
name:   P. P GEORGE 
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: Electric pump fed cycle (EPFC) is a rather novel addition to the rocket engine family. Unlike the conventional rocket engine cycles where the propellants are pressurised before injection using thermodynamic cycles, EPFC based engine uses an electric motor to drive the pumps. Simplicity and ease in control are the major attractions of EPFC, while the limitation in thrust achievable with the current level of maturity in battery and electric motor technologies poses a great disadvantage as reported by various researchers across the globe [5] [2] [1] . The study being reported was undertaken to arrive at a realisable configuration of a low thrust EPFC based engine to be used in the upper stage of a futuristic micro-launcher. The pre project activities carried out and reported by Kiran et. al. [3] revealed that LOX-LCH4 would be the best choice of propellant combination for the proposed application. The study reported by Vishak et. al.[4] reveals that EPFC would be a better choice for use in upper stages of micro-launchers in comparison to the conventional gas generator cycle. The current study was hence carried out to configure an EPFC based LOX-LCH4 engine to be used in the upper stage of a futuristic micro-launcher. A reference, all solid micro-launcher capable of delivering 500kg payload to 500km Low Earth Orbit was configured using staging optimisation code. The upper stage of this reference rocket was then assumed to be replaced with an equivalent LOX-LCH4 stage powered by an EPFC based engine named Jugnu. The configuration of Jugnu engine was studied in detail with assessment of implications of sub-system selection on overall payload capability of the reference vehicle. The sub-system selection process was followed by iterations of system parameters like chamber pressure and propellant storage temperatures to arrive at optimal engine working parameters. The study was carried out using the Integrated Stage Cycle Analysis (ISCA) tool customised for this case. ISCA tool integrates the engine cycle analysis, stage parametric estimations and basic mission studies in a single interactive module. The present article reports all details of the theoretical studies carried out while configuring Jugnu. Various advantages and specific constraints to be met while configuring such engines are also detailed. Finally, a sensitivity analysis of changes in system parameters on the reference rocket payload capability is also brought out. References [1] Kai Dresia, Simon Jentzsch, G. Waxenegger-Wilfing, Robson Dos, Santos Hahn, and Jan Deeken. Multidisciplinary design optimization of reusable launch vehicles for different propellants and objectives. Journal of Spacecrafts and Rockets, 58:10171029, 2021. [2] Hwanil Huh Juyeon Lee, Tae Seong Roh, Hwanil Huh, and Hyoung Jin Lee. Performance analysis and mass estimation of a small-sized liquid rocket engine with electric-pump cycle. International Journal of Aeronautical and Space Sciences, 22:94107, 2021. [3] Kiran Mohan, Vishak Sasidharan, Nandakumar V., and Suresh Kumar C. Comparative study on the suitability of liquid rocket propellants for use in electric pump fed rocket upper stages. Proceedings of the 26th National and 4th International ISHMT-ASTFE Heat and Mass Transfer Conference, IIT Madras, Chennai, India, Dec 17-20 2021. [4] Vishak Sasidharan, Fahd B. A. Hasis, Kiran Mohan, Nandakumar V., Jayan N., and Suresh Kumar C. Comparative study on the suitability of electric pump fed and gas generator engine cycles in Indian micro launchers. Proceedings of the 48th National Conference on Fluid Mechanics and Fluid Power (FMFP),BITS Pilani, Pilani Campus, Rajasthan, India, Dec 27-29 2021. [5] G. Waxenegger Wilfing, R.H.S. Hahn, and J. Deeken. Studies on electric pump fed liquid rocket engines for micro-launchers. Space Propulsion, 452, 2018.