International Journal of Engineering Technology and Management Sciences Website: ijetms.in Issue: 6 Volume No.6 October - November – 2022 DOI:10.46647/ijetms.2022.v06i06.065 ISSN: 2581-4621 @2022, IJETMS | Impact Factor Value: 5.672 | Page 368 Conceptual Study on Propulsive Characteristics and Performance of Cryogenic Propellants Shruti Dipak Jadhav 1 , Raghvendra Pratap Singh 2 , Atri Bandyopadhyay 2 , Tapas Kumar Nag 2 1 Research Supervisor, Department of Research and Development, ASTROEX RESEARCH ASSOCIATION, Uttar Pradesh, India 2 Graduate Research Trainee, Department of Research and Development, ASTROEX RESEARCH ASSOCIATION, Uttar Pradesh, India Abstract— In the era of cryogenic propellants with high specific impulse; under microgravity situations, long-term storage and higher energy thruster management are highly needed. As methane is a reasonable cooling membrane for radiation and ablation chambers so high LOX/LCH4 combustion efficiency and reliable spark ignition to be achieved to develop a methane engine. To maintain the thermocouple system in the spacecraft and to prevent outer harmful radiation in space, the respected agencies may use thick-walled propellant containers with high pressure. To check the feasibility and effectiveness of a subcooled cryogenic propellant, a combination of pump depressurization as active cooling and liquid choke evaporation as passive cooling has been proposed and analyzed. Keywords— Cryogenic propellants, Specific impulse, Microgravity, Spark ignition, Stirling cycle, Reverse Turbo-Brayton cycle, Recirculation, Subcooled, Liquid choke. I. INTRODUCTION Methane/oxygen rocket engines have the ability to provide tremendous undertaking lifestyle cycle benefits over traditional rocket propellants presently in use within side the United States. Liquid methane (LCH4) and liquid oxygen (LOX) propulsion are notably aggressive because of their bulk density momentum as compared to the booster-propellant combos historically used these days in the area. There is a resurgence of hobby in methane-oxygen propulsion structures because of the probable improvement of the latest rocket motors to help area exploration and business markets. Cryogenic propellants utilized in massive rockets have grown to be one of the maximum usually used fuels because of their benefits of being non-toxic, non-toxic, inexpensive, excessive particular impulse and massive thrust. Currently, the temperature of cryogenic fuels is broadly speaking near the ordinary boiling point, ensuing in negative thermophysical performance, particular for liquid hydrogen. In cryogenic propulsion structures, a cooling system is done earlier than every ignition to modify the temperature of the delivered strains and rapid pumps. A recirculating cooling device is a candidate to lessen this intake on long-period area missions that require a couple of firings of the cryogenic engine. In a recirculating cooling device, a cryogenic pump attracts gasoline from the tank via a delivery line and into the engine. In essence, destiny cryogenic orbital propulsion structures would require a cryogenic propellant recirculation device to chill the recirculation, lively cooling, and tank stress and temperature management for green propellant utilization. II. LITERATURE REVIEW Methane/oxygen rocket engines have the potential to offer significant mission life cycle advantages over conventional rocket propellants currently in use in the United States. Liquid methane (LCH4) and liquid oxygen (LOX) propulsion is highly competitive due to their bulk density momentum compared to the booster-propellant combinations traditionally used today in space. There is a resurgence of interest in methane-oxygen propulsion systems due to the likely development of new rocket vehicles to support space exploration and commercial markets. These propellants have