Momentum Thrust Enhancement of Liquid Rockets at Vacuum by Spraying High Heat Capacity Nano-Granules to the Subsonic Region of the Rocket Nozzle

Sridhar, SS and Raj, Y and Kumar, VRS (2023) Momentum Thrust Enhancement of Liquid Rockets at Vacuum by Spraying High Heat Capacity Nano-Granules to the Subsonic Region of the Rocket Nozzle. In: AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023, 12 June 2023 through 16 June 2023, San Diego.

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Abstract

The theoretical discovery of the phenomenon of the Sanal flow choking and/or Streamtube flow choking in physical, chemical, and biological systems (V.R.S.Kumar et al. Physics of Fluids, 2022) is a paradigm shift in the design optimization of dual-thrust hybrid rocket systems at vacuum. The finest option for improving the propellant loading density in the nanoscale propulsion system design, without inducing any detrimental detonation, is to prohibit the occurrence of undesirable Sanal flow choking phenomenon (V.R.S.Kumar et al., Scientific Reports, 2021). In the case of biological systems increasing the heat capacity ratio of the fluid and/or decreasing the total-to-static pressure ratio is considered the best option for negating the undesirable Sanal flow choking (V.R.S.Kumar et al. Global Challenges, 2020, Physics of Fluids, 2022). The option of increasing the heat capacity ratio of combustion gas can be invoked in chemical propulsion systems, by altering the propellant composition to annul the undesirable phenomenon of Sanal flow choking, but it curtails the propulsive thrust during the non-optimal/non-vacuum flying conditions of rockets due to the decrease in thrust flow coefficient. On this rationale diagnostic investigation of examining all the possibilities of negating the occurrence of Sanal flow choking and achieving the highest momentum thrust of a dual thrust rocket at vacuum is a meaningful objective for further studies. Herein, we are proposing a conceptual approach to enhance the momentum thrust of a liquid rocket at vacuum by spraying nano-granules of solid propellant with high heat capacity to the subsonic region of the rocket nozzle. Note that at vacuum the thrust flow coefficient of any chemical rocket at optimum expansion is a unique function of the heat capacity ratio of the combustion gas. At vacuum, the exit velocity of any chemical rocket at optimum expansion is a function of the heat capacity and the combustion gas temperature. While adding the nano additives with high heat capacity to the combustion gas we can increase the momentum thrust. It helps for increasing the exit velocity as well as the mass flow rate. Comprehensive in silico studies have been carried out and presented herein to demonstrate the proof of concept. © 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Item Type:	Conference Paper
Publication:	AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
Publisher:	American Institute of Aeronautics and Astronautics Inc, AIAA
Additional Information:	The copyright for this article belongs to the publisher.
Keywords:	Additives; Biological systems; Combustion; Expansion; Gases; Granulation; Momentum; Rocket engines; Rocket nozzles; Rockets; Solid propellants, Chemical and biologicals; Chemical rockets; Combustion gas; Exit velocity; Flow choking; Flow coefficients; High heat capacity; Liquid rockets; Stream tubes; Subsonic region, Specific heat
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	11 Oct 2024 22:46
Last Modified:	11 Oct 2024 22:46
URI:	http://eprints.iisc.ac.in/id/eprint/86431

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