Rushikesh Kore

ORCID ID: 0000-0002-6993-3218

Research Project Title: Green Propellant for Future Small Satellite Launch Vehicle

Supervisors/s: Dr Ashish Vashishtha

Project Funding: IRC Government of Ireland PhD Scholarship



  • Biography
  • Research Project Description
  • Publications and Outputs


My name is Rushikesh Kore. I am currently pursuing my research master’s at South East Technological University Carlow. My Current research area is to explore the Green Solid Propellants which can be implemented in future launch vehicles.

I have completed my Bachelor’s Degree in Aerospace Engineering from MIT-ADT University, Pune, India (2022). During my bachelor’s programme, I worked on Solid and Liquid Propulsion Systems. As part of my project and research, I conducted experiments on solid propellants using ballistic evaluation motors and worked on a CFD model for Liquid Propulsion Systems.

Research Project Description

Solid propellants are being used to launch satellites in different orbits for decades. Solid propellants are preferred because they offer significant benefits over the other existing propulsion systems with less complexity. Conventional solid propellants consist of metallic fuels, oxidizers, and additives to make good compositions. They have both advantages and disadvantages. Being less hygroscopic in nature it allows for wide storability is the advantage of solid propellants. The burning of these propellants produces harmful exhaust gases which have an adverse effect on the environment and human life is the disadvantage of solid propellants. To overcome the negative impact of solid propellants the current research will focus on the development of green solid propellants which will help to reduce the harmful gases and allied effects associated with them. The purpose of the project is to examine the viability of using green solid propellant in solid rocket motors for future rocket launch vehicles and small-scale amateur rocketry. It plans to test the improved green propellant with small-scale 3D printed manufactured nozzles and allied components as part of expanding space systems capabilities at South East Technological University Carlow. Static testing of various green propellant formulations will aid in understanding their suitability for use in small rocket launch vehicles.

Publications and Outputs

  • Rushikesh Kore and Dr Ashish Vashishtha (2023). NUMERICAL STUDY OF OBLIQUE DETONATION WAVE CONTROL FOR FUEL BLENDS at 57th 3AF International Conference on Applied Aerodynamics, France Bordeaux.

Summary: This study aims to develop control strategies for oblique detonation wave formation on a finite-length wedge in a premixed methane-air incoming flow. The effectiveness of hydrogen blends (0-100%) to methane-air premixed mixture (at 300 K) on Chapmann Jouguet (CJ) detonation and oblique detonation wave formation is analyzed for different pressure and incoming velocities. Two-dimensional numerical simulations for the oblique shock wave to oblique detonation wave transition are performed for an incoming flow velocity of 2800 m/s, pressure of 20 kPa and temperature of 300 K.

  • Rushikesh Kore, Patil, S., Victor, V., Suresh, S., Bajaj, D.K. and Jain, S. (2023). CFD approach to predict the significance of the shape bluff body on flame stabilisation in lean premixed combustion of hydrogen-air mixturesMaterials Today: Proceedings, [online] 72, pp.1181–1189. doi:

Summary: Europe, particularly France, has been investing in supersonic air-breathing such as Ramjet and Scramjets. To generate higher temperatures, an air-heating system must be organised at the test site. This study is centred on studying the effect of the different bluff bodies in air heaters. To conduct the simulation the fuel selected is hydrogen, which is further supplied with makeup oxygen. A validated FLUENT CFD Code is used to model the burning of the air heater. The air vitiator structure is good for giving air at a temperature range of 400-1000 K, the pressure between 20 and 35 bar at Mach numbers between 0.1 and 0.5, and an air mass stream pace of a reasonable amount.

  • Rushikesh Kore, Talele, V., Desai, H., Chandak, A., Sangwan, H., Bhale, G., Bhirud, A., Pathrikar, S., Nema, A. and Patil, N.G. (2022). Thermal Design and Numerical Investigation of Cold Plate for Active Water Cooling for High-Energy Density Lithium-Ion Battery Module.Engineering Optimization: Methods and Applications, pp.343–364. doi:

Summary: This article presents a comparative analysis of the temperature and velocity distributions inside cold plates mounted on a lithium-ion battery identical mimic battery module. The numerical model is created using commercial Ansys software to examine heat transport properties across the battery module surface temperature. A multi-objective optimization strategy is proposed for increasing input flow rate to increase heat transfer coefficient, which drastically reduces surface temperature. Recommendations are aligned with the thermal design view.

  • Rushikesh Kore, Shreya Patil, S. Suresh, Dr Shaoo and Dr Sunil Jain (2022). Theoretical and CFD analysis of air vitiators for combustion of fuel-rich propellant gasses in ram combustor at 13th International High Energy and Materials Conference & Exhibits (TBRL, India)-2022.

Summary: Ramjets are the simplest and most economical form of propulsion system/device without moving parts. They are operational between Mach 2-6 and can be operated with either liquid or solid fuels. This paper investigates the air heating apparatus and the investigation of combustion followed by theoretical and CFD (Ansys) approaches. Flame stabilization techniques have been examined, with the small triangular stabilizer showing the optimum air-fuel mixture and uniform temperature throughout the combustion chamber. The paper also demonstrates the variation of temperature in the combustion chamber, the blow-off limit of various bluff bodies, and combustion efficiency.

  • Rushikesh Kore, Shreya Patil, V. Nadar, S. Suresh, D. K. Bajaj, and Dr S. Jain. (2022) Performance Analysis of Bell Nozzle for Solid Rocket Motor Using Cfd Approach at the 13th International High Energy and Materials Conference & Exhibits (TBRL, India)-2022

Summary: The Bell Nozzle is used in rocket motors to change chemical-thermal energy into kinetic energy. It is more effective and compact than a tapered nozzle and is intended to give a huge large angle expansion for the gases just after the throat. This research paper will introduce logical strategies and ways to adopt optimum nozzle geometry for a solid rocket motor. CFD analysis and geometry optimization will be used to carry out the CFD investigation. This paper uses a computational approach to predict performance parameters such as pressure, temperature, and Mach number along the length of a Bell nozzle. The Axis Symmetry model is used to carry out the analysis. NASA CEA code is used to evaluate the performance parameters and MATLAB is used to calculate them. Results show that pressure and temperature graphs decrease with respect to length, size, and cross-section area, while Mach number and velocity graphs increase with respect to length, size, and cross-section area.

  • Rushikesh Kore, Devanshi Gandhi, Akash Marade and Manan Joshi. (2022) Consequence of Bluff Body in Lean, Premixed Micro-Combustion of Methane-Air Mixture Presented at 1st International Symposium on “Recent Advancements in Aerospace & Defence Technology” Organised by the Department of Aerospace Engineering, MITSOE, MIT ADT University, Pune in association with AESI Pune.

Summary: Micro-combustion is the exothermic chemical reaction between a fuel and an oxidizer that results in the combustion characteristics and flame stability of a lean premixed methane-air mixture in a micro combustor with different heat production and chemical species conversion. It is studied at a micro-level by solving two-dimensional governing equation shapes of bluff bodies (half ellipse, triangle, crescent, and wall-blade) under various physical and chemical conditions. The micro combustor will be made out of steel with a conductivity of 20 W/mK. Existing literature suggests that the wall blade produces the highest flame temperature for non-hydrocarbon – air mixtures.

  • Rushikesh Kore, Virendra Talele, Akshay Deshmukh, and Saurabh Patrika. (2021) A CFD investigation to predict delay effect the thermal performance of PCM on integrated circuit application Accepted in Springer Lecture Notes in Mechanical Engineering.

Summary: This paper investigates the thermal behaviour of five unidentical integrated circuit chips (IC) under passive thermal cooling arrangements. The investigation is based on time-dependent transient scaled analysis and provides standard guidelines on how to predict passive thermal performance. The results show that the PCM arrangement with Paraffin wax provides a better delay effect causing cooling of IC chips in passive mode. A verification guideline is also proposed to select a proper grid while dealing with phase change time-dependent simulations.

  • Kore, Patil, S., Victor, V., Suresh, S. and Bajaj, D.K. (2021). CFD Investigation in CD Nozzle at Different Convergence Angles and Constant Divergence Angle and Throat Diameter. IEEEXplore.doi:

Summary:  This work presents a computational approach to investigate the flow behaviour inside the CD nozzle by varying the convergence angle. The k-epsilon analytical equation is used to model the compressible flow of gas within the nozzle and its hot exhaust plumes. Exhaust nozzle characteristics were computed and compared to existing empirical evidence to demonstrate the models’ correctness. The nozzle model was created with SolidWorks software (2013) and Ansys FLUENT software (18.1) to depict fluctuations in velocity, Mach number, pressure, and temperature contours. The validated CFD process will be used to conduct the CFD investigation.