Advances in Aerospace Science and Technology

Volume 5, Issue 4 (December 2020)

ISSN Print: 2473-6708   ISSN Online: 2473-6724

Google-based Impact Factor: 0.31  Citations  

Numerical Analysis and Modelling of a 100 N Hypergolic Liquid Bipropellant Thruster

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DOI: 10.4236/aast.2020.54006    148 Downloads   369 Views  


This study focuses on the stepwise procedure involved in the development of a numerical model of a bi-propellant hypergolic chemical propulsion system using key features and performance characteristics of existing and planned (near future) propulsion systems. The study targets specific impulse of 100 N delivery performance of thrust chambers which is suitable for primary propulsion and attitude control for spacecraft. Results from numerical models are reported and validated with the Rocket Propulsion Analysis (RPA) computation concept. In the modelling process, there was proper consideration for the essential parts of the thruster engine such as the nozzle, combustion chamber, catalyst bed, injector, and cooling jacket. This propulsion system is designed to be fabricated in our next step in advancing this idea, using a combination of additive manufacturing technology and commercial off the shelf (COTS) parts along with non-toxic propellants. The two non-toxic propellants being considered are Hydrogen Peroxide as the oxidiser and Kerosene as the fuel, thus making it a low-cost, readily available and environmentally-friendly option for future microsatellite missions.

Cite this paper

Ngwu, G. , Ugheoke, B. , Yusuf, O. , Nyabam, M. and Onuh, S. (2020) Numerical Analysis and Modelling of a 100 N Hypergolic Liquid Bipropellant Thruster. Advances in Aerospace Science and Technology, 5, 85-99. doi: 10.4236/aast.2020.54006.

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