Author(s)

Grace Olileanya Ngwu¹, Benjamin Iyenagbe Ugheoke¹, Olatunbosun Tarfa Yusuf², Mopa Ashem Nyabam², Spencer Ojogba Onuh^3*

¹Department of Mechanical Engineering, University of Abuja, Abuja, Nigeria.
²National Space Research and Development Agency, Abuja, Nigeria.
³Department of Mechanical Engineering, University of Maiduguri, Maiduguri, Borno State, Nigeria.

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.

Bi-Propellant, Hypergolic Chemical, Thrust Chambers, Hydrogen Peroxide, Additive Manufacturing, Rocket Propulsion Analysis

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.