TITLE:
Numerical Analysis and Modelling of a 100 N Hypergolic Liquid Bipropellant Thruster
AUTHORS:
Grace Olileanya Ngwu, Benjamin Iyenagbe Ugheoke, Olatunbosun Tarfa Yusuf, Mopa Ashem Nyabam, Spencer Ojogba Onuh
KEYWORDS:
Bi-Propellant, Hypergolic Chemical, Thrust Chambers, Hydrogen Peroxide, Additive Manufacturing, Rocket Propulsion Analysis
JOURNAL NAME:
Advances in Aerospace Science and Technology,
Vol.5 No.4,
November
27,
2020
ABSTRACT: 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.