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

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Document pages: 15 pages

Abstract: This study focuses on the stepwise procedureinvolved in the development of a numerical model of a bi-propellant hypergolicchemical propulsion system using key features and performance characteristicsof existing and planned (near future) propulsion systems. The study targetsspecific impulse of 100 N delivery performance of thrust chambers which is suitable for primarypropulsion and attitude control for spacecraft. Results from numerical modelsare reported and validated with the Rocket Propulsion Analysis (RPA)computation concept. In the modelling process, there was proper considerationfor the essential parts of the thruster engine such as the nozzle, combustionchamber, catalyst bed, injector, and cooling jacket. This propulsion system isdesigned to be fabricated in our next step in advancing this idea, using acombination of additive manufacturing technology and commercial off the shelf(COTS) parts along with non-toxic propellants. The two non-toxic propellantsbeing considered are Hydrogen Peroxide as the oxidiser and Kerosene as the fuel,thus making it a low-cost, readily available and environmentally-friendlyoption for future microsatellite missions.

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