Résumé:
The purpose of master thesis is a contribution into the realization of an inexpensive and lightweight thruster of one Newton (1N), that local manufacturing companies can produce, and this using a green fuel : Hydrogen Peroxide 𝐻 of a concentration equal to 87.5 % for satellites
application. 2 𝑂 2
The methodology used was based under a set of analysis steps starting from Thermochemistry
to Theoretical Rocket Performance, and Preliminary Thruster Design. The effective factors used to study our system are dependent upon one another, meanwhile these factors are directed the decisions
made throughout this design project that are the thrust, pressure, fuel, loading factor, catalyzer type and study state (vacuum – atmospheric).
Nozzle is the most important part for any thruster design, a set of conditions were made within storage system and thruster to determine the right design for the converging diverging nozzle,
meanwhile determining the correct catalyst model sustain the desired efficiency.
Matlab program was used for the dimensioning step. ANSYS Fluent 19.0 was used for CFD analysis & SolidWorks 2017 for CAD generation respectively.
The value of this project is to aid in the reconnaissance and analysis of green propellant propulsion system by adding a catalyzer for higher efficiency corresponding to control attitude conditions as well as provide a stable and controllable platform for testing equipment that can be ultimately applied to space applications.
