Case study regarding the use of three different fuels in a multi-stage hybrid rocket engine

Abstract

Based on previous researches carried in the field on hybrid rocket engines, the authors propose the idea of three different fuel used in a multi-stage hybrid rocket engine. The aim of this paper is make a comparative analysis of rockets hybrid propulsion systems, considering a three stage hybrid rocket engine using one single type of fuel, and a three stage hybrid rocket engine using three different fuels for each stage. Numerical modelling is assuming a similar design mathematical model for both rockets. It is assumed that a concept like this, using different fuel types could lead to a reduction of pollutants and the improvement of combustion efficiency. For both design solution, the comparative analysis is using one imposed criteria, respectively the payload. The calculations are made in order to determine the required thrust force based on the required mass flows of fuel and oxidizer, and next, it is resulting the length and critical diameter of the flue gases nozzle. It is to be mentioned that the mathematical modelling is based on estimated values regarding combustion processes from different studies available in this research field. The numerical model can be used in loop cycle, to obtain a proper design of combustion system for each stage, and thus to get the performance of rocket engine.