A computational model for the design of a nitrous oxide--paraffin wax hybrid rocket engine

TL;DR

This paper presents a three-phase computational model for designing a hybrid rocket engine using nitrous oxide and paraffin wax, optimizing performance, predicting propellant needs, and validating with experimental data.

Contribution

It introduces a comprehensive three-phase model for hybrid rocket engine design, including steady-state, unsteady, and validation stages, tailored for the McGill Rocket Team.

Findings

Optimized engine parameters for maximum specific impulse.

Predicted propellant requirements for a 10,000 ft apogee.

Validated model against hot fire testing data.

Abstract

A computational model is developed to assist the design of the first hybrid rocket engine of the McGill Rocket Team, using liquid nitrous oxide as an oxidizer and solid paraffin wax as a fuel. The model is developed in three phases: In the first phase, a steady-state model which neglects transient performance decrease of the hybrid engine is considered. The steady-state model considers: a constant oxidizer mass flow rate; a combustion chamber in chemical equilibrium; a one-dimensional isentropic nozzle; and a one-dimensional constant-thrust rocket ascent. The steady-state model is used to conduct parametric studies on engine performance as a function of design parameters such as: oxidizer mass flow rate, fuel grain dimensions, and nozzle dimensions. The engine design point is selected to optimize specific impulse, given physical and structural constraints of the system. In the second phase, an unsteady model incorporating transient performance decrease of the hybrid engine is considered. The transient model considers: a self-pressurizing oxidizer tank in quasi-steady liquid-vapor equilibrium; a combustion chamber in quasi-steady chemical equilibrium; a one-dimensional non-isentropic nozzle; and a one-dimensional rocket ascent model. The transient performance profile of the engine is established, and the unsteady model is used to predict propellant requirements for the launch vehicle, given a target apogee of 3048 m (10,000 ft). In the third stage, the unsteady model is compared to hot fire testing data of the McGill Rocket Team. Semi-empirical parameters used in the formulation are calibrated against testing data, and the validity of the model is assessed.