Effect of magnesium metal in the characteristics performance of a sucrose-based solid rocket propellant

Oyedeko K.f.k Oyedeko K.F.K,Egwenu S O Egwenu S O

doi:10.30574/gjeta.2021.6.2.0016

Abstract

This research work aimed at investigating the effects of magnesium metal (powder) and carbon on a potassium nitrate-sucrose (KNSU) solid propellant formulation. Characterization of propellant is very important to determine its performance before it can be suitable for use for a rocket flight or any mission. Ballistic loadcell method was used. The ballistic load cell instrumentation measured the thrust generated by the propellant, the propellant burn time and the exit temperature of the burning hot propellant gases. The carbon constituent which acts as an opacifier and coolant was kept constant at 2% in order to arrest some of the heat during the combustion process and helped to lower the combustion temperature, because high combustion temperature could lead to combustion chamber rupture or failure. Also, carbon was not increased beyond 2%, so as not to make the propellant excessively smoky because of presence of magnesium oxide and other solids in the combustion products that can cause air pollution, and could be harmful to human lives and the environment. The propellant specific impulse (117.9s), combustion temperature (1818K), heat ratio (1.1508), propellant molecular weight (38.88g/mole), propellant density (1874.6kg/m3), characteristics velocity (997.2m/s) and burn rate (0.00906m/s) were obtained. The effect of addition of magnesium which was optimized for 3% in the formulation contributed significantly in improving the overall performance of the propellant as parameters such as the specific impulse, chamber temperature, characteristics velocity and heat ratio were found to have higher values as compare to the KNSU propellant when magnesium was not present in the formulation. Basically, higher values of these parameters suggest better propellant performance. Also, in this case, when carbon was increased beyond 2%, the propellant was excessively smoky because of presence of magnesium oxide and other solids in the combustion products that can cause air pollution, and could be harmful to human lives and the environment.

Highlights

Most modern missile systems e.g Rocket motor make use of propellants to produce thrust force require to propel them [1]
Many researchers have been working over the years to improve and develop new propellant formulations significantly to meet the need of the type reaching targets and missions with less weight [4,5]. and propellant mass fraction can be sometimes be up to 70-90% of the rocket total mass, improving and developing new propellant formulations to meet this need is very significant [6]
Potassium nitrate with some water is first introduced. When it is thoroughly dissolved in the water, the sucrose is added, after both are well mixed, the magnesium is added, and lastly the carbon is introduced into the propellant slurry

Summary

Introduction

Most modern missile systems e.g Rocket motor make use of propellants to produce thrust force require to propel them [1]. An oxidizer produces oxygen for reaction with the fuel to give requires proportion [2]. Propellants are of different types solid, liquid or hybrid based on the constituents of oxidizer and physical state of the fuel [3]. Many researchers have been working over the years to improve and develop new propellant formulations significantly to meet the need of the type reaching targets and missions with less weight [4,5]. Propellant mass fraction can be sometimes be up to 70-90% of the rocket total mass, improving and developing new propellant formulations to meet this need is very significant [6]. Potassium nitrate is so chemically stable that it is absolutely impossible

Objectives

Methods

Conclusion