DESIGN AND TESTING OF A 50N HYDROGEN PEROXIDE MONOPROPELLANT ROCKET THRUSTER

Abstract

Among research and development activities concerning the monopropellant thrusters are on the safe handling of the propellant and the environmental issue rises from the toxicity of the combustion products. The development of the “green†propellant was a reaction toward controlling the release of toxic combustion products. Using the hydrogen peroxide as the monopropellant and silver screen as the catalyst to enhance the performance of thruster, oxygen and superheated steams are the only combustion products produced. The non-toxic hydrogen peroxide on its own is very stable at room temperature and with the non-toxic combustion products qualify it as green propellant. The results show that the output from decomposition process produces no other toxic materials. Thrusters of 50N thrust or below can be used in satellite application and the problem is to develop this thruster using Hydrogen Peroxide monopropellant. This paper presents the chemical equation of the silver-catalyst chemical decomposition of the hydrogen peroxide and the design of 50N hydrogen peroxide monopropellant rocket thruster. The provision for varying injector orifice diameter was also incorporated in the design. The test results of rocket thruster using hydrogen peroxide of concentration above 90% are presented. The results indicate that for the successful operation of rocket thruster, the catalyst pack should be heated above 100oC and high purity hydrogen peroxide should be used.