Ali Saberimoghaddam* - Malek Ashtar University of Technology, Tehran, Iran
Elahe Basafa - Department of chemistry and chemical engineering, Malek Ashtar University of technology, Tehran, Iran

Liquid propellant missiles are commonly applied to launch satellites that must be located in  upper orbits. These systems normally use hydrogen and oxygen propellants that are non-hypergolic mixtures. In this study, the test results of a designed hydrogen/oxygen engine were evaluated, and a designed spark igniter was successfully used to start the engine. Seven hot tests were carried out to determine the performance of the engine. The effect of oxygen to fuel ratio (O/F ratio) at a constant combustion chamber pressure (۸۰۰ kPa) showed that the maximum value of the specific impulse (Isp) and characteristic velocity (C*) occurs at an O/F ratio of about ۲.۸. Experimental tests at the constant O/F ratio of ۲.۸ showed that performance parameters, such as Isp and C*, were enhanced when the chamber pressure was increased. However, the trend was sluggish at pressures higher than ۸۰۰ kPa.

Hydrogen/Oxygen Engine, Performance, Specific Impulse, Characteristic Velocity