Chemical Rocket Motors for Space Launch Applications: Parametric Approach

Abstract

Hybridrocket motors are widely used in heavy launch vehicles with maximum payload capacity. The main reason for the study in this field is that the hybrid rocket motor is very easy to handle and has a simple design. In this paper, we have studied the parameters involved in designing and optimizing the hybrid rockets which provides in achieving maximum performance value. The several parameters considered for parameters involve are- burn rate, specific fuel consumption, specific impulse, efficiency. The design constraints will be responsible in achieving a high thrust level through the nozzle. The study also highlights the propellants being used in hybrid rocket motor. The collaborative research will aid in briefing the design and the working of the hybrid motors that is frequently being utilized in the industry.