Innovation in Hybrid Rocket Propulsion System

Abstract

The hybrid rocket propulsion system is a one-of-a-kind propulsion method that integrates aspects of both solid rocket engines and liquid rocket engines. It has a number of benefits over conventional rocket propulsion systems, such as greater safety, simplicity, and the capability to be controlled. This abstract offers a summary of hybrid rockets, including information on their operating principles as well as the current state of research and development in this area. The use of a solid fuel grain and a liquid or gaseous oxidizer is the primary component of the hybrid rocket design concept. The solid fuel grain, which is normally made up of a compound that is similar to rubber, is set ablaze and allowed to burn while in the presence of the oxidizer, which results in the production of hot gases. These gases are forced out of the rocket through a nozzle, which generates thrust and drives forward movement of the rocket. A hybrid rocket engine incorporates components for rocket motors that run on liquid fuel as well as those that run on solid fuel. The fuel itself is often a solid grain (paraffin or hydroxyl-terminated polybutadiene, or HTPB), whilst the oxidising agent is typically a liquid (hydrogen peroxide or liquid oxygen). These components are brought together in the fuel chamber of the hybrid motor, which also performs the function of the combustion chamber. In this research, we investigate the various technological advancements that have taken place in the production of these motors from the year 1995. There are methods available for measuring the thrust of rocket motors as well as monitoring the combustion reaction products that are present in the rocket plume.