In this article, the potential of the hybrid propellant rocket engine technique is discussed. it is a great dream to flight engineers to design and fabricate a rocket engine with more reliability and nil rate of combustion instability probably for long range applications. Solid propellant rocket engine and liquid propellant rocket engine has a considerable rate of advantages but combustion instability is a great threaten in both the engines. Hybrid propellant rocket engine has a very less rate of combustion instabilities when compared to both solid and liquid propellant engines. The ultimate aim of every engine design is to prevent occurrence of this combustion instability and maintain reliable operation during entire span of the combustion process. This article is mainly focused on occurrence of various type of combustion instabilities in hybrid propellant rocket engine and its preventing methods. The performance of the hybrid propellant rocket engine was analysed under various aspects and its unique characteristics were presented in detail.