Despite all the other rocket motors on the market such as solid and liquid. A historically failed motor was in the market which was handicapped in performance but now with technological development in the previous years, hybrid rocket motor is the most influential talk in the market. Deeper in the paper we will discuss the hybrid motor focusing on the fuel used in Hybrid rocket engines and the performance depending on the design. Furthermore, this review paper will help us to study the different materials for the betterment of the engine performance. We will also be focusing on the methods required to improve total impulse. Moreover, will be elaborating on the performance of paraffin wax and its material property.
The cardinal pillar for this paper is to showcase the composition of Graphene-based composites and reveal the hidden uses of Graphene-based composites in aerospace dominion. This paper briefly discusses the different methods by which graphene-based composites can be synthesized mostly those with functional polymers and inorganic nanostructures and additionally covers a few of the applications of graphene-based composites such as lightweight, fire retardancy, and additive manufacturing. Moreover, this detailed paper also brings up crucial highlights where graphene-based composites have covered long distances from the research lab to commercialization, specifically focusing on aerospace industries.
The nozzle is a critical component of any rocket engine because it transforms high pressure and high temperature (with sluggish net velocity) within the combustion chamber into high velocity but low pressure. Individually, the molecules in the mixed propellants have rapid velocity in the combustion chamber, but directions are randomly pointing in all directions. A convergent-divergent nozzle, also known as a CD nozzle, is fashioned like a tube with two bulging ends and a thin part in the center. This structure/design provides the nozzle with a balanced shape. By turning the flow's heat energy into kinetic energy, the nozzle accelerates hot, pressured gas traveling past it in the axial (push) direction. Whereas the nozzle provides the acquired incremental thrust to the rocket engine, it also results in unwanted thrust losses. Out of which divergent losses in the divergent section are the primary foci of our research. Moreover, in this research paper, we produced verified results to reduce the thrust losses at the divergent sections of the nozzle by optimizing the nozzle with different half divergent angles.
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