Evolution in Propellant of the Rocket Engine

Abstract

Evolution of rocket engine had contributed global opportunity for human civilization on the base of expanding science and technology, artificial intelligence and economic expansion which have given us potential to explore the universe as well as solve the burning issue over population, scarcity of basics and industrial resources, global warming and most prominently safety of mother earth and mankind. Hence, collecting and studying the data of various engine’s propellants and structures made till date to overcome various efficiency challenges, analyzing the current potential and challenges; and future visions with possible challenges is important, conducted as an spontaneous effort by NASA, ISRO, CNSA, Space-X and other space agencies. This theoretical research will help us to find scope, challenge and method to solve those chaos related to space engine’s efficiency in multiple time frame. Historic data will give us a mind set about our past experience of solving restriction giving us general ideas to solve future probable problems in propellant or fuel and design of rocket engine. History of primitive engine initiated since 1794 in Thomas Mead’s gas engine, Robert Street’s combustion engine in 1794, Francois Isaac de Rivaz’s electric spark followed by industrial utilization of Samuel Brown’s engine in 1823. Subsequently, all had set a base for the first liquid propellant rocket engine of Robert Goddard’s facilitated by Felix Wankel’s piston-less eccentric rotary engine design triggering today’s biggest space travel vision ultimately necessary for modern world in order to understand universe, and space exploration coupled with mass inter-stellar emigration. Hence, we shall discuss about the historic problems of space engine with their solution made till date, instantaneous situation and complication in space engine coupled with future vision and obstacles with their suitable solutions. For instance; the the factors responsible for the improvement of propellant efficiency, Isp relations with ve, Fn produced giving us mass ratio and various issues variability with the propellant used to produce an exhaust impact. By the help of comparative study of various engine’s propellant and design, we can figure out future space engine challenges and solution. Here, we shall also discuss the changes brought in structure of physically powered rocket (cold gas thruster, water rocket), chemically powered rocket(solid rocket, hybrid rocket, mono-propellant rocket, bi-propellant rocket, dual mode propulsion rocket, tri-propellant rocket, air-augmented rocket, turbo rocket, precool-ed jet engine/LACE, electrically powered (resistojet rocket, arc jet rocket, variable specific impulse magneto-plasma rocket, pulsed plasma thruster, ion propulsion system), thermal powered, solar thermal powered, beamed thermal powered, nuclear thermal powered(radioscope rocket, nuclear fission energy), nuclear propulsion powered(gas core reactor rocket, fission fragment rocket,fission sail, nuclear salt-water rocket, nuclear pulse propulsion, antimatter catalyzed nuclear pulse propulsion fusion energy, and antimatter rocket) due to properties of propellant used in combustion chamber.