Study and Conceptual Design on Cryogenic-Nuclear Propulsion System for Interplanetary & Leo Mission

Abstract

In the past years, Space technology has developed exponentially, and this growth has made the dream of every man to realize interplanetary missions just a stone s throw away. The reason for such exponential growth is the curiosity to understand, research and explore other celestial objects and various other phenomena that are present in this vast universe. To realize this, various propulsion systems have been designed, tested and experimented for its usage in space exploration by countries like USA and Russia, while there are some advanced propulsion systems which remain in the conceptual phase due to lack of resources, technology and safety concerns in the present day. This paper highlights a study done on the use of a combination of advanced propulsion systems which would be an add on to the existing Nuclear Cryogenic Propulsion Stage (NCPS) designed by NASA. A conceptual design is proposed to use the Cryogenic propulsion system (CPS) with Nuclear Thermal propulsion system (NTS) for various spaceflight missions at the same time considering the affordability, viability, safety concerns and complexity involved with it. This design of combined propulsion system will focus more on CPS, to be used as a source of propellant for achieving higher specific impulse and thrust while in the atmosphere and in outer space with NTS and to provide more efficient cooling for Nuclear reactor core and the Nozzle. This makes it possible to conduct various interplanetary spaceflight missions at a longer distance as well as above LEO orbit missions with optimal use of the resources and time. The paper will also provide an insight into the testing s done on NCPS and its applicability on the conceptual design to make it efficient and reliable. Further, a thorough compared analysis of NCPS with other advanced propulsion devices is done as well as with separate NTS and CPS propulsion systems, concerning mass budget, thrust to weight ratio, materials, geometry and various other parameters, to realize the benefits which could be obtained from the conceptual design proposed. Such propulsion systems would reduce exposure of spacecraft to harmful space radiation and other effects of long-term space missions and may help in transporting heavy payloads when used with other systems to make Interplanetary and above LEO orbit missions more expeditious.