Theoretical Investigation of Liquid Propellant Rocket Engine Performance
Journal Title: International Journal of engineering Research and Applications - Year 2018, Vol 8, Issue 3
Abstract
Liquid propellant rockets are economically more suitable for long range operations. For long range missiles liquid propellant rocket is widely used because of its suitability and performance. But when we consider high range rocket missiles, a liquid propellant rockets are not suitable, because of its size and weight is more compared to solid propellant rocket. Many liquid propellants can exist in liquid state at very low temperature itself. When more number of components present in engine panel, causing of vibration is very high and in the case of liquid propellant rocket engine it is very difficult to provide cooling of thrust chamber. There is no universal well-defined procedure or design method for making a design of liquid propellant rocket engine. Even though we followed some common concepts while making a design of liquid propellant rocket engine, there also some critical problems occur. In order to rectify such a problems we should take almost care on propellant selection and propellant ingredients. In this paper we discuss in detail about complete analysis of liquid propellant rocket engine by theoretical approach. The design and operational performance of a rocket engine is purely depends on the combustion characteristics of a propellant, its burning rate, burning surface, nozzle exit area ratio. Keywords – liquid propellants, Propellant burning rate, Propellant burning surface, Thrust co-efficient, Nozzle exit area ratio.
Authors and Affiliations
Siva V
Keywords
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- EP ID EP393812
- DOI 10.9790/9622-0803023841.
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