Performance Evaluation of Hybrid Propellant Rocket Engine
Journal Title: International Journal of engineering Research and Applications - Year 2018, Vol 8, Issue 9
Abstract
Hybrid Propulsion Technique is more suitable to applications requiring throattling and restart of long duration missions. Such application would include primary boost propulsion for vehicles of space launch, upper stages and satallite maneuvering systems. In hybrid techniques speed regulation is possible by regulating the supply of oxidizer. Higher fuel density can attained in case of hybrid propellant rocket system. In hybrid propellant Rocket system the fuel and oxidizer are stored separately, there is no chemical deterioration between fuel and oxidizer. Hybrid rockets are light weight when compared to liquid propellant and solid propellant rocket engines. Higher amount of theoretical specific impulse can be achieved compare to solid and liquid propellant engines. When more number of components available in engine construction, it is very difficult to provide a cooling to Engine thrust chamber. There is no universal well defined procedure or design method for making a design of hybrid propellant rocket engine. In order to rectify such a problems we should take almost care on propellant selection and propellant Incredients. In this paper we discuss in detail about evaluation of hybrid 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 area, nozzle exit area ratio, grain geometry and thrust coefficient.
Authors and Affiliations
Siva V
Keywords
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- EP ID EP395132
- DOI 10.9790/9622-0809015154.
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