Investigation of Solid Propellant Rocket Engine – An Theoretical Approach
Journal Title: International Journal of engineering Research and Applications - Year 2017, Vol 7, Issue 9
Abstract
Solid propellant rockets are mostly playing important role in assisted-takeoff missiles, projectiles and a number of other applications. For small rocket missiles solid propellant rocket is widely used because of its suitability and performance along with the geometrical orientation. But when we consider high range rocket missiles, a solid propellant rockets are not suitable, because of its low specific impulse and high speed. A solid propellant rocket also have a disadvantages of limitation in burning duration. Difficult to control the burning of the propellant as well as cooling of the thrust chamber. There is no universal well-defined procedure or design method for making a design of solid propellant rocket engine. Even though we followed some common concepts while making a design of solid propellant rocket engine, there also some critical problems occur. In order to rectify such a problems we should take almost care on propellant grain and grain configuration and propellant ingredients. In this paper we discuss in detail about analysis of solid propellant rocket engine though a theoretical approach. The operation and design of rocket engine is purely depends on the combustion characteristics of the propellant, its burning rate, burning surface and grain geometry.
Authors and Affiliations
Siva V
Keywords
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- EP ID EP392404
- DOI 10.9790/9622-0709057375.
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