2D CFD Analysis of Combustion in Eight Legged Star Shaped Perforation

ISBN-13: 9783659694905 / Angielski / Miękka / 2015 / 92 str.

Pandey Krishna;Deb Sunita

Opis

Chemical rocket propellants undergo exothermic chemical reactions to produce hot gases which expand and push on a nozzle, which accelerates them until they rush out of the back of the rocket at extremely high speed. They can be basically classified into two types, liquid propellants and solid propellants. Solid propellants can be basically classified into double base propellant and composite propellant. Solid propellants are used in forms called grains. A grain is any individual particle of propellant regardless of the size or shape. The shape and size of a propellant grain determines the burn time, amount of gas and rate produced from the burning propellant and consequently thrust vs time profile. Most commonly used solid propellant is ammonium perchlorate composite propellant with Hydroxyl Terminated Polybutadiene (HTPB) binder. Ammonium perchlorate decomposes to give oxidizer molecules and HTPB decomposes to give out fuel molecules. The exothermic reactions that sustain the combustion process occur in solid, surface and the gaseous phase and thus comprise complex chemical kinetics.

O autorze

Professor Pandey received his B.Tech in Mechanical Engineering from IIT Varanasi n 1980, M.Tech in Heat Power in 1987 from the same institute in January 1987. He obtained Ph.D. in Mechanical Engineering from IIT,Kanpur in 1994.He has joined as faculty in Mechanical Engineering in the National Institute of Technology Silchar on 6th January 1987.