PowerPoint

Karary University College of Engineering Aeronautic Engineering Department

Project name : design of liquid propellant rocket thruster Prepared by :-Hosham Mohamed Ahmed AlawadMohamed Abo Algasim Ali

Supervisor:-Colonel , Dr .MotwaKil Abd allah Suliman

Contents : - Introduction Objectives Methodology Project plan Work done References

Introduction

A liquid rocket engine employs liquid propellants which are fed under pressure from tank in to a combustion chamber. The propellants usually consist of a liquid oxidizer and a liquid fuel.

In the combustion chamber the propellants chemically react (burn) to form hot gases which are then accelerated and ejected at high velocity through a nozzle, thereby imparting momentum to the engine.Momentum is the product of mass and velocity.

The thrust force of a rocket motor is the reaction experienced by the motor structure due to the ejection of the high velocity matter.

Applications :

V-2 rocket .DF-4 rocket .Shihab-1

Objectives We aim to design and fabricate liquid rocket thruster (include combustion chamber and nozzle ) .Methodology: AnalyticalEquations of rocket motion , thermodynamic Relations and equations of the chemical propellant .Software :Numerical using MATLAB.Analysis & CFD using fluent & GAMBIT.

Project plan : Stages :Search for belongings of project .Mathematical methods in the analysis . CFD programing .Fabrication

Work done 1

234567891011121314Stage -1Stage -2Stage -3Stage -4 Work done

Studies about thrusts .Studies about nozzles. Studies about method of characteristic .Cfd programming .

references :GEORGEP SUTTON & OSCAR BIBLARZ Rocket, Propulsion Elements , Seventh Edition, A Wiley-lnterscience Publication, .Martin J.L.Turner, Rocket and spacecraft propulsion, 3d edition, Praxis Publishing. Dieter K. Huzel and David H. Huang ,Design of liquid propellant engine , 1997, Rocketdyne Division North American Aviation Inc , .

End