Design and Development of Hydrogen Peroxide Monopropellant Thruster: Basic Theory and Performance Calculations

Norazila Othman, Subramaniam Krishnan, Wan Khairuddin Wan Ali

ISBN 10: 3846594067 / ISBN 13: 9783846594063

Published by LAP LAMBERT Academic Publishing 2011-12-29, 2011

About this Item

Seller Inventory # 6666-IUK-9783846594063

Bibliographic Details

• Title: Design and Development of Hydrogen Peroxide Monopropellant Thruster: Basic Theory and Performance Calculations
• Publisher: LAP LAMBERT Academic Publishing 2011-12-29
• Publication Date: 2011
• Language: English
• ISBN 10: 3846594067
• ISBN 13: 9783846594063
• Binding: Paperback
• Condition: New

About this title

Synopsis

Roughly in 1990’s, the concern about lower cost, more environmental friendly and non-toxic propellants showed that hydrogen peroxide can become as an alternative propellant to hydrazine and nitrogen tetroxide for those applications where these propellants were unacceptable. From this issues, the theory and performance calculation of hydrogen peroxide monopropellant thruster are theory concerning about the thrust produced by the thruster and designing of the thruster based on the require thrust. Design and Development of the thruster must be verify by the thruster performance from LabVIEW to the manual calculation. The performance will be compared between the model design and the experiment. Still, the theory and performance calculations falls short of being a complete theory of fundamental monopropellant thruster. Here, experiment results were shown,due to the effect during experiment,repeated experiment were done. From this issue, list of the method for preparing the thruster before firing must be followed by the proper steps and precautions were explained.

About the Author

Mrs. Norazila Othman is a tutor at Universiti Teknologi Malaysia (UTM) with M.Eng. degree specializing in monopropellant rocket motor. Prof Dr. Subramaniam Krishnan and Prof Ir. Dr. Wan Khairuddin Wan Ali are from Faculty of Eng. and Technology, SRM University, India and Dept. of Aeronautics, Faculty of Mech. Eng., UTM, Malaysia respectively.