Static Thrust Measurement of Two Types of Perforated Solid Propellant Grain Configurations
Publication: Journal of Aerospace Engineering
Volume 25, Issue 4
Abstract
A laboratory scale experimental setup has been developed to explore an alternative source of solid propellant. A combination of potassium nitrate and ferric oxide embedded in epoxy binder constitutes the ingredients of the propellant used. A scanning electron microscope and nondestructive test (X-ray radiography) were utilized to study the crack surface and internal structure of the cured propellants. The influence of the epoxy mixing ratio on the sample density has been studied. Two solid propellant grain configurations were utilized to study the performance characteristics in terms of the thrust generated. It was found that the manufacturer’s mixing ratio provided the optimum density results for the given set of configurations tested. The multiperforated grain configuration showed higher performance in terms of trust when compared with the single perforated grain configuration.
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Acknowledgments
The writers acknowledge the support provided through the Short Term Grant (No. 304/6035303) by Universiti Sains Malaysia in carrying out this work. The writers would also like to express their sincere gratitude to Dr. Khazali Haji Zin and his team from SIRIM Berhad, Malaysia, for their support and technical advice.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 25 • Issue 4 • October 2012
Pages: 653 - 659
Copyright
© 2012 American Society of Civil Engineers.
History
Received: Jan 3, 2011
Accepted: Jul 28, 2011
Published online: Jul 30, 2011
Published in print: Oct 1, 2012
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