Development of Ammonium Perchlorate + Aluminium Base Solid Propellant

Rocket propellant has been identified as a component that played an important role in the development of rockets. The ejected material in rocket propulsion is due to material called propellant. Without propellant, a rocket cannot be launched. Due to this reason, many have started to conduct research...

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Bibliographic Details
Published in:Proceedings of the 10th International Conference 2009-10, Vol.1225, p.990-995
Main Authors: Othman, Norazila, Ali, Wan Khairuddin Wan
Format: Article
Language:English
Subjects:
Aluminium
Aluminum
Ammonium perchlorates
Binders
Burning rate
Chemical compounds
Combustion
Ejection
Empirical analysis
Exponents
Fuels
Mathematical analysis
Oxidizers
Perchlorates
Polybutadienes
Propellants
Rocket propellants
Rocket propulsion
Rockets
Solid propellants
Spacecraft components
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Summary:Rocket propellant has been identified as a component that played an important role in the development of rockets. The ejected material in rocket propulsion is due to material called propellant. Without propellant, a rocket cannot be launched. Due to this reason, many have started to conduct research on new chemical compound of propellant with new technique if needed. The objectives of this study are to study the thermo-chemistry aspect of the composition and to determine the burning characteristics parameters. For this reason, this dissertation presented a detail preparation of developing a solid propellant using.Ammonium Perchlorate (AP) as an oxidizer, Aluminum (Al) as fuel and Hydroxyl Terminated Polybutadiene (HTPB) as the binder. To determine the propellant performance such as burning rate, testing was conducted. From testing result the propellant composition oxidizer-fuel (76/11) at pressure 110 Psi gave the maximum burning rate. From test results the empirical constant, 'a' and pressure exponent 'n' were calculated for each different propellant compositions.
ISSN:0094-243X