Othman, Norazila and Wan Ali, Wan Khairuddin (2010) Development of ammonium perchlorate plus aluminium base solid propellant. In: 10th Asian International Conference On Fluid Machinery, 2010, Kuala Lumpur, Malaysia.
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Official URL: http://dx.doi.org/10.1063/1.3464952
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.
|Item Type:||Conference or Workshop Item (Paper)|
|Uncontrolled Keywords:||bubbles, combustion, compressible flow, drops and bubbles, flames, combustion, compressible flows, shock waves|
|Subjects:||T Technology > TJ Mechanical engineering and machinery|
|Deposited By:||Liza Porijo|
|Deposited On:||27 Jul 2012 07:46|
|Last Modified:||07 Feb 2017 07:22|
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