Enhancement of regression rate in hybrid rocket motor using various techniques /
A hybrid rocket motor represents a compromise between a solid rocket and a liquid rocket motor. It offers throttling capability, increased safety, moderate cost, in addition to its benign environmental impact. However, low regression rate is a major drawback of hybrid rocket performance. In this wor...
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| Main Author: | |
|---|---|
| Format: | Thesis |
| Language: | English |
| Published: |
Kuala Lumpur:
Kulliyyah of Engineering, International Islamic University Malaysia,
2014
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| Subjects: | |
| Online Access: | http://studentrepo.iium.edu.my/handle/123456789/4772 |
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| 050 | 0 | 0 | |a TL783.45 |
| 100 | 0 | |a Muhammad Hanafi Azami |9 64520 | |
| 245 | 1 | |a Enhancement of regression rate in hybrid rocket motor using various techniques / |c by Muhammad Hanafi Azami | |
| 260 | |a Kuala Lumpur: |b Kulliyyah of Engineering, International Islamic University Malaysia, |c 2014 | ||
| 300 | |a xvii, 119 leaves : |b ill. ; |c 30cm. | ||
| 336 | |2 rdacontent | ||
| 337 | |2 rdamedia | ||
| 338 | |2 rdacarrier | ||
| 502 | |a Thesis (MSME)--International Islamic University Malaysia, 2014. | ||
| 504 | |a Includes bibliographical references (leaves 92-96) | ||
| 520 | |a A hybrid rocket motor represents a compromise between a solid rocket and a liquid rocket motor. It offers throttling capability, increased safety, moderate cost, in addition to its benign environmental impact. However, low regression rate is a major drawback of hybrid rocket performance. In this work, a design and simulation codes are developed to size the rocket, analyze its performance both in steady state and transience. The codes are based on a legacy interior ballistic model and developed using MATLAB® environment. The codes were also used to analyze the temporal variation of regression rate, specific impulse and thrust with different initial design features; different nozzle expansion ratios, different initial mass fluxes, different number of ports used, different type of propellants used, different ports designs and different metallic doping. These design parameters bring a significant effect on hybrid rocket size and performance especially the regression rate. We also develop a lab scale hybrid rocket motor testing facility to study the effect of doping metallic additives. In the test runs, paraffin wax is used as a fuel and gaseous oxygen as the oxidizer. Experimental results reveal that varying the distribution and concentration of metallic additive concentration can improve the regression rate up to 22%. However, the non-homogeneous fuel does not improve the uniformity of the burning fuel but at least it has 70% improve on the regression rate using aluminum powder and 170% increase using zirconium powder. The code shows reasonable consistency with the experimental results. | ||
| 650 | 0 | |a Hybrid propellant rockets |9 64521 | |
| 655 | 7 | |a Theses, IIUM local | |
| 690 | |a Dissertations, Academic |x Department of Mechanical Engineering |z IIUM |9 2174 | ||
| 710 | 2 | |a International Islamic University Malaysia. |b Department of Mechanical Engineering |9 2178 | |
| 856 | 4 | |u http://studentrepo.iium.edu.my/handle/123456789/4772 | |
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