Experimental Study of the Swirling Oxidizer Flow in HTPB/N2O Hybrid Rocket Motor
Effects of swirling oxidizer flow on the performance of a HTPB/N2O Hybrid rocket motor were studied. A hybrid propulsion laboratory has been developed, to characterize internal ballistics characteristics of swirl flow hybrid motors and to define the operating parameters, like fuel regression rate, s...
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| Format: | Article |
| Language: | English |
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Wiley
2017-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2017/3174140 |
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| author | Mohammad Mahdi Heydari Nooredin Ghadiri Massoom |
| author_facet | Mohammad Mahdi Heydari Nooredin Ghadiri Massoom |
| author_sort | Mohammad Mahdi Heydari |
| collection | DOAJ |
| description | Effects of swirling oxidizer flow on the performance of a HTPB/N2O Hybrid rocket motor were studied. A hybrid propulsion laboratory has been developed, to characterize internal ballistics characteristics of swirl flow hybrid motors and to define the operating parameters, like fuel regression rate, specific impulse, and characteristics velocity and combustion efficiency. Primitive variables, like pressure, thrust, temperature, and the oxidizer mass flow rate, were logged. A modular motor with 70 mm outer diameter and variable chamber length is designed for experimental analysis. The injector module has four tangential injectors and one axial injector. Liquid nitrous oxide (N2O) as an oxidizer is injected at the head of combustion chamber into the motor. The feed system uses pressurized air as the pressurant. Two sets of tests have been performed. Some tests with axial and tangential oxidizer injection and a test with axial oxidizer injection were done. The test results show that the fuel grain regression rate has been improved by applying tangential oxidizer injection at the head of the motor. Besides, it was seen that combustion efficiency of motors with the swirl flow was about 10 percent more than motors with axial flow. |
| format | Article |
| id | doaj-art-f6b472292e8e4c60bee856df5ce427b1 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2017-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-f6b472292e8e4c60bee856df5ce427b12025-02-03T05:44:24ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742017-01-01201710.1155/2017/31741403174140Experimental Study of the Swirling Oxidizer Flow in HTPB/N2O Hybrid Rocket MotorMohammad Mahdi Heydari0Nooredin Ghadiri Massoom1Malek Ashtar University of Technology, Babaei Highway, Lavizan, Tehran 15875-1774, IranMalek Ashtar University of Technology, Babaei Highway, Lavizan, Tehran 15875-1774, IranEffects of swirling oxidizer flow on the performance of a HTPB/N2O Hybrid rocket motor were studied. A hybrid propulsion laboratory has been developed, to characterize internal ballistics characteristics of swirl flow hybrid motors and to define the operating parameters, like fuel regression rate, specific impulse, and characteristics velocity and combustion efficiency. Primitive variables, like pressure, thrust, temperature, and the oxidizer mass flow rate, were logged. A modular motor with 70 mm outer diameter and variable chamber length is designed for experimental analysis. The injector module has four tangential injectors and one axial injector. Liquid nitrous oxide (N2O) as an oxidizer is injected at the head of combustion chamber into the motor. The feed system uses pressurized air as the pressurant. Two sets of tests have been performed. Some tests with axial and tangential oxidizer injection and a test with axial oxidizer injection were done. The test results show that the fuel grain regression rate has been improved by applying tangential oxidizer injection at the head of the motor. Besides, it was seen that combustion efficiency of motors with the swirl flow was about 10 percent more than motors with axial flow.http://dx.doi.org/10.1155/2017/3174140 |
| spellingShingle | Mohammad Mahdi Heydari Nooredin Ghadiri Massoom Experimental Study of the Swirling Oxidizer Flow in HTPB/N2O Hybrid Rocket Motor International Journal of Aerospace Engineering |
| title | Experimental Study of the Swirling Oxidizer Flow in HTPB/N2O Hybrid Rocket Motor |
| title_full | Experimental Study of the Swirling Oxidizer Flow in HTPB/N2O Hybrid Rocket Motor |
| title_fullStr | Experimental Study of the Swirling Oxidizer Flow in HTPB/N2O Hybrid Rocket Motor |
| title_full_unstemmed | Experimental Study of the Swirling Oxidizer Flow in HTPB/N2O Hybrid Rocket Motor |
| title_short | Experimental Study of the Swirling Oxidizer Flow in HTPB/N2O Hybrid Rocket Motor |
| title_sort | experimental study of the swirling oxidizer flow in htpb n2o hybrid rocket motor |
| url | http://dx.doi.org/10.1155/2017/3174140 |
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