A LABSCALE HYBRID ROCKET MOTOR IGNITION SYSTEM | ||||
The International Conference on Applied Mechanics and Mechanical Engineering | ||||
Article 16, Volume 15, 15th International Conference on Applied Mechanics and Mechanical Engineering., May 2012, Page 1-20 PDF (1.15 MB) | ||||
Document Type: Original Article | ||||
DOI: 10.21608/amme.2012.36912 | ||||
View on SCiNiTO | ||||
Authors | ||||
A. E. Makled1; H. E. Mostafa1; M. A. Al-Sanabawy1; M. J. Al-Timimi2 | ||||
1Egyptian Armed forces. | ||||
2Bahrain Armed Forces. | ||||
Abstract | ||||
ABSTRACT The hybrid propulsion has the superiority of safety (Non-explosive), simplicity (high reliability), low environmental pollution and available technology over traditional solid and liquid propulsion, all these benefits have a tendency to low cost and laboratory work. Classical hybrid rocket motor (HRM), however have suffered from slow fuel regression rate, relatively poor combustion efficiency and still in search of safety ignition system. The direct goal of the paper is to realize a functioning test, evaluating the performance of a designed Small-Scale Hybrid Rocket Motor (SSHRM) and prepared for laboratory firing tests. Moreover, the objective is extended to examine different types of ignition methods (pyrotechnic charge, fuse wire, heat wire and finally hot oxidizer method by using heat exchanger), which are proposed as very safe ignition method and finally recognize phenomena of re-start operation. Various fuel grains with different configuration of Polyethylene (PE), metalized PE (PE+AL) and Polymethyle-methacrylate (PMMA) were developed and it is decided to use the commercial gaseous oxygen, for its availability and low cost. A SSHRM has been designed, manufactured and tested at various conditions with high level of safety. Ignition by hot air has been proved to be a very attractive ignition method for SSHRM, for its higher safety, higher reliability and acceptable delay time. Adding Al powder to PE fuel proved to have more smooth fuel grain surface with less plume soot, higher regression rate and combustion efficiency, less combustion instability, ignition delay time and nozzle life compared with pure PE combustion. Finally; the re-start operation was demonstrated several times and can be carried out more easily with hot air ignition method. | ||||
Keywords | ||||
Small Scale Hybrid Rocket Motor; ignition system; re-start phenomena; metal powder additive | ||||
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