HYBRID ROCKET ENGINE TEST FACILITY DESIGN
Keywords:
Hybrid Rocket Engine, Rocket Propulsion, Gaseous Oxygen, PMMAAbstract
Hybrid rocket engines is relatively less researched subject of chemical rockets. Using fuel and oxidizer in different phases hybrids are safe and cheap. Yet, they are not generating enogh thrust to deliver heavy payloads to edge of space. Continuing researches on low regression rates, combustion instabilities and propellant diversity would carry this very subject to space.
In this essay, a lab-scale hybrid rocket engine is designed and performance calculations of this design is executed. As an interdisciplinary study, hybrid facility’s engine components are detail-designed, other components are explained as an input. PMMA and gaseous oxygen are chosen as fuel and oxidizer respectively due to their ease of availability and low-cost.
Hybrid engine components, main oxidizer system, ignition system and data acqusition system is studied in this thesis. Hybrid engine, shaped according to calculations, is modified to be compatible with off the shelf products for the ease of manifacture.Axial flow hybrid motor with a single injector is examined, including single port fuel grain. With the addition of DAQ sub-system, it would be available to record instant pressure and temperature values to study on. The main components of DAQ sub-system are included in related chapter.
Our country does nor accomodate any ready-to-use hybrid rocket test facility. With the finding of sufficient funds and appropriate schedule it’s not a matter of subject having the first facility in Turkish Air Force Academy.
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[2] Chiaverini, M., & Kuo, K. (2007). Fundamentals of Hybrid Rocket Propulsion and Combustion (Vol. 218). (F. Lu, Ed.) Virginia: American Institute of Aeronautics and Astronautics.
[3] Conley, E., & Valencia, J. (2012). Hybrid Rocket Experiment Station for Capstone Design. New Mexico: New Mexico State University.
[4] Davydenko, N. A., Gollender, R. G., Gubertov, A. M., Mironov, M. M., & Volkov, N. N. (2007, 11). Hybrid Rocket Engines: The Benefits and Prospects. Aerospace Science and Technology, s. 55-60.
[5] Dunn, Z., Dyer, J., Lohner, K., Doran, E., Bayart, C., Sadhwani, A., . . . Cantwell, B. (2007). Test Facility Development for the 15,000 lf Thrust Peregrine Hybrid Sounding Rocket. 43rd AIAA/ASME/SAE/ASEE Joint Propulison Conference & Exhibit. Cincinnati: American Institute of Aeronautics and Astronautics.
[6] Einav, O., Peretz, A., Hashmonay, B.-A., Birnholz, A., & Sobe, Z. (2009). Development of a Lab-Scale System for Hybrid Rocket Motor Testing. 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Colorado: American Institute of Aeronautics and Astronautics.
[7] Electric Actuators. (2015, 05 01). Swagelok: www.swagelok.com adresinden alınmıştır
[8] Gomes, S. R., Junior, L. R., Rocco, J. A., & Iha, K. (2011). Design and Testing of a Hybrid Rocket Motor. 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. California: American Institute of Aeronautics and Astronautics.
[9] Grosse, M. (1997). Development Work On a Small Experimental Hybrid Rocket. 33rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Seattle: American Institute of Aeronautics and Astronautics.
[10] Jefferson 2026 Series. (2014, 12 10). Jefferson: www.jefferson.com adresinden alınmıştır
[11] Karabeyoğlu, M. A. (2008). Hybrid Rocket Propulsion for Future Space launch. California: Space Propulsion Group Inc.
[12] Karabeyoğlu, M. A. (2013). AA 284a / MECH 427 Advanced Rocket Propulsion. İstanbul: Koç Üniversitesi.
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