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논문 기본 정보

자료유형
학술저널
저자정보
Jeongmoo Huh (Korea Advanced Institute of Science and Technology) Byeonguk Ahn (Korea Advanced Institute of Science and Technology) Youngil Kim (Korea Advanced Institute of Science and Technology) Hyunki Song (Space Solutions Co) Hosung Yoon (Space Solutions Co) Sejin Kwon (Korea Advanced Institute of Science and Technology)
저널정보
한국항공우주학회 International Journal of Aeronautical and Space Sciences International Journal of Aeronautical and Space Sciences Volume.18 Number.3
발행연도
2017.9
수록면
512 - 521 (10page)
DOI
10.5139/IJASS.2017.18.3.512

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This paper reports development process of a university-based sounding rocket using simplified hybrid rocket propulsion system for low-altitude flight application. A hybrid propulsion system was tried to be designed with as few components as possible for more economical, simpler and safer propulsion system, which is essential for the small scale sounding rocket operation as a CanSat carrier. Using blow-down feeding system and catalytic ignition as combustion starter, 250 N class hybrid rocket system was composed of three components: a composite tank, valves, and a thruster. With a composite tank filled with both hydrogen peroxide(H₂O₂) as an oxidizer and nitrogen gas(N₂) as a pressurant, the feeding pressure was operated in blowdown mode during thruster operation. The MnO₂/Al₂O₃ catalyst was fabricated for propellant decomposition, and ground test of propulsion system showed the almost theoretical temperature of decomposed H₂O₂ at the catalyst reactor, indicating sufficient catalyst efficiency for propellant decomposition. Auto-ignition of the high density polyethylene(HDPE) fuel grain successfully occurred by the decomposed H₂O₂ product without additional installation of any ignition devices. Performance test result was well matched with numerical internal ballistics conducted prior to the experimental propulsion system ground test. A sounding rocket using the developed hybrid rocket was designed, fabricated, flight simulated and launch tested. Six degree-of-freedom trajectory estimation code was developed and the comparison result between expected and experimental trajectory validated the accuracy of the developed trajectory estimation code. The fabricated sounding rocket was successfully launched showing the effectiveness of the simplified hybrid rocket propulsion system.
#Hybrid sounding rocket #Hydrogen peroxide #Polyethylene #Flight test

목차

Abstract
1. Introduction
2. Design of the propulsion system
3. Propulsion system performance test
4. Sounding rocket system configuration and flight testing
5. Conclusion
References

참고문헌 (42)

참고문헌 신청
Hass, N. E., Smart, M. K. and Paull, A., “Flight Data Analysis of HyShot 2”, 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Coference, AIAA, Capua, Italy, 2005. Gardner, A., Hannemann, K., Steelant, J. and Paull, A., “Ground Testing of the Hyshot Supersonic Combustion Experiment in HEG and Comparison with Flight Data”, 40th AIAA Joint Propulsion Conference, AIAA, Florida, USA, 2004. Paiva, K. V., Mantelli, M. B. H. and Slongo, L. K., “Experimental Testing of Mini Heat Pipes Under Microgravity Conditions Aboard a Suborbital Rocket”, Aerospace Science and Technology, Vol. 45, 2015, pp. 367-375. doi:10.1016/j.ast.2015.06.004 Stamminger, A., “Re-Entry Analysis of Research Rocket Payloads”, 62nd International Astronautical Congress, The International Astronautical Federation, Cape town, South Africa, 2010. Lingard, J. S., Saunders, A., Merrifield, J., Caldwell, J., Longo, J. and Ferracina, L., “Supersonic Parachute Testing Using a MAXUS Sounding Rocket Piggyback Payload”, 8th European Symposium on Aerothermodynamics for Space Vehicles Proceedings, European Space Agency, Lisbon, Portugal, 2015.

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