Abo Bibliothek: Guest
Digitales Portal Digitale Bibliothek eBooks Zeitschriften Referenzen und Berichte Forschungssammlungen
International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.28 SNIP: 0.421 CiteScore™: 0.9

ISSN Druckformat: 2150-766X
ISSN Online: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2019028124
pages 367-383

IMPROVEMENT OF COMBUSTION EFFICIENCY USING A BAFFLE PLATE FOR A LT/GOX HYBRID ROCKET MOTOR

Yo Kawabata
Chiba Institute of Technology, Narashino, Chiba, 275-0016, Japan
Y. Wada
Chiba Institute of Technology, Narashino, Chiba, Japan
Ryo Nagase
Chiba Institute of Technology, Narashino, Chiba, 275-0016, Japan
Ryuichi Kato
Akita University, Akita, Akita, Japan
Nobuji Kato
Katazen Corporation, Obu, Aichi, 474-0011, Japan
Keiichi Hori
Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, Japan

ABSTRAKT

In this study, we developed a high-performance, high-thrust hybrid rocket motor using low-melting-point thermoplastic (LT) fuel and a baffle plate compared to conventional hybrid rocket motors using a low regression rate fuel such as hydroxyl terminal polybutadiene (HTPB). LT fuel has excellent mechanical and adhesive properties, as well as a high regression rate compared to conventional hybrid rocket fuel. Static firing tests lasting 10 s using the LT fuel and gaseous oxygen (GOX) were conducted to investigate the influence of different geometric-shaped baffle plates on the characteristic velocity. Tests with baffle plates with two or more holes improved the characteristic velocities and bottom chamber pressures compared to tests without the baffle plate. In the test using a baffle plate with two rows of holes, no improvement in the characteristic velocity was confirmed. This was because the oxidizer and fuel passed through different holes and did not mix. The characteristic velocity using a baffle plate having three holes was ~ 10% higher than without the baffle plate, because the fuel and the oxidizer passed through a common hole and the combustion gas stayed at the top of the baffle plate. In all the experiments, the fuel regression rate was higher than the conventional value, as the back end of the fuel was regressed by the baffle plate and unburned fuel was discharged. These results suggested that when two more baffle plates are set, or an after-combustion chamber is provided on the downstream side, the characteristic velocity is improved.

REFERENZEN

  1. Bettella, A., Lazzarin, M., Bellomo, N., Barato, F., and Pavarin, D., (2011) Testing and CFD Simulation of Diaphragm Hybrid Rocket Motors, 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. Exhibit, AIAA Paper No. 2011-6023.

  2. Ishiguro, T., Shinohara, K., Sakio, K., and Nakagawa, I., (2011) A Study on Combustion Efficiency of Paraffin-Based Hybrid Rockets, 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. Exhibit, AIAA Paper No. 2011-5679.

  3. Karabeyoglu, M.A., Cantwell, B.J., and Altman, D., (2001) Development and Testing of Parafin-Based Hybrid Rocket Fuels, 37th Joint Propulsion Conf. Exhibit, AIAA Paper No. 2001-4503.

  4. Kawabata, Y., Wada, Y., Kato, N., Hori, K., and Nagase, R., (2016) Study on Improvement of Mechanical Characteristics of LT Fuels for Hybrid Rocket, 13th Int. Conf. on Flow Dynamics, Paper No. OS8-22.

  5. Lazzarin, M., Bellomo, N., Barato, F., and Grosse, M., (2010) Numerical Investigation of the Effect of a Diaphragm on the Performance of a Hybrid Rocket Motor, 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. Exhibit, AIAA Paper No. 2010-7033.

  6. Sutton, P.G. and Biblarz, O., (2001) Rocket Propulsion Elements, 7th ed., Hoboken, NJ: Wiley.

  7. Wada, Y., Jikei, M., Kato, R., Kato, N., and Hori, K., (2012) Application of Low Melting Point Thermoplastics to Hybrid Rocket Fuel, Trans. Jpn. Soc. Aeronaut. Space Sci., 10(28), pp. 1-5.

  8. Wada, Y., Kato, R., Kato, N., and Hori, K., (2013) Small Rocket Launch Experiment Using Low Melting Point Temperature Thermoplastic Fuel/N2O Hybrid Rocket, 49th AIAA/ASME/SAE/ASEE Joint Propulsion. Conf., AIAA Paper No. 2013-5050.

  9. Wada, Y., Kawabata, Y., Shinnakazaki, K., Kato, R., Kato, N., and Hori, K., (2014) A Study on Combustion Efficiency Improvement of Low Melting Temperature Thermoplastics as a Hybrid Rocket Fuel, Trans. JSASS Aerospace Tech. Jpn., 12(29), pp. 9-14.

  10. Yuasa, S., Yamamoto, K., Hachiya, H., and Kitagawa, K., (2001) Development of a Small Sounding Hybrid Rocket with a Swirling-Oxidizer-Type Engine, 37th Joint Propulsion Conf. Exhibit, AIAA Paper 2001-3537.


Articles with similar content:

LIQUID OXYGEN VAPORIZATION TECHNIQUES FOR SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINES
International Journal of Energetic Materials and Chemical Propulsion, Vol.10, 2011, issue 2
Takashi Sakurai, Ikuno Kumazawa, Saburo Yuasa, Koki Kitagawa, Toshiaki Sakurazawa
INSENSITIVE HIGH ENERGY BOOSTER PROPELLANT SUITABLE FOR HIGH PRESSURE OPERATION
International Journal of Energetic Materials and Chemical Propulsion, Vol.6, 2007, issue 4
Alan D. Turner, May Lee Chan
A NOVEL POLYETHYLENE PARTICLES/PARAFFIN-BASED SELF-DISINTEGRATION FUEL FOR HYBRID ROCKET PROPULSION
International Journal of Energetic Materials and Chemical Propulsion, Vol.17, 2018, issue 3
Wei Zhang, Yue Tang, Ruiqi Shen, Suhang Chen, Yinghua Ye, Luigi T. De Luca, Hongsheng Yu
PERFORMANCE CHARACTERIZATION OF HYBRID ROCKET FUEL GRAINS WITH COMPLEX PORT GEOMETRIES FABRICATED USING RAPID PROTOTYPING TECHNOLOGY
International Journal of Energetic Materials and Chemical Propulsion, Vol.13, 2014, issue 4
Brendan R McKnight, Thomas J. Curtiss, J. Eric Boyer, Derrick Armold, John D. DeSain, Brian B. Brady, J. K. Fuller, Kenneth K. Kuo
OBSERVATION OF COMBUSTION BEHAVIOR OF LOW MELTING TEMPERATURE FUEL FOR A HYBRID ROCKET USING DOUBLE SLAB MOTOR
International Journal of Energetic Materials and Chemical Propulsion, Vol.15, 2016, issue 5
Ryuichi Kato, Yo Kawabata, Nobuji Kato, Keiichi Hori, Yutaka Wada