DOI QR코드

DOI QR Code

A Correlation between the Pressure Oscillation of Combustion Chamber and Thrust Response in a 70 N-class Hydrazine Thruster

70 N급 하이드라진 추력기의 연소실 압력진동 강도와 추력 응답특성의 상관관계

  • Jung, Hun (Department of Mechanical Engineering, Graduate School, Pukyong National University) ;
  • Kim, Jeong Soo (Department of Mechanical Engineering, Pukyong National University)
  • Received : 2015.04.11
  • Accepted : 2015.05.13
  • Published : 2015.06.01

Abstract

A ground hot-firing test(HFT) was accomplished to draw a correlation between the pressure oscillation intensity of combustion chamber and thrust response characteristics in a 70 N-class hydrazine thruster which has been developed recently. Monopropellant grade hydrazine was adopted as a propellant for the HFT, and combustion-chamber characteristic length, propellant injection pressure were applied as test parameters. It was confirmed that the decrease of thrust-chamber diameter and injection pressure augmented the pressure oscillation of stagnation chamber in the test condition specified, and the oscillation hampered the pulse response performance of test models.

Acknowledgement

Supported by : 한국연구재단

References

  1. Jung, H., Kim, J.H. and Kim, J.S., "Test and Evaluation of a 70 N-class Hydrazine Thruster for Application to the Precise Attitude Control of Space Vehicles," 49th Joint Propulsion Conference, San Jose, CA, USA, AIAA 2013-3987, Jul. 2013.
  2. Kim, J.H., Jung, H. and Kim, J.S., "Pulse-mode Performance Characteristics of a Small Liquid-monopropellant Rocket Engine," 5th European Conference for Aeronautics and Space Sciences, Munich, Germany, A376, Jul. 2013.
  3. Kim, J.H., Jung, H. and Kim, J.S., "Test and Evaluation for the Configuration Optimization of Thrust Chamber in 70 N-class N2H4 Thruster - Part I: Pulse-mode Performance According to the Chamber Diameter Variation," Journal of the Korean Society of Propulsion Engineers, Vol. 18, No. 1, pp. 42-49, 2014.
  4. Jung, H., Kim, J.H. and Kim, J.S., "Test and Evaluation for the Configuration Optimization of Thrust Chamber in 70 N-class N2H4 Thruster - Part II: Pulse-mode Performance According to the Chamber Length Variation," Journal of the Korean Society of Propulsion Engineers, Vol. 18, No. 1, pp. 50-57, 2014. https://doi.org/10.6108/KSPE.2014.18.1.050
  5. Sutton, G.P. and Biblarz, O., Rocket Propulsion Elements, 7th Ed., John Wiley & Sons Inc., New York, NY, USA, pp. 282-308, 2001.
  6. Price, T.W. and Evans, D.D., "The Status of Monopropellant Hydrazine Technology," NASA Technical Report 32-1227, 1968.
  7. Harrje, D.T. and Reardon, F.H., "Liquid Propellant Rocket Combustion Instability," NASA SP-194, 1972.
  8. Jung, H., Kim, J.H. and Kim, J.S., "Characteristics of the Pressure Instability in a Hydrazine Thruster with Various Length-to-Diameter Ratio of Catalyst-bed," Journal of the Korean Society of Propulsion Engineers, Vol. 18, No. 6, pp. 19-26, 2014. https://doi.org/10.6108/KSPE.2014.18.6.019
  9. DOD(USA), "Performance Specification (Propellant, Hydrazine)," MIL-PRF-26536F, 2011.
  10. Gordon, S. and McBride, B.J., "Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications," NASA RP-1311, 1994.
  11. Jeon, S., Kim, J. and Choi, H., "Development of a Thrust Measurement System," Proceedings of World Academy of Science, Engineering and Technology, No. 63, pp. 494-498, 2012.
  12. Kim, J.S., Jung, H., Kam, H.D., Seo, H.S. and Su, H., "A Development of the Thrusters for Space-Vehicle Maneuver/ACS and Their Application to Launch Vehicles," Journal of the Korean Society of Propulsion Engineers, Vol. 14, No. 6, pp. 103-120, 2010.
  13. Sutton, G.P., History of Liquid Propellant Rocket Engines, AIAA Reston, VA, USA, 2006.