Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
권호 표지
DOI QR코드

DOI QR Code

Flow Characteristics with Distance between Solid Propellant Grain and Igniter

고체 추진제와 점화기 간 간격에 따른 유동 특성

  • Received : 2017.06.14
  • Accepted : 2017.07.23
  • Published : 2018.04.01
Download PDF
⟨ Previous Next ⟩

Abstract

Flow analysis using computational fluid dynamics was conducted to investigate the effect of the igniter flame caused by the gap between the igniter and the propellant grain in a solid rocket motor. Two propellant grain types were assumed; namely cylinder type (1 mm, 3 mm, and 5 mm gap) and the slot type. The slot type had two igniter hole locations. One was located at the small gap of the propellant grain, and the other one was located at the large gap. In the case of the cylinder type, the pressure in the igniter zone was higher with a thinner gap. Additionally, in the case of the cylinder type, the pressure difference between the igniter installed zone and the free volume was also higher as the gap became lower. The cylinder types were affected by the gap distance, but the slot types were not. Moreover, the results of the slot types were similar to the 5-mm gap case of the cylinder type.

고체추진기관 내에 점화기와 추진제 그레인 간격에 따라 화염에 의해 발현되는 내부 유동 형태에 대해 전산유체해석(CFD)를 이용하여 살펴보았다. 실린더형과 슬롯형 추진제 그레인에 대해 실린더형은 간격 1 mm, 3 mm, 5 mm, 슬롯형은 점화기의 화염 분출구가 넓은 간격에 위치한 경우와 좁은 간격에 위치한 경우에 대해 수치 해석을 수행하였다. 실린더형은 간격이 좁을수록 점화기와 추진제 사이에 고압력이 형성되며, 점화기 말단 부근에서 압력 강하 또한 상대적으로 크게 나타났다. 실린더형은 간격에 영향을 받았으나, 슬롯형은 화염 분출구 위치에 관계없이 압력 형태가 유사하게 나타났으며, 실린더형 간격 5 mm와 유사한 결과를 보였다.

Keywords

References

  1. Cho, I.H., Baek, S.W., Chang, S.T. and Cha, H.S., "A Numerical Simulation of Ignition Transient on the Solid rocket Motor," The Korean Society For Aeronautical And Space Sciences Fall Conference, Jeju, Korea, pp. 212-216, Nov. 1995.
  2. Serraglia, F., "Modeling and Numerical Simulation of Ignition Transient of Large Solid Rocket Motors," Dottorato di Ingengneria Aerospaspaziale XV Ciclo, La Sapienza University of Rome, 2002/2003.
  3. Cho, I.H., Baek, S.W., Chang, S.T. and Cha, H.S., "A Numerical Simulation of Axisymmetric Solid Rocket Motor Ignition Transient with Radiation Effect," The Korean Society For Aeronautical And Space Sciences, Vol. 25, No. 2, pp. 81-88, 1997.
  4. Cho, I.H., and Baek, S.W., "Numerical Simulation of Axisymmetric Solid Rocket Motor Ignition Transient with Radiation Effect," Journal of Propulsion and Power, Vol. 16, No. 4, pp. 725-728, 2000. https://doi.org/10.2514/2.5636
  5. Sanal, K.V.R. and Kim, H.D., "Studies on Starting Transient in Solid Rockets," The Korean Society of Propulsion Engineers Conference, pp.6-10, Oct. 2003.
  6. Lee, C.S., Han, S.H., Kim, C.G., Oh, J.Y. and Oh, S.J., "Fluid-Structure-Combustion Intera ction Simulation for Solid Propellant Rocket Interior Coupling Phenomena," The Korea Institude of Military Science and Technology, Jeju, Korea, Jul. 2013.
  7. Lee, C.S., Han, S.H., Kim, C.G., Oh, J.Y. and Oh, S.J., "FSbI simulation for solid propellant rocket interior with flame propagation delay and secondary burning," The Korea Institude of Military Science and Technology, Jeju, Korea, Jun. 2014.
  8. Chang, S.T., Han, S.M. and Chai, J.C., "Ignition Transient Investigation of Rocket Motor," Journal of Propulsion and Power, Vol. 4, No. 3, pp. 45-54, 2000.
  9. Jang, S.G., Kim, Z.I. and Ryu, B.T., "Ignition Delay Time of A Solid Rocket Motor," The Korean Society For Aeronautical And Space Sciences Fall Conference, Jeju, Korea, pp. 1038-1041, Nov. 2012.
  10. Konstantin, K., "Unstructured Hexa hedral Non-conformal Mesh Generation," the degree of Doctor in Engineering Sciences, Department of Mechanical Engineering, Vrije Universiteit Brussel, Belgium, 2005.
  11. Choi, J.S., Kim, I.S., Lee, H.J. and Cho, J.H., "Ignition Characteristic of the Amount of Ignition Compound Used for the Solid Rocket," The Korean Society For Aeronautical And Space Sciences Spring Conference, Goseong, Korea, pp. 206-208, Apr. 2014.