DOI QR코드

DOI QR Code

Thrust modulation performance analysis of pintle-nozzle motor

핀틀 노즐형 로켓 모타의 추력 조절 성능에 관한 연구

  • 김중근 (국방과학연구소 1기술본부 6부) ;
  • 박종호 (충남대학교 BK21 메카트로닉스사업단)
  • Published : 2009.04.01

Abstract

Theoretical thrust equations for the diverse nozzle expansion condition were derived. By using the obtained thrust equations, parametric studies were carried out to estimate the effect of pressure exponent, minimum operation pressure, ambient pressure and extinguishment pressure on thrust modulation performance in pintle-nozzle solid rocket motors. Analysis results showed that thrust turndown ratio can be easily attained by small nozzle-throat area variation at high pressure exponent, low minimum operation pressure, high ambient pressure and high extinguishment pressure condition. At those conditions, the highest chamber pressure to obtain the intended thrust turndown ratio can be minimized.

노즐의 팽창 조건에 따라 적용할 수 있는 이론적인 추력을 구하고 구해진 추력식을 이용하여 고체 추진기관의 추력을 조절하는 핀틀 추진기관의 설계변수, 즉 압력지수, 최소 작동압력, 대기압, 소화압력이 추력 조절 성능에 미치는 영향을 분석하였다. 분석결과 압력지수가 클수록, 최소 작동압력이 낮을수록, 대기압이 높을수록, 그리고 소화압력이 높을수록 핀틀로 노즐목 면적 크기를 조금만 조절하여도 낮은 연소관 압력 조절 범위에서 충분히 원하는 추력비를 얻을 수 있음을 확인하였다.

References

  1. John Napior and Victoria Garmy, "Controllable Solid Propulsion For Launch Vehicle And Spacecraft Application", AIAA 2006-905, 2006.
  2. Ho-Girl Jung, Changjin Lee and Jae-Woo Lee," Role of Radiation on Dynamic Extinction by Depressurization in Metalized Solid Propellants", Journal of Propulsion and Power, Vol. 20, No. 3, 2004, pp. 432-439 https://doi.org/10.2514/1.10384
  3. Merkle, C. L., Turk, S. L., and Summerfield, M., "Extinguishment of Solid Propellants by Depressurization: Effects of Propellant Parameters", AIAA 69-176, 1969.
  4. D. C. Sayles, "The development of test motors for advanced controllable propellants", AIAA 73-1206, 1973.
  5. Stephanie Joner and Isabelle Quinquis, “Control of an exoatmospheric Kill Vehicle with a solid propulsion Attitude Control System”, AIAA 2006-6572, 2006.
  6. Mattingly, J. D.,"Element of Gas Turbine Propulsion", McGraw-Hill series, 1996
  7. Summerfield M., Foster C., and Swan W.,"Flow separation in Overexpanded Supersonic Exhaust Nozzle", Jet propulsion, Vol. 24, No. 9, pp. 319-321,1954
  8. Maurice J. Zucrow and Joe D. Hoffman, "Gas Dynamics", John Wiley & Sons, INC., 1976
  9. George P. Sutton," Rocket Propulsion Element-An Introduction to the Engineering of Rockets", John Wiley & Sons, INC.,1992
  10. Michel A. Saad, "Compresible Fluid Flow", Prentice Hall, INC.,1985.

Cited by

  1. Performance Analysis of the Pintle Thruster Using 1-D Simulation -I : Steady State Characteristics vol.43, pp.4, 2015, https://doi.org/10.5139/JKSAS.2015.43.4.304
  2. Study on Flow Analysis of Hot Gas Valve with Pintle vol.19, pp.6, 2015, https://doi.org/10.6108/KSPE.2015.19.6.019
  3. Study on Transient Analysis of Hot Gas Valve with Pintle vol.22, pp.2, 2018, https://doi.org/10.6108/KSPE.2018.22.2.152