نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 دانشکده مهندسی هوافضا، دانشگاه صنعتی شریف، تهران، ایران

2 دفتر خدمات فناوری ، دانشگاه صنعتی شریف، تهران، ایران

3 دفتر خدمات فناوری، دانشگاه صنعتی شریف، تهران، ایران

4 پژوهشکده سامانه‌های حمل‌ و نقل فضایی، پژوهشگاه فضایی ایران، تهران، ایران

10.22034/jsst.2021.1223

چکیده

در مرحله طراحی موتورهای پیشران فضایی، استفاده از نرم‌افزارهایی با هزینه‌ی محاسباتی کم، از اهمیت فوق‌العاده‌ای برخوردار است. در این مقاله یک نرم‌افزار مدل‌سازی محفظه رانش موتورهای فضایی دومؤلفه‌ای در مقیاس کوچک توسعه داده می‌شود. با استفاده از مدل‌های پاشش و تبخیر، فرآیندهای تزریق پیشرانه و توزیع تبخیر محاسبه می‌گردد. حلگر احتراقی با استفاده از سینتیک شیمیایی، فرآیند احتراق درون محفظه را به صورت یک‌بعدی در راستای محور محفظه رانش محاسبه می‌کند. حلگر خنک‌کاری، میزان انتقال حرارت از گازهای داغ به فیلم‌های خنک‌کاری و محیط بیرون را پیش‌بینی می‌کند. اعتبارسنجی مدل‌ها نشان می‌دهد که خطای آن‌ها در شبیه‌سازی فرآیندها قابل‌قبول است. با استفاده از ابزار توسعه داده شده، عملکرد تراستر دومؤلفه‌ای شرکت آستریوم با سوخت منومتیل‌هیدرازین و تتراکسید نیتروژن و سینتیک احتراقی گسترده، مورد بررسی قرار گرفته است. نتایج نشان می‌دهد که دمای گازهای درون محفظه یکنواخت نبوده و دارای پیک است. همچنین فرآیند تبخیر قطرات سوخت و اکسنده تا گلوگاه نازل ادامه دارد.

کلیدواژه‌ها

عنوان مقاله [English]

Investigation of a Bi-propellant Thruster by a Developed Space Engine’s Thrust Chamber Analysis Code

نویسندگان [English]

  • Masoud EidiAttarZade 1
  • Atiyeh SarAbadani 2
  • ghazal davarnia 3
  • Hamed Khosrobeygi 2
  • Mohammad Farshchi 1
  • alireza Ramezani 4

1 Aerospace Engineering University, Sharif University of Technology, Tehran, Iran

2 Sharif Technology Services Complex, Sharif University of Technology, Tehran. Iran

3 Sharif Technology Services Complex, Sharif University of Technology, Tehran, Iran

4 Space Transportation Research Institute, Iranian Space Research Center, Tehran,Iran

چکیده [English]

Numerical modeling of space engines aside the experimental test is routine. In the design step of such engines, low-cost softwares are vital. In this paper, small-scale space engine thrust chamber analysis code will be developed. In this code, propellant injection and evaporation distribution will be modelled. 1D Combustion solver calculates the reactions of distributed fuel and oxidizer through the thrust chamber axis by chemical mechanisms. Then the cooling solver computes the heat transfer from hot gases to the film cooling layer and the outer surroundings. Validation shows acceptable errors in the modelling of processes. By this developed code, the performance of the Astrium bi-propellant thruster with MonoMethylHydrazine and NitrogenTetrOxide and distributed chemical reaction has been investigated. Results show that hot gas temperature inside the combustor is not uniform and has a peak. Furthermore, the evaporation of the propellant droplets is continued to the nozzle throat.

کلیدواژه‌ها [English]

  • Analysis Code
  • injection
  • Combustion
  • Bi-propellant Thruster
  • Space Engine
[1] Mason, J. R. and R. D. Southwick, "Large Liquid Rocket Engine Transient Performance Simulation System," Marshall Space Flight Center, Alabama .
[2] Bradford, J., A. Charania and B. S. Germain, "REDTOP-2: Rocket Engine Design Tool Featuring Engine Performance, Weight, Cost, and Reliability," 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Florida, AIAA-2004-3514.
[3] McBRIDE and GORDON, "Computer Program for Calculation of Complex Chemical Equilibrium Compositions, Rocket Performance, Incident and R efleaed Shocks, and Chapman-Jouguet Detonations," NASA SP-273.
[4] Ponomarenko, A., "RPA: Thermal Analysis of Thrust Chambers.," 2012.
[5]Available, [on line]: "http://sierraengineering.com/ ROCCID/roccid.html," [Online].
[6] Davidian, K.J., "Comparison of Two Procedures for Predicting Rocket Engine Nozzle Performance," in 23rd Joint Propulsion Conference, San Diego, CA, U.S.A., AIAA-87-2071.
[7] Manfletti, C., "Start-Up Transient Simulation of a Pressure Fed LOx/LH2 Upper Stage Engine Using the Lumped Parameter-based MOLIERE Code," in 46th Joint Propulsion Conference & Exhibit, Nashville, 2010.
[8] Song, E. and J. Song, "Modeling of Kerosene Combustion Modeling of Kerosene Combustion," Advances in Mechanical Engineering, vol. 9, 2017.
[9] Gray, H.L. "Modelling of Combustion Processes in Small Liquid Bipropellant Thruster," in 28th Joint Propulsion Conference and Exhibit, Nashville, 1992.
[10] Nonnenmacher, S. and M. Piesche, "Design of Hollow Cone Pressure Swirl Nozzles to Atomize Newtonian Fluids," Chemical Engineering Science, vol. 55, no. 19, 2000, pp. 4339-4348.
[11] Rizk, N.K. and A.H. Lefebvre, "Internal Flow Characteristics of Simplex Swirl Atomizers," Journal of Propulsion and Power, vol. 1, no. 3, pp. 193-199, 1985.
[12] Kim, S., T. Khil, D. Kim and Y. Yoon, "Effect of Geometric Parameters on the Liquid Film Thickness and Air Core Formation in a Swirl Injector." Measurement Science and Technology, vol. 20, no. 1, 2008.
[13] Rizk, N. K. and A. H. Lefebvre, "Prediction of Velocity Coefficient and Spray Cone Angle for Simplex Swirl Atomizers," in Proceedings of the 3rd International Conference on Liquid Atomization and Spray Systems, London, 1985.
[14] Moongeun, H., J. Jeon and S.Y. Lee, "Discharge Coefficient of Pressure-Swirl Atomizers with Low Nozzle Opening Coefficients," Journal of Propulsion and Power , vol. 28.1, 2012, pp. 213-218.
[15] Jones, A. R., "Design Optimization of a Large Pressure-Jet Atomizer for Power Plant," in Proc. 2nd ICLASS, Madison, Wis., , 1982.
[16] Gater, R.A. M. R. L'Ecuyer and C. F. Warner, Liquid-Film Cooling It's Physical Nature and Theorical Analysis, Jet Propulsion Center,Purdue university, Indiana, 1965.
[17] G. P. Sutton and Biblarz, O., Rocket Propulsion Elements, 7th ed., New York: John Wiley & Sons, 2001, p. 197–240.
[18] S. Shine, Sunil Kumar, S. and Suresh, B. "A New Generalised Model for Liquid Film Cooling in Rocket Combustion Chambers," International Journal of Heat and Mass Transfer, vol. 55, no. 9, 2012, pp. 5065–5075.
[19] Stechman, R. C., J. Oberstone and J. C. Howell, "Film Cooling Design Criteria for Small Rocket Engines," 4th Propulsion Joint Specialist Conference, Cleveland, AIAA, 1968.
[20] Grisson, W.M., "Liquid Film Cooling in Rocket Engines," United states air force, Atlanta, Georgia, 1991.
[21] Gotzig, U. and E. Dargies, "Development Status of Astriums New 22N Bipropellant Thruster Family," in 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Alabama, 2003.
[22] Preclik, D., D. Estublier and D. Wennerberg, "An Eulerian-Lagrangian Approach to Spray Combustion Modeling for Liquid Bi-Propellant Rocket Motors," in 31 st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibi, San Diego, CA, 1995.
[23] Soltani, M.R., K. Ghorbanian, M. Ashjaee and M. R. Morad, "Spray Characteristics of a Liquid–liquid Coaxial Swirl Atomizer at Different Mass Flow Rates," Aerospace Science and Technology, vol. 9, no. 7, 2005, pp. 592-604.
[24] Lefebvre, A.H. and V. G. McDonell, Atomization and Sprays, Taylor & Francis Group, 2017.
[25] Yang, V., M. Habiballah, J. Hulka and M. Popp, Liquid Rocket Thrust Chambers: Aspects of Modeling, Analysis, and Design, American Institute of Aeronautics and Astronautics, Inc, 2004.
[26] Suess, R.P. and L.B. Weckesser, "Equilibrium, Adiabatic Wall and Stagnation Temperatures at Altitudes up to 100,000 Feet and Mach Numbers up to 20," Defense Documentation Center for Scientific and Technical Information, Viginia, 1966.
[27] Howell, J.C., J. Oberstone and R. C. Stechman, "Design Criteria for Film Cooling for Small Liquid-propellant," Journal of Spacecraft and Rockets, vol. 6, no. 2, 1969, pp. 97-102.
[28] J.D. Anderson, Modern Compressible Flow: with Historical Perspective, Boston: McGraw-Hill, 2003.
[29] Silva Couto, H., P. T. Lacava, D. Bastos-Netto and A. P. Pimenta, "Experimental Evaluation of a Low Pressure-swirl Atomizer Applied Engineering Design Procedure," Journal of Propulsion and Power, vol. 25, no. 2, 2009, pp. 358-364.
[30] N. J. Labbe, Determining Detailed Reaction Kinetics for Nitrogen-and Oxygen-Containing Fuels, PhD Thesis, University of Massachusetts - Amherst, 2013.