طراحی و تحلیل عملکرد میکروموتور سوخت مایع دو پیشرانه‌ی اکسیژن مایع-کراسین

نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 گروه مهندسی هوافضا، دانشکده مهندسی مکانیک، دانشگاه تربیت مدرس، تهران، ایران.

2 عضو هیئت علمی پژوهشکده علوم و فناوری هوایی، پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران

چکیده

در میکروموتورهای سوخت مایع دو پیشرانه از ترکیبات سوخت متعددی می­توان استفاده کرد که در این پژوهش از ترکیب احیاکننده کراسین و اکسنده­ی سرمازای اکسیژن مایع استفاده شده است. هدف، تحلیل عملکرد یک میکروموتور با تراست پایین به منظور امکان­سنجی اولیه­ی استفاده از آن به عنوان پیشرانش کمکی در ماموریت­های فضایی است. به همین منظور ابتدا یک میکروموتور طراحی شده و تحلیل احتراق، انتقال حرارت، جریان خروجی نازل و مقدار پارامترهای عملکردی در آن با استفاده از نرم­افزار RPA انجام می­شود. میکروموتورها همانند موتورهای بزرگ اجزایی چون انژکتور، صفحه انژکتور، محفظه احتراق و نازل دارند و طراحی تمام این اجزا با ذکر معادلات حاکم شرح داده می­شوند. با ساخت نمونه طراحی شده و انجام تست گرم، می­توان عملکرد میکروموتور طراحی شده را به شکل دقیق مشاهده کرد و در انتها پارامترهای عملکردی محاسبه شده از نرم­افزار با نتایج حاصل شده از تست گرم با هم مقایسه می­شوند.

کلیدواژه‌ها


عنوان مقاله [English]

Performance Analysis of Liquid Propellant Micro-propulsion with Liquid Oxygen as Cryogenic Oxidizer

نویسندگان [English]

  • Amirhossein Edalatpour 1
  • Fatholah Ommi 1
  • Zoheir Saboohi 2
1 Department of Aerospace Engineering, Faculty of Mechanical Engineering, Tarbiat Modares University, Tehran,IRAN
2 Faculty member of Aerospace Research Institute, Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran
چکیده [English]

Micro-propulsion Systems are low thrust engines that be used in space missions like keeping satellite in orbit and changing orbit. These engines have several kinds and liquid propellant micro-propulsion is used in this project. In two propellant micro-propulsion systems, various fuels and oxidizers can be used. Kerosene is used as fuel and liquid oxygen is used as oxidizer in this project. First of all, a micro-propulsion is designed and analysis of combustion, heat transfer, nozzle exit flow and amount of performance’s parameters is done with RPA software. Similar to big engines, micro-propulsion systems have injectors, injection plate, combustion chamber and nozzle. Design of all of this parts will be explained. With manufacturing of designed model and perform hot fire test, accurate performance of engine is observed. Finally, performance’s parameters in hot fire test are compared with performance’s parameters in RPA.

کلیدواژه‌ها [English]

  • micro-propulsion
  • cryogenic oxidizer
  • Injector
  • Combustion chamber
  • Nozzle
  • heat transfer
  • hot fire test
[1] Ommi, F., Design Principle of Space Rocket Propulsion & Engines, Tehran: Hooshmand Tadbir, 2015. (in persian)
[2] Scott, E.H., Bloome, H.E. and Mansour, A.H., M1 Engine Subscale Injector Tests by NASA, NASA Technical Note, 1967.
[3] Burick, R.J., Space Storable Propellent Performance Program Coaxial Injector Characterization, NASA-CR-120936, 1972.
[4] Micci, M.M., Thomas, J.L., Glogowski, M., “Shear Coaxial Injector Spray Combustion Experiments”, 32nd JANNAF Combustion Meeting, Huntsville, Alabama, October 23-27, 1995.
[5] Nosratollahi,M. and Adami Dehkordi, A.H., “Comprehensive Pattern of Design Low-thrust Thrusters”, Journal of Space Science and Technology (JSST), Vol.3, No.3 and 4, Fall-Winter 2010-2011, p.20 (In Persian).
[6] Fazeli, H., Naseh, H., Mirshams, M. and Basohbat, A., “Comprehensive Pattern of Design Low-thrust Thrusters”, Journal of Space Science and Technology (JSST), Vol.7, No.3, Fall 2014, p.9 (In Persian).
[7] Mehrabi, A., Design and Manufacturing of Subscale Engine with Single Double Base Injector and its Combustion Model Investigation, (Thesis MSc), Department of Mechanical Engineering, Tarbiat Modares University, Tehran, 2012. (in persian)
[8] Mehrabi, A., Ommi, F., Valizadeh, S. and Movahednejad, E.,“Design, Manufacturing, Cold and Hot-Fire Test of a Liquid Subscale Engine with Single Swirl Double Base Injector”, AmirKabir Journal of Science & Research Mechanical Engineering, Vol.48, No.1, pp.25-28, 2016. (in persian)
[9] Space Micropropulsion Laboratory, Tarbiat Modares University, Tehran, Iran, 2017.
[10] Liquid Rocket Propulsion, Accessed 18 March 2017; http://dare.tudelft.nl/projects-and-teams/liquid-rocket-propulsion/
[11] Ojeda, C.E., Persaud, T. and Prescott, K., “Production and Manufacture of Low-Cost Liquid Rocket Engines for Sounding Rockets”, 53rd AIAA/SAE/ASEE Joint Propulsion Conference, Atalanta, 2017.
[12] Huzel, D.K., Modern Engineering for Design of Liquid-Propellant Rocket Engines, Chapter 4, AIAA, 1992.
[13] Sutton, G.P. and Biblarz, O., Rocket Propulsion Elements, Seventh Edition, Chapter 19, Seventh Edition, Wiley, 2001.
[14] Raju, B.P. and  Mastaniah.T., “Design of liquid oxygen Storage Tank with Welded Joints & its Safety”, International Journal of Modern Engineering Research (IJMER), Vol 5, 2015.
[15] Liquid Oxygene, Accessed 28 Februrary 2017, www.airproducts.com/~/media/files/pdf/company/safetygram-6.pdf
[16] Sforza, P.M., Theory of Aerospace Propulsion, Chapter 11, Elsevier, 2017.
[17] Turner, M.J., Rocket and Spacecraft Propulsion: Principles, Practice and New Developments, Third Edition, Chapter 6, Springer,2009.
[18] Hill, P.G. and Peterson, C.R., Mechanics and Thermodynamics of Propulsion, Second Edition, Chapter 14, Addison-Wesley Publishing Company, 1992.
[19] Advancing Next-Generation Rockets and the Engines that Power Them, Accessed 24 March 2017, https://str.llnl.gov/november-2015/burton,
[20] Ponomarenko, A., Tool for Rocket Propulsion Analysis, Accessed 25 May 2017, https://www.slideshare.net/ AlexanderPonomarenko/rpa-tool-for
[21] Marchi, C.H., “Numercial Solutions of Flows in Rocket Engines with regenerative Cooling”, Numercial Heat Transfer Journal, Vol.45, pp.64-81, 2010.
[22] Ulas, A., “Numerical Analysis of Regenerative Cooling in Liquid Propellant Rocket Engines”, Aerospace Science and Technology Journal, Elsevier, Vol.24, 2013, pp.187-197.
[23] Negishi, H., Kumakawa, A., Yamanishi, N. and Kurosu, A., “Heat Transfer Simulations in Liquid Rocket Engine Subscale Thrust Chambers”, 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Hartford, 2008.
[24] Song, W., Son, M. and Shin, D., “Ignition Transition of GOx/Kerosene Spray Combustion with Nitrogen Film Cooling”, 53rd AIAA/SAE/ASEE Joint Propulsion Conference, Atlanta, 2017.
[25] Rocket Propulsion Analysis, Software Package, Ver. 2.3, RP Software+Engineering, Cologne/Bonn Area, Germany, 2017.