نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 استادیار / گروه علوم فضایی، پژوهشکده سامانه های فضانوردی، پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران

2 استادیار / گروه علوم فضایی، پژوهشکده سامانه های فضانوردی، پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناری،تهران، ایران

3 کارشناس پژوهشی / گروه علوم فضایی، پژوهشکده سامانه‌های فضانوردی، پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران

چکیده

در این مقاله، طراحی و جانمایی اجزای مختلف یک رانشگر تک‎مؤلفه‎ای هیدرازینی 10 نیوتنی با تمرکز بر محاسبات طراحی انجام شده است. براین اساس، یک نمونه مهندسی از این رانشگر ساخته خواهد شد. رانشگر مذکور به صورت ماژولار دارای سه بخش اصلی است که عبارتند از: سامانه انژکتور، محفظه تجزیه و نازل. به کمک روش­های تحلیلی، پارامترهای اصلی برای هر یک از این بخش­ها تعیین و برای بخش بعدی مورد استفاده قرار گرفته‎اند. همچنین رفتار و عملکرد کلی سامانه رانشگر به ازای شرایط محیطی و خصوصیات ماده پیشران مورد مطالعه و بررسی قرار گرفته است. ماژول اول، انژکتور، از نوع جریان پیچشی با ورودی‌های مماسی است که مخروط اسپری توخالی با زاویه متوسط، ایجاد می‎نماید. ماژول دوم، محفظه تجزیه حاوی گرانول‎های کاتالیست است که ابعاد آن محفظه بر مبنای معیار حداکثر تجزیه 40% آمونیاک و عدد ماخ محفظه 02/0 انتخاب شده است. ماژول سوم نیز نازل تخلیه است که به صورت مخروطی ساده طراحی شده است. طراحی بدنه بیرونی این سه ماژول، بر اساس ملاحظات جانمایی، محدودیت وزن و دومنظوره بودن (قابل استفاده در آزمون­های سرد و گرم زمینی)، انجام شده است. در نهایت تأیید نتایج طراحی در این مقاله با مقایسه با پارامترهای اصلی طراحی یک نمونه واقعی صورت پذیرفته است.

کلیدواژه‌ها

عنوان مقاله [English]

Physical Configuration Design of a 10N Monopropellant Hydrazine Thruster

نویسندگان [English]

  • Hadiseh Karimaei 1
  • Mohammad Reza Salimi 1
  • Hassan Naseh 2
  • Ehsan Jokari 3

1 Assistant Professor / Department of Space Sciences, Aerospace Systems Research Institute, Aerospace Research Institute.Tehran.IRAN

2 Assistant Professor/ Department of Space Sciences, Aerospace Systems Research Institute, Aerospace Research Institute, Ministry of Science, Research and Technology.Tehran.IRAN

3 Expert Researcher, / Department of Space Sciences, Aerospace Systems Research Institute, Aerospace Research Institute, Ministry of Science, Research and Technology.Tehran.IRAN

چکیده [English]

In this paper, design and physical configuration of various components of a 10N Monopropellant Hydrazine Thruster focusing on design calculations and optimization of catalytic combustion chamber. According to this design, a prototype of the thruster will be manufactured. The mentioned thruster has been designed as a three-piece modular thruster, including an injection system, catalytic combustion chamber and nozzle. Based on analyzes done for each module, the propulsion characteristics of monopropellant thruster system have been identified and used for the next module as necessary inputs. The combustion chamber dimensions are selected based on criterion of maximum decomposition of 40% ammonia and Mach number of 0.02. Also, the third module is the nozzle, designed as a simple cone. The exterior body design of these three modules and their connections to each other, based on considerations of sizing and weight limitation, as well as being dual purpose for use in the cold and hot tests, has been performed.

کلیدواژه‌ها [English]

  • Monopropellant thruster
  • Swirl injector
  • Nozzle
  • decomposition chamber
  • Catalyst
[1]  Yang, A.S., “Satellite Hydrazine Propulsion System Design Trades”, Journal of Da-Yeh University, 10, 2001, pp. 41-50.
[2]  Meibody, M.N.P., Naseh, H. and Ommi, F., Hydrazine Monopropellant Catalyst Bed Optimization Methodology, the 16th International Conference of Iranian Aerospace Society, Tehran, 21-23 Feb 2017.
[3]  Birbara, P.J. and Conn, W.L., Catalyst for Hydrazine Decomposition and the Method of Producing the Catalyst, US Patent 4324819, 1980.
[4]  Soares Netoa, T.G., Cobob, A.J.G. and Cruz, G.M., “Evolution of Morphologic Properties on the Preparation of Ir/Al2O3 Catalysts with High Metallic Contents,” Applied Surface Science, Vol. 240, 2005, pp. 355–365.
[5]  Armstrong,W.E., Ryland, L.B. and Voge, H.H., Catalyst for hydrazine decomposition and method for preparing such catalyst, US Patent 4124538, 1978.
[6]  Bayvel, L. and Orzechovski, Z., Liquid Atomization, Taylor &Francis, 1993.
[7]  Birbara, P.J., Conn and W.L., Catalyst for Hydrazine Decomposition and the Method of Producing the Catalyst, US Patent 4324819, 1980.
[8]  Kim, J.H., Jung, H. and Kim, J.S., “Effects of Characteristic Length Variation for Thrust Chamber on the Hot-fire Performance of Hydrazine Thruster”, Journal of The Korean Society for Aeronautical and Space Sciences, Vol. 42, No. 2, 2014, 144-149.
[9]  Available, [on line]: http://www.space-propulsion.com/ spacecraft-propulsion/hydrazine-thrusters/20n-hydrazine-thruster.html
[10]              Available, [on line]: http://www.moog.com/content/ dam/moog/literature/Space_Defense/Spacecraft/Monopropellant_Thrusters_Rev_0613.pdf
[11]  Meyers, J.M., “Rocket Propulsion-Nozzle Thermodynamics and Isentropic Flow Relations,” Pamphlet in university of Vermont (http://www. academia.edu/29771019/ME_239_ Rocket _Propulsion_ Nozzle_Thermodynamics_ and_ Isentropic_Flow_Relations).
[12]  Kuensberg Sarre, C., Kong, S.C. and Reitz, R.D. Modeling the Effects of Injector Nozzle Geometry on Diesel Sprays, SAE International, SAE paper, 1999
[13]  Buelow, Ph., Mao, E. O. Ch., Smith, S. and Bretz, D., “Two-phase Computational Fluid Dynamics Analysis Applied to Prefilming Pure-Airblast Atomizer,” Journal of Propulsion and Power, 19, 2003, pp. 235-241.
[14]  El-Sayed Negeed, R., Hidaka, S., Kohno, M. and Takata, Y. “Experimental and Analytical Investigation of Liquid Sheet Breakup Characteristics”, International Journal of Heat and Fluid Flow, 32, 2011, pp. 95–106.
[15]  Hosseinalipour, S.M., Karimaei, H. and Ommi, F., “Numerical Study the Effect of Mass flow Rate on Liquid Sheet Properties Resulting from as Wirlinjector”, 3nd Proceeding of Gasturbine, Iran University of Science and Technology, May 2014, Tehran, 13–15 (in Persian).
[16]  Hosseinalipour, S. M. and Karimaei, H., “A New Model Based on Coupling of MEP/CFD/ILIA for Prediction of Primary Atomization”, Canadian Journal of Chemical Engineering, 94, 2016, pp. 792-802.
[17]  Hosseinalipour, S. M. and Karimaei, H., Movahednejad E., Ommi, F., “Application of Maximum Entropy Principle for Estimation of Droplet-Size Distribution Using Internal Flow Analysis of a Swirl Injector”, International Journal of  Spray and Combustion Dynamic, 8, 2016, pp. 205-216.
[18]  Karimaei H., “Design and Simulation of Fuel Injector of a 10N Monopropellant Hydrazine Thruster”, Journal of  Space Science and Technology, 10, 2018, pp. 59-65 (in Persian).
[19]  Mark Ventura, P., Wernimont, E., Heister, S. and Steve Yuan, P., "Rocket Grade Hydrogen Peroxide (RGHP) for use in Propulsion and Power Devices-Historical Discussion of Hazards," 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2007.
[20]  Chiappetta, L., Spadaccini, L., Huang, H., Watkins, W. and Crocker, A., "Modeling a Hydrogen Peroxide Gas Generator for Rockets," 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, vol. 3223, 2000, pp. 17-19.
[21]  Corpening, J., Heister, S.D., Anderson, W. and Austin, B., “Thermal Decomposition of Hydrogen Peroxide, Part 2: Modeling Studies,” Journal of Propulsion and Power, Vol. 22, No. 5, 2006, pp. 996-1005.
[22]  Heister, S., Anderson, W., Corpening, J. and Austin, B., “A Model for Thermal Decomposition of Hydrogen Peroxide," Purdue Univ Lafayette in School of Aeronautics and Astronautics, 2004.
[23]  Pasini, A., Torre, L., Romeo, L. and d’Agostino, L., "Performance Modeling and Analysis of H2O2 Catalytic Pellet Reactors," 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Vol. 5025, 2008, p. 2008.
[24]  Ghassemi, H.M. and Asghari, I., M. N.P., "Experimental Investigation on Specific velocity of Hydrogenperoxid Monopropellant Thruster," 11th Iranian Aerospace Society Conference, Tehran, Iran, March 1-3, 2011.
[25]  V, Shankar and K. Anantha Ram, “Experimental Investigations of the 10 N catalytic Hydrazine Thruster”, Acta Astronautica, 12, 1985, pp. 237-249.
[26]  Ommi., F., “Space Propulsion and Rocket”, Besat Publication, 2009 (in persian).
[27]  Kim, S.K., Jang, Shin, I.J., Shin, H.S.,   Kim, N.R.,Yu, S.H. and Choa, M. J. S. J.  “Macroporous–Mesoporous Alumina Supported Iridium Catalyst for Hydrazine Decomposition”, Catalysis Today, Vol. 185,  , PP. 198-204.
[28] Birbara, P.J. and Conn, W.L., Catalyst for Hydrazine Decomposition and the Method of Producing the Catalyst, US Patent 4324819, 1980.