تحلیل عددی بالستیک داخلی میکرو تراستر سوخت جامد، جهت استفاده در کاربردهای فضایی

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشکده مهندسی هوافضا ، دانشگاه صنعتی امیرکبیر

2 مدیر گروه هوانوردی،دانشگاه علوم و فنون هوایی شهید ستاری

10.22034/jfnc.2024.444281.1374

چکیده

در مطالعه­ ی حاضر، سعی شده است که بالیستیک داخلی میکرو تراستر سوخت جامد به صورت عددی شبیه­ سازی شود. شبیه سازی انجام شده به وسیله­ ی یک کد شبه یک بعدی که شامل معادلات جرم، انرژی (انتقال حرارت) و حالت است، انجام شده است. نتایج به‌دست آمده با یک کار آزمایشگاهی معتبر اعتبارسنجی شده که انطباق خوبی را نشان می ­دهد. گرین مورد استفاده در میکروتراستر از نوع فینوسیل[1] بوده که در سه حالت 4،8 و بی‌نهایت فین طراحی شده است. زوایای فین­ها به ترتیب 45، 90 و 0 درجه (دایره) است. روابط مذکور، تشکیل یک دستگاه معادلاتی را می­دهند که از آن، مقادیر فشار P‌، دما T و جرم m بدست آمده و به‌وسیله­ ی بدست آوردن این سه پارامتر می­توان مقدار زمان سوزش گرین t‌، نرخ سوزش گرین r0‌، فشار و ماخ در خروجی نازل همگرا-واگرا Pe و Me و در انتها تراست و ایمپالس کل را محاسبه کرد. نتایج بدست آمده نشان می­دهد که استفاده از گرین فینوسیل به‌علت افزایش سطح سوزش و به طبع آن افزایش مناسب فشار محفظه­ ی احتراق گزینه­ ی مناسبی جهت استفاده در میکرو تراسترهای فضایی است. همچنین نتایج نشان می­دهد که در صورت وجود انتقال حرارت، فشار محفظه تقریبا 5/0 بار و ایمپالس کل 15 درصد کاهش می­ یابد.
 
 
[1] Finocyl

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Numerical Analysis Of Internal Ballistic Of Solid Fuel Micro-Thruster For Use In Space Applications

نویسندگان [English]

  • Jalal Zarvandi 1
  • Javad zarvandi 2
1 Aerospace engineering ,amirkabir university of technology
2 Director of Aviation Department, Shahid Sattari University of Aviation Sciences and Technologies
چکیده [English]

In the present study, an attempt was made to numerically simulate the internal ballistics of a solid fuel micro-thruster. The simulation is performed by a one-dimensional code that includes the equations of mass, energy (heat transfer), species and state. The results are validated by one experimental work that show good compliance. The grain used in Micro thruster is of Finocyl type, which is designed in three modes of 4, 8 and infinite fin. The angles of the fins are 90,45, 0 (circle) degrees, respectively. The mentioned equations form a set of equations from which the values of pressure P, temperature T and mass m are obtained and by obtaining these three parameters, the amount of grain's burning time t ,grain's burning rate r0,pressure and mach at the exit of convergent-divergent nozzle Pe and Me can be determined. At the end calculated thrust and total impulse. The results show that the use of Finocyl grain due to the increased level of burning causes the chamber pressure to increase and more thrust to be generated. The results also show that in the presence of heat transfer, the chamber pressure is reduced by approximately 0.5 bar and the total impulse is reduced by 15%.

کلیدواژه‌ها [English]

  • "؛ Micro-thruster"؛ Internal ballistic"؛ Finocyl grain"؛
  • "؛ Solid fuel"
] S. Raimondeau, D.A. Norton, D.G. Vlachos, and R.I. Masel, "Modeling of high temperature micro burners", Proceedings of the Combustion Institute., vol.29, pp. 901-907, 2003.
[2] B. Larangot, V. Conédéra, P. Dubreuil, T. Do Conto, and C.Rossi, "Solid Propellant Micro Thruster: an alternative propulsion device for nano satellite". LAAS-CNRS, France, 2003.
[3] A. Chaalane, R. Chemam, M. Houabes, R. Yahiaoui, A. Metatla, B. Ouari, N. Metatla, D. Mahi, A. Dkhissi,  and D. Esteve1, "A MEMS-based solid propellant micro thruster array for space and military applications", Journal of Physics., Conference Series, 2015.
[4] C. Rossi, B. Larangot, A. Chalaane, V. Conedera, P. Q. Pham, D. Briand, and N. F. De rooij, "Solid propellant thruster for space application," 4th round table on MNT for space., 20-22 May, ESTEC, Noordwijk, Netherlands, 2003.
[5] J. Lee, K. Kim and S.Kwon, "Design fabrication and testing of MEMS solid propellant thruster array chip on glass wafer," Journal of Sensor and Actuators., Vol.157, pp.126-134, 2010.
[6] Xu. Jianbing, Zh. Jiangtao, Li. Fuwei, Li. Shiyi, Ye. Yinghua, and Sh. Ruiqi, "A review on solid propellant micro-thruster array based on MEMS technology," FirePhysChem, 2023.
[7] Q. Shen, W. Yuan, and X. Li, "A fully decoupled design method for MEMS micro thruster based on orthogonal analysis," In Proceedings of the 17th International Conference on Solid-State Sensors, Actuators and Microsystems, Barcelona, Spain, 2013.
[8] Q. Shen, W. Yuan, X. Li, J. Xie, and  H. Chang, "An orthogonal analysis method for decoupling the nozzle geometrical parameters of micro thrusters," Microsyst. Technol., Vol 21, pp.1157–1166, 2014.
[9] Q. Shen, W. Yuan, J. Xie, and H. Chang, "A quantitative optimization model for a horizontal MEMS solid propellant thruster with experimental verification," Microsyst. Technol. Vol 22, pp. 847–859, 2015.
[10] F. Wang, “Structural Design and Propellant performance of a Horizontal Micro-Thruster,” M.Sc. Nanjing University of
Science and Technology., Nanjing, 2018.
[11] C.B. Ru, “Design, Fabrication and Characterization of Solid Propellant Micro propulsion System,” Ph.D. Nanjing University of Science and Technology., Nanjing, 2017.
[12] Nanjing University of Science and Technology. “The world’s first on-orbit ignition test of silicon carbide MEMS  micro thruster array was successful [EB/OL], ” Ministry of Industry and Information Technology of the People’s Republic of  China,[Online].Available:https://www.miit.gov.cn/xwdt/gxdt/bsdw/art/2020/art_4e984438e7474d999e845b1acad10f61. html , 2019-10-29.
[13] W. Xu, “Determinant Ignition and Control Technology of Micro Thruster Array,” M.Sc. Nanjing University of Science
 and Technology, Nanjing, 2019.
[14] L.F. Ma, J. He, and S. Xue, "A micro thrust measurement system with two-wire torsion balance," J. Propuls.Technol. Vol.39,  pp.948–954, 2018.
[15] J. Lee, and T. Kim, "MEMS solid propellant thruster array with micro membrane igniter," Sens. Actuators A Phys. 190, pp.52–60, 2013.
[16] C. Rossi, D. Briand, M. Dumonteuil, TH. Camps, PH. Pham, and  N. De Rooij, "Matrix of 10 × 10 addressed solid propellant micro thrusters: review of the technologies," Sens. Actuators A Phys. 126, pp.241–252 ,2006.
[17] S. Tanaka, K. Kondo, H. Habu, and A.Itoh, "Test of B/Ti multilayer reactive igniters for a micro solid rocket array thruster," Sens. Actuators A Phys. 144, pp. 361–366, 2008.
[18] G.F. Zhang, Z. You, and S. Hu, "MEMS-based propulsion arrays with solid propellant," J. Tsinghua Univ. Sci. Technol. 44, pp.1489–1492, 2004.
[19] X.Z. Yu, “Design, Fabrication and Performance Study of MEMS Solid State Chemical Micro propulsion Array,” M.Sc Nanjing University of Science and Technology, Nanjing, 2012.
[20] K.L. Zhang, S.K. Chou, and S.S. Ang, "MEMS-based solid propellant micro thruster design, simulation, fabrication, and testing," J. Microelectromech. Syst. 13, pp.165–175, 2004.
[21] I. Puchades, M. Hobosyan, L.F. Fuller, F. Liu, S. Thakur, K.S. Martirosyan, and S.E. Lyshevski, "MEMS micro thrusters with nanoenergetic solid propellants," in: Proceedings of the 14th IEEE International Conference on Nanotechnology, IEEE, 2014.
[22] C.B. Ru, F. Wang, J. Xu, J.Dai, Y. Shen, Y. Ye, P. Zhu, and R. Shen, "Superior performance of a MEMS-based solid propellant micro thruster (SPM) array with nano thermites," Microsyst. Technol. 23, pp.3161–3174, 2017.
[23] S. Orieux, C. Rossi, and D. Esteve, "Compact  model based on a lumped parameter approach for the prediction of  solid
propellant micro-thruster performance," Journal of Sensor and Actuators, Vol.101, pp.383-391, 2002.
[24] J. D. Anderson,  Fundamentals of aerodynamics,  New York,McGraw Hill Book Co.,Inc.1991.
[25] I.H. Shames, Mechanics of fluids, New York,McGraw Hill Book Co.,Inc.1962.
[26] V. Giovangigli, "Etude bibliographique des cin´etiques de combustion H2/ O2/ N2/ CO/KOH," RT ONERA 10/6129, 1995.
[27] S.M. Dash, "Rocket Motor Plume Flowfields," Phenomenology and Simulation AGARD LS 188. Rocket Motor Plume Technology, June 1993.
[28] J.R. Roesler, R.A. Yetter, and F.L. Dryer, "Kinetics Interactions of CO, NOx and HCl Emissions in Post combustion Gases," Combustion and Flame, 100, 1995.
[29] D.G. Norton, and D.G. Vlachos, "Combustion characteristics and flame stability at the micro scale: a CFD study of premixed methane/air mixtures," Chem Eng Sci, Vol .58, pp.4871-4882, 2003.
[30] D.L. Baulch, C.J. Cobos, R.A. Cox, C.P. Esser, P. Frank, Th. Just, J.A. Kerr, M.J. Pilling, J.Troe, R.W. Walker, and J. Warnatz, "Evaluated Kinetic Data for Combustion Modeling," J. Phys.Chem. Ref. Data, Vol. 21, No. 3, 1992.
[31] U. Mass, J. Warnatz, "Ignition Processes in Carbon-Monoxide-Hydrogen-Oxygen Mixtures," Twenty-Second Symposium (International) on Combustion, The Combustion Institute, 1988.
[32] R.A. ­Yetter, F.L. Dryer, and H. Rabitz, "A Comprehensive Reaction Mechanism for Carbon Monoxide/Hydrogen/Oxygen. Kinetics Combust," Sci. And Tech., Vol.79, 1991.