دینامیک و مدل سازی غیر خطی موتور سیکل انبساطی

نوع مقاله: مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 دانشکده مهندسی هوافضا/ دانشگاه صنعتی خواجه نصیر

2 استاد، دانشکده مهندسی هوافضا، دانشگاه صنعتی خواجه نصیرالدین طوسی، تهران

3 دانشگاه صنعتی خواجه نصیرالدین طوسی

4 کارشناس ارشد، دانشکده مهندسی هوافضا، دانشگاه صنعتی خواجه نصیرالدین طوسی، تهران

چکیده

موتورهای انبساطی، موتورهایی هستند که از نظر دینامیکی رفتار بسیار پیچیده و حساسی دارند. در این موتورها برخلاف سایر موتورها، از دبی مولفه سوخت برای به تولید توان مورد نیاز پمپ ها بهره برده می شود. همین امر فرآیند راه اندازی را در این نوع موتورها را بسیار دشوار و پیچیده نموده است. عملکرد شیرآلات کنترلی فرآیند دینامیکی پیچیده ای است و پیش بینی اثر آن با اجرای آزمون های تجربی بسیار پیچیده و هزینه بر خواهد بود از این رو مدل سازی دینامیکی در توسعه این نوع موتورها از اهمیت بالایی برخوردار است و می تواند از بسیاری از هزینه های آتی جلوگیری کند. در این مقاله اقدام به مدل سازی غیر خطی موتور سوخت مایعRL-10 پرداخته می شود. هدف این پژوهش بررسی رفتار دینامیکی موتور انبساطی با استفاده از مدل های ریاضی غیر خطی است. نتایج شبیه سازی نشان داد که مدل غیر خطی ارائه شده برای این موتور از اعتبار کافی برخوردار است.

کلیدواژه‌ها


عنوان مقاله [English]

Dynamic & Non-linear Modelling of an Expansion Cycle Rocket Engine

نویسندگان [English]

  • Mohammad Amin Eskandari 1
  • حسن کریمی 2
  • داود رمش 3
  • Mohammda Reza Alikhani 4
1 Department of Aerospace Engineering, K.N. Toosi University of Technology, Tehran, Iran.
2 P.O.B/Department of Aerospace Engineering, K.N. Toosi University of Technology, Tehran, Iran
3 Khajeh Nasir Toosi University
4 Department of Aerospace Engineering, K.N. Toosi University of Technology, Tehran, Iran
چکیده [English]

Expansion cycle rocket engines have unintelligible and sensitive dynamic behavior. Contrary to other types of rocket engine which have gas generator, Expansion cycle rocket engines utilizes mass flow of fuel propellant to provide power for rotating turbo pump. Which contributes to a complicated and difficult ignitions process in these engines. Priority and delay process in opening of control valves is important to prevent aforementioned phenomena. As opening and closing of control valves cause dynamic process in rocket engine, whose effects are expensive and difficult to predict by experimental tests. Therefore, dynamic modelling plays a key role in development of expansion cycle rocket engines and may decrees future expenses. In this article RL-10 rocket engine with sufficient data for validation has been chosen. The main goal of this article is dynamic modelling of expansion cycle rocket engine using mathematical non-linear models. Modelling results yield that the presented non-linear model is valid.

کلیدواژه‌ها [English]

  • RL-10
  • Dynamic analysis
  • Liquid Rocket Engine
[1] Martin, M. A., Huy, H. Nguyen, D. Greene, W. and C. Seymout, D., "Transient Mathematical Modeling For Liquid Rocket Engine Systems: Methods, Capabilities, and Experience," 5th International Symposium on Liquid Space Propulsion, Chattanooga, TN; United States, Oct 27-30. 2003.

[2]Sutton, George P., and Biblarz. O., Rocket Propulsion Elements, John Wiley & Sons, pp. 223-225, 2016.

[3] Binder, M., Tomsik, T. and P. Veres, J., RL10A-3-3A Rocket Engine Modeling Project, NASA Technical Report, 1997.

[4] Binder, M., "A Transient Model of the RL10A-3-3A Rocket Engine," In 31st Joint Propulsion Conference and Exhibit, p. 2968. 1995.

[5] Binder, M., "An RL10A-3-3A rocket engine model using the Rocket Engine Transient Simulator (ROCETS) Software," 29th Joint Propulsion Conference and Exhibit. 1993.

[6] Rachuk, V. and Titkov, N., "The First Russian LOX-LH2 Expander Cycle LRE: RD0146," Presented at the 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Sacramento, California, 9 - 12 July 2006.

[7] Sekita, R., Yasui, M. and Warashina, S., "The LE-5 Series Development,Approach to Higher Thrust," Higher Reliability and Greater Flexibility, Presented at the 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Alabama, 17-19 July 2000

[8] Durteste, S., "A Transient Model of the VINCI Cryogenic Upper Stag Rocket Engine," Presented at the 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Cincinnati, OH, 8 - 11 July 2007

[9] Leonardi, M., Nasuti, F., Onofri, M., "Basic Analysis of a LOX/Methane Expander Bleed Engine," presented at the 7TH European Conference for Aeronautics and Aerospace Sciences (EUCASS), Milan, Italy, 3 - 6 July 2017

[10] Atsumi, M. and et al., "Development of the LE-X Engine," Mitsubishi Heavy Industries Technical Review, Vol.48, No. 4, 2011, pp. 36-41.

[11] Lozano, T.P.C., "Dynamic Models For Liquid Rocket Engines With Health Monitoring Application," in: Master of Science, Aeronautics and Astronautics, Massachusetts Institute of Technology, 1998

[12] Di Matteo, F.. Modelling and Simulation of Liquid Rocket Engine Ignition Transients, (PhD Thesis), Department of Aerospace Engineering, SAPIENZA University, Roma, 2010..

[13] Di Matteo, F., De Rosa, M. and Onofri, M., "Start-up Transient Simulation of A Liquid Rocket Engine," 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 2011.

[14] Di Matteo, F., De Rosa, M. and Onofri, M., "Transient Simulation of the RL-10A-3-3A Rocket Engine," Space Propulsion Conference. 2012.

[15] Naderi, M., LiangGuozhu,. Static Performance Modeling And Simulation of the Staged Combustion Cycle LPREs. AerospaceScienceandTechnology. 2018.

[16] Santana Jr., A., Barbosa, F.I., Niwa, M. and Goes, L.C.S., "Modeling and Robust Analysis of a Liquid Rocket Engine," 36th Joint Propulsion Conference & ExhibitHuntsville, Alabama, July 2000.

[17] Karimi, H., Nassirharand, A. and Beheshti, M., Dynamic and Nonlinear Simulation of Liquid Propellant Engines, AIAA Journal of Propulsion and Power, vol. 19, no. 5, 2003, pp. 938-944,

[18] Kanmuri, A., Kanda, T., Wakamatsu, Y., Torri, Y. and Kagawa, E. and Hasegawa, K., Transient Analysis of LOX/LH2Rocket Engine (LE-7), 25th Joint Propulsion Conference & ExhibitHuntsville, Monterey, CA, July 10-12, 1989.

[19] Kun, L. and Yulin,Z., Study on Versatile Simulation of Liquid Propellant Rocket Engine Systems Transients, 36th Joint Propulsion Conference & Exhibit Huntsville, Huntsville, AL, July 17-19, 2000.

[20] Ramesh, D. and Aminpoor,M., "Nonlinear, Dynamic Simulation of an Open Cycle Liquid Rocket Engine," 43th Joint Propulsion Conference & Exhibit Huntsville, Cincinnati, OH, July8 - 11 , 2007.

 [21] i Bel, Núria Margarit, and Manuel Martínez Sánchez. Simulation of A Liquid Rocket Engine,1st Meeting of EcosimPro Users, UNED, Madrid, 3-4 May 2001.

[22]Beliaev, E., Chevanov, V., Chervakov, V., "Mathematical Modeling of Operating Process of Liquid Propellant Rocket Engines," MAI, 1999. (In Russian)

[23] Hybrid Systems Analysis Unit and System Dynamics Unit, Engine Balance and Dynamics Model, Rockwell International Corporation, Rocket dyne Division, report number RL00001, January 19.

[24] Avsianikov, B.V., "Theory and Calculation of Feed System’s Elements of Liquid Propellant Rocket Engines," Mashinostroeinye Publications, Moscow, Russia, 1983. (In Russian).