مدل‌سازی فرآیند قطع در موتور پیشران مایع

شفیعی‌دهج, محمد; ابراهیمی, رضا; کریمی, حسن; جلالی, علیرضا; نادری, مهیار

نویسندگان

دانشکده خواجه نصیرالدین طوسی - دانشکده هوافضا

چکیده

زمان خاموشی موتور و کاهش نیروی رانش یکی از مهمترین مراحل کنترل موشک‌های بالستیک، جدایش بوسترها و حامل‌های فضایی می‌باشد. در این مقاله با توجه به فیزیک مساله و رفتار اجزای موتور، یک مدل ریاضی برای پیش بینی تغییرات فشار محفظه احتراق، کاهش نیروی رانش و تعیین ضربه پس از قطع ایجاد شده است. این مد‌‌ل‌سازی از لحاظ زمانی به چهار بخش تقسیم‌بندی شده است: (1) زمان صدور فرمان قطع تا شروع بسته شدن شیر، (2) مدت زمان عملکرد شیر قطع، (3) بعد از اتمام عملکرد شیر‌های قطع تا تخلیه محفظه از محصولات احتراق و (4) مدت دوفازی شدن و بجوش آمدن مؤلفه‌های پیشران در مسیر‌ خنک‌کاری بعد از شیرهای قطع. نتایح حاکی از آن است که مدت زمان دو بخش اول تاثیر زیادی بر افزایش و یا کاهش میزان نیروی رانش دارد و زمان چهارم کمتر از 10 درصدِ نیروی رانش، سهم دارد، این درحالی است که در این زمان بیشترین نوسانات در نیروی رانش دیده می‌شود

کلیدواژه‌ها

عنوان مقاله [English]

Modeling of Shutdown Process in Liquid Propellant Rocket Engines

نویسندگان [English]

M. Shafiey Dehaj
R. Ebrahimi
H. Karimi
A. Jalali
M. Naderi

چکیده [English]

The effects of liquid propellant rocket engines thrust termination transients are important in achieving the launch vehicle’s desired final velocity with the required precision. In this paper, a mathematical model has been developed to predict the changes in the combustion chamber pressure and the related cut-off impulse based on the physical aspects of engine’s components. The modeling is divided into four steps: (1) from issuing the cut-off command to the activation of valve (2) from the time of executing the stop command until the end of the operation of the cut-off valves, (3)from the time that after the valve is shutt closed until the combustion chamber is extinguished and (4) simulation of the phase change and propellant components evaporation in corrugates. Results suggest that the duration of the first two steps have a significant effect on increasing or decreasing the amount of the thrust force and the 4th step’s thrust is less than 10 percent of nominal value while, the most thrust fluctuations appear in this step.

کلیدواژه‌ها [English]

Liquid propellant rocket engine
Shutdown
Cut
off impulse
Modeling

مراجع

Moshkin, Ye. K. and Prysnyakov, V. F., Liquid Propellant Rocket Engines Dynamics, Mashinostroeniye, Moscow, 1969, (In Russian).

[2] Volodin, V. A., “Construction and Design of Rocket Engines,” Foreign Technology Division Wright-Patterson Air Force Base, Ohio, 1972.

[3] Glikman, B. F., Automatic Control in Liquid Propellant Rocket Engines, Mashinostroeniye, Moscow, 1974, (In Russian).

[4] Glikman, B. F., Unsteady Process in Hydraulic- Pneumatic Systems, Mashinostroeniye, Moscow, 1979, (In Russian).

[5] Prysnyakov, V. F., Dynamics of Liquid Rocket Engines and Propulsion Systems, Mashinostroeniye, Moscow, 1983, (In Russian).

[6] Moshkin, Ye. K. and Prysnyakov, V. F., Liquid Propellant Rocket Engines Systems, Mashinostroeniye, Moscow, 1983, (In Russian).

[7] Moshkin, Ye. K., Prisnyakov, V. F. and Belik, N. P., Dynamics of Liquid Rocket Engines, Mashinostroeniye, Moscow, 1983, (In Russian).

[8] Babkin, A. I., Belov, S. V., Rotovcki, N. B. and Soloviev, E. V., Principles of Automatic Control in Liquid Propellant Rocket Engines, Mashinostroeniye, Moscow, 1986, (In Russian).

[9] Glikman, B. F., Automatic Control in Liquid Propellant Rocket Engines Dynamic Systems, Mashinostroeniye, Moscow, 1987, (In Russian).

[10] Kazlov, A. A., Novikov, B. N. and Soloviev, E. V., Propulsion and Control Systems of Liquid Propellant Rocket Engine, Mashinostroeniye, Moscow, 1998, (In Russian).

[11] Prysnyakov, V. F. and Serebryansky, V. N., “Non-Stationary Heat Behavior of Lliquid Propellant Rocket Engines,” Journal of ActaAstronautica, Vol. 8, No. 8, 1981, pp. 855-866.

[12] Moshkin, Ye. K., Dynamic Processes in Liquid Propellant Rocket Engines, Mashinostroeniye, Moscow, 1964, (In Russian).

[13] Moshkin, Ye. K., Non- Steady Operating Regimes of Liquid Propellant Rocket Engines, Mashinostroyeniye, Moscow, 1970, (In Russian).

[14] Smith, G. W. and Sforzini, R. H., “Pulse Performance Analysis for Small Hypergolic Propellant Rocket Engines,” Marshall Space Flight Center, 1972.

[15] Hongyan, C., “Measuring Methods of Cutoff Impulse for Liquid Propellant Rocket Engine,” Journal of Astronautic Metrology and Measurement Technology, Vol. 6, 1989.

[16] Karimi, H., Nasirharand, A., and Beheshti, M., “Dynamic and Nonlinear Simulation of Liquid Propellant Engines,” Journal of Propulsion and Power, Vol. 19, No. 5, 2003, pp. 938-944.

[17] Karimi, H., and Mohammadi, R., “Modeling and Simulation of a Two Combustion Chambers Liquid Propellant Engine.” Journal of Aircraft Engineering and Aerospace Technology, Vol.79, 2007, pp. 390– 397.

[18] Karimi, H., Mohammadi, R., and Taheri., “Dynamic Simulation and Parametric Study of a Liquid Propellant Engine,” 3^rd International Conference on Recent Advances in Space Technologies(RAST), Istanbul, Turkey, 2007, pp. 219-224.

[19]Yamanishi, N. and et.al,“Transient Analysis of the LE-7A Rocket Engine Using the Rocket Engine Dynamic Simulator (REDS),” 40^th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Fort Lauderdale, Florida, 2004.

[20] Di Matteo, F., “Modeling and Simulation of Liquid Rocket Engine Ignition Transients,” Ph.D Dissertation, Faculty of Engineering, Sapienza University., Roma, Italy, 2011.

[21] Manfletti, C., “Transient Simulation of Liquid Rocket Engine: A Step Towards A More Educated propellant Choice between Kerosene and Methane,” Proceedings of the 2^nd International Conference on Green Propellants for Space Propulsion (ESA SP-557), Chia Laguna (Cagliari), Sardinia, Italy, 2004.

[22] Zucrow, M. J. and Hoffman, J. P., Gas Dynamics, John Wiley& Sons, Vol. 1, New York, 1976.

علوم و فناوری فضایی

مدل‌سازی فرآیند قطع در موتور پیشران مایع

مراجع

مراجع

دوره 6، شماره 4 - شماره پیاپی 17
شماره پیاپی 17
دی 1392
صفحه 1-11

مدل‌سازی فرآیند قطع در موتور پیشران مایع

مراجع

مراجع

دوره 6، شماره 4 - شماره پیاپی 17شماره پیاپی 17دی 1392صفحه 1-11

دوره 6، شماره 4 - شماره پیاپی 17
شماره پیاپی 17
دی 1392
صفحه 1-11