Modelling and Verification of Solid Propellant Rocket Motor Operation

• Autorzy: Zygmunt B. , Surma Z. , Leciejewski Z. , Motyl K. , Rasztabiga T.

Identyfikatory

DOI

10.22211/cejem/67434

• Języki publikacji: EN

Abstrakty

EN

This paper presents a mathematical-physical model of phenomena occurring in the combustion chamber of a new solid propellant rocket motor. Due to the fact that the geometrical shape of the propellant grain has already been elaborated, the proposal for the modelling of combustion gas generation is a novelty. To solve the system of equations associated with the mathematical model, a computer programme in Turbo Pascal 7.0 was developed. For the solution of ordinary first-order differential equations, the fourth-order Runge-Kutta numerical method was applied. The main results of the completed simulations, i.e. changes in gas pressure, p, in the combustion chamber, and the rocket motor thrust, R, as a function of time, t, of motor operation, are shown graphically. Experimental verification of the parameters of the designed motor shows good agreement with the numerically calculated parameters.

Słowa kluczowe

EN

modelling of rocket motor operation; ballistic parameters; experimental verification

• Wydawca: Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
• Czasopismo: Central European Journal of Energetic Materials
• Rocznik: 2016
• Tom: Vol. 13, no. 4
• Strony: 944--956
• Opis fizyczny: Bibliogr. 14 poz., rys., tab.

Twórcy

autor

Zygmunt B.

• Military University of Technology, Faculty of Mechatronics and Aerospace, Kaliskiego 2, 00-908 Warsaw, Poland

autor

Surma Z.

• Military University of Technology, Faculty of Mechatronics and Aerospace, Kaliskiego 2, 00-908 Warsaw, Poland

autor

Leciejewski Z.

• Military University of Technology, Faculty of Mechatronics and Aerospace, Kaliskiego 2, 00-908 Warsaw, Poland

autor

Motyl K.

• Military University of Technology, Faculty of Mechatronics and Aerospace, Kaliskiego 2, 00-908 Warsaw, Poland

autor

Rasztabiga T.

• Military University of Technology, Faculty of Mechatronics and Aerospace, Kaliskiego 2, 00-908 Warsaw, Poland

Bibliografia

• [1] PRODAS, Arrow Tech Associates, Inc. USA, 2008.
• [2] Coats D.E., Dunn S.S., French J.C., Performance Modelling Requirements for Solid Propellant Rocket Motors, Chemical Propulsion Information Agency, 2003.
• [3] Coats D.E., French J.C., Dunn S.S., Berker D.R., Improvements to the Solid Performance Program (SPP), 39thAIAA/ASME/SAE/ASEE Joint Propulsion Conference, Huntsville, AL, 2003.
• [4] Coats D.E., Levine J.N., Cohen N.S., Nickerson G.R., Tyson T.J., A Computer Program for the Prediction of Solid Propellant Rocket Motor Performance, Vol. 1, Air Force Rocket Propulsion Laboratory, 1975.
• [5] Scippa S., Propellant Grain Design, in: Design Methods in Solid Rocket Motors, AGARD-LS-150 (Revised), Paris, 1988.
• [6] Alvilli P., Buckmaster J., Jackson T.L., Short M., Ignition-transient Modelling for Solid Propellant Rocket Motors, 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, AL, 2000.
• [7] Alvilli P., Tafti D., Najjar F., The Development of an Advanced Solid Rocket Flow Simulation, Program ROCFLO, 38th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, 2000.
• [8] Willcox M.A., Brewster M.Q., Tang K.C., Stewart D.S., Kuznetsov I., Solid Rocket Motor Internal Ballistics Simulation using Three-dimensional Grain Burnback, J. Propul. Power, 2007, 23, 3.
• [9] Terzic J., Zecevic B., Baskarad M., Catovic A., Serdarevic-Kadic S., Prediction of Internal Ballistic Parameters of Solid Propellant Rocket Motors, Problems of Mechatronics. Armament, Aviation, Safety Engineering, 2011, 2(4), 7-26.
• [10] Zygmunt B., Motyl K., Machowski B., Makowski M., Olejniczak E., Rasztabiga T., Theoretical and Experimental Research of Supersonic Missile Ballistics, Bull. PAS − Technical Science, 2015, 63(1), 229-233.
• [11] Rasztabiga T., Motyl K., Zygmunt B., Kaźmierczak R., The Concept of a Two-stage Supersonic Missile Design (in Polish), Problems of Mechatronics. Armament, Aviation, Safety Engineering, 2014, 5(3), 51-68.
• [12] Torecki S., Rocket Engines (in Polish), MKL, Warszawa, 1984.
• [13] Razdan K.M., Kuo K.K., Erosive Burning of Solid Propellants, Fundamentals of Solid Propellant Combustion, (Kuo K.K., Summerfield M., Eds.), Progress in Astronautics and Aeronautics, vol. 90, AIAA, 1984.
• [14] Drabik Z., Rasztabiga T., Rocket Motor with Composite Combustion Chamber (in Polish), Problems of Mechatronics. Armament, Aviation, Safety Engineering, 2015, 6(3), 71-83.

Uwagi

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017).