Determining combustion zone acoustic admittance of non-metal and metalized energy condensed systems

Fluid, gas and plasma mechanics


Kuroedov A. A.*, Borisov D. M.**, Semyonov P. A.***

Keldysh Research Centre, 8, Onezhskaya str., Moscow, 125438, Russia

***e-mail: mezhvsel_pavlo@mail.r


The work is devoted to the experimental study of combustion zone dynamic characteristics for metallized and non-metallized solid propellants. The goal of the study consists in developing a device to determine acoustic admittance and the pressure-response function of solid propellant combustion zone at various pressure pulsation frequencies and operation pressure.

The pulsed T-burner consisting of a classical T-burner and two auxiliary pressure pulsation generation (AG) chambers is proposed. Changing the T-chamber sections number allows varying frequency of created longitudinal vibrations combustion products, making it possible to measure acoustic admittance of the combustion zone in a wide frequency range. Nozzle design envisages the possibility of changing the throat diameter before launching by replacing the molybdenum liner. A pyrotechnic compound placed in the AG free space ensures the tearing up of metal diaphragm, clamped in the channel, connecting AG and T-burner.

To determine the solid propellant acoustic admittance a series of firings is being performed. For each firing cylindrical charges with a channel are prepared and glued to T-chamber cover. During the T-chamber firing without AG the installation, the operation time necessary for the right setting of time delay of triggering pyrotechnic compositions in AGs for the next firings is determined. Further firings are performed with AG, in which the decay constants of the two pressure pulses, created at the main operation segment, and at the end after both charges burning out are being fixed. Acoustic admittance of the solid propellant combustion zone and a function of combustion zone pressure-coupled response are calculated according to the obtained coefficients.

The acoustic admittances of a non-metallized solid propellant (AP / low-molecular rubber) and metallized propellant (AP / butyl-rubber /Al) were measured at frequencies in the range 150 to 850 Hz. Comparison of the obtained results to the published data indicates the perspective of the proposed installation implementation. A significant relative error of acoustic admittancehav and pressure-coupled response function determination requires more close attention to the technique of pulse pressure forming in the T-chamber.

The obtained acoustic admittance values can be used as boundary condition for solid fuel power plants acoustic stability calculation while employing various numeric methods.


acoustic instability, T-burner, decay constant, solid propellant, acoustic admittance


  1. Horton M.D. Use of the one-dimensional T-burner to study oscillatory combustion, AIAA Journal, 1964, vol. 2, no. 6, pp. 1112 – 1118.

  2. Coates R.L., Horton M.D., Ryan N.W. T-Burner Method of Determining the Acoustic Admittance of Burning Propellants, AIAA Journal, 1964, vol. 2, no. 6, pp. 1119 – 1122.

  3. Culick F.E.C., Perry E.H. T-burner data and combustion instability in solid propellant rockets, AIAA Journal, 1969, vol. 7, no. 6, pp. 1204 – 1205.

  4. Perry E.H. Investigations of the T-burner and its role in combustion instability problem: Ph. dis., Pasadena, California, 1970, 145 p.

  5. Lovine R.L. High frequency propellant response measurements, AIAA Paper 1977-976, 13th Joint Propulsion Conference, 1977, pp. 1 – 9.

  6. Lin A., Wang S. Investigation of aluminized solid propellant combustion instability by means of a T-burner, AIAA Paper 95-0606, 1995, pp. 1 – 8.

  7. Foner S.N., Hudson R.L., Nall B.H. Admittance measurements of solid propellants by an acoustic oscillator technique, AIAA Journal, 1964, vol. 2, no. 6, pp. 1123 – 1129.

  8. Oberg, C.L., Ryan N.W., Bear A.D. A pulsed t-burner technique, AIAA Journal, 1968, vol. 6, no. 5, pp. 920 – 921.

  9. Culick F.E.C. T-burner testing of metalized solid propellants: report, California, Institute of Technology, AFRPL-TR-74-28, 1974, 274 p.

  10. Price E.W., Mathes H.B., Madden O.H. Pulsed T-burner testing of combustion dynamics of aluminized solid propellants, AIAA Paper 71-634, 1974, pp. 1 – 9.

  11. Su W., Wang N., Li J., Zhao Y., Yan M. Improved method of measuring pressure coupled response for composite solid propellants, Journal of Sound and Vibration, 2013, vol. 333, issue 8, pp. 2226 – 2240.

  12. Song A., Li J., Yan M., Sun B., Wang N. Propagation of pressure wave in a pulsed T-burner, AIAA Paper 2017-4951, 2017, pp. 1 – 10.

  13. Arkhipov V.A., Volkov S.A., Revyagin L.N. Fizika goreniya i vzryva, 2011, vol. 47, no. 2, pp. 74 – 80.

  14. Leibovitz Z., Gany A. Investigation of solid propellant combustion instability by means of a T-burner, Acta Astronautica, 1984, vol. 11, no. 9, pp. 603 – 606.

  15. Beckstead M.W., Culick F.E.C. Investigations of novel energetic materials to stabilize rocket motors: final report, California Institute of Technology, N00014-95-1-1338, 2000, 275 p.

  16. Beckstead M.W., Meredith K.V., Blomshield F.S. Examples of unsteady combustion in non-metalized propellants, AIAA Papers 2000-3696, 2000, pp. 1 – 18.

  17. Flandro G.A., Majdalani J. Aeroacoustic instability in rockets, AIAA Journal, 2003, vol. 41, no. 2, pp. 485 – 497.

  18. Radenac E., Fluctuating energy balance method for postprocessing multiphase flow computations, Journal of Propulsion and Power, 2013, vol. 29, no. 3, pp. 699 – 708.

  19. Culick F.E.C. Acoustic oscillations in solid propellant rocket chambers, Acta Astronautica, 1966, vol. 12, no. 2, pp. 113 – 126.

  20. Kuroedov A.A., Borisov D.M. Trudy MAI, 2017, no. 94, available at:

  21. Kuroedov A.A., Laptev I.V., Borisov D.M. Trudy MAI, 2016, no. 90, available at:

  22. Kashina I.A., Sal’nikov A.F. Trudy MAI, 2013, no. 65, available at:

Download — informational site MAI

Copyright © 2000-2022 by MAI