Experimental Analysis of the Influence of Length to Diameter Ratio on Erosive Burning in a Solid Tubular Propellant Grain

Abstract:

Erosive burning usually refers to the increase in the propellant burning rate caused by high velocity combustion gasses flowing over the propellant surface. It may seriously affect the performance of solid-propellant rocket motors [1]. A series of experiments had been made to study the effects of length to the diameter ratio in a single tubular propellant grain on the erosive burning phenomenon. In the same combustion pressure and different grain geometries, the burning pattern of AP¹based propellant were recorded. Furthermore, pressure-time curve for each condition was obtained. The mean velocity gradient is obtained by some thermo-gas-dynamical analysis on experimental data. The results can be used for preliminary design of AP based tubular propellant rocket motors. This method may be used for other types of tubular solid propellants which defer in chemical formulation.

• Periodical: Applied Mechanics and Materials (Volumes 110-116)
• Pages: 3394-3399
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.110-116.3394
• Online since: October 2011
• Authors: Mohammad Reza Zadeh Sheikholeslam, Daryoosh Kazemi, Hooman Amiri
• Keywords: Composite Solid Rocket Motor, Erosive Burning, Length to Diameter Ratio, Port to Throat Area, Saint Robert’s Law, Strand Burner, Wire Break Method

References

[1] N. F. Wang and W. Feng, Theoretical and Experimental Research on the Throat to Port Area Ratio in a Solid Rocket Motor, Propellants, Explosives and Pyrotechnics, Vol. 24, p: 246-248, (1999).

DOI: 10.1002/(sici)1521-4087(199908)24:4<246::aid-prep246>3.0.co;2-2

[2] George P. Sutton and Oscar Biblarz, Rocket Propulsion Elements, 7th edition, John Wiley and sons inc., p: 428-436, (2001).

[3] N. Kubota, Survey of Rocket Propellants and Their Combustion Characteristics, chapter 1 in K. K. Kuo and M. Summerfield (Eds. ), Fundamental of Solid-Propellant Combustion, Progress in Astronautics and Aeronautics, Vol. 90, AIAA, New York, (1984).

DOI: 10.2514/5.9781600865671.0001.0052

[4] M. K. King, A Modification of the Composite Propellant Erosive Burning Model on Lenoir and Robilard, Combustion and Flame, Vol. 24, p: 365-368, (1975).

DOI: 10.1016/0010-2180(75)90169-8

[5] R. J. Burick and J. R. Osborn, Erosive Combustion of Double-base Solid Rocket Propellants, 4th ICRPG Combustion Conference, CPIA pub. 162, vol. II, p: 57-69, Dec. (1967).

[6] M. J. Zucrow, J. R. Osborn and J. M. Murphy, The Erosive Burning of a Nonhomogeneous Solid Propellant, Chemical Engineering Techniques in Aerospace, edited by D. J. Simkin, American Institute of Chemical Engineering, p: 23-29, New York, (1964).

[7] T. Marklund, Propellant Erosion Studies, Research Institute of Nation Defense, Sweden, (1961).

[8] NASA-SP-8039, Solid Rocket Motor Performance Analysis and Prediction, Space Vehicle Design Criteria (Chemical Propulsion), p: 46-47, (1971).

[9] N. Yilmaz, B. Donaldson, W. Gill, W. Erikson, Solid Propellant Burning Rate from Strand Burner Pressure Measurement, Propellants, Explosives and Pyrotechnics, Vol. 33, No. 2, p: 109-117, (2008).

DOI: 10.1002/prep.200800216

[10] P. Hill and C. Peterson, Mechanics and Thermodynamics of Propulsion, 2nd edition, Pearson Education, (2009).