Influence of Port Geometry on Thrust Transient of Solid Propellant Rockets at Liftoff
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Influence of Port Geometry on Thrust Transient of Solid Propellant Rockets at Liftoff

Authors: Karuppasamy Pandian. M, Krishna Raj. K, Sabarinath. K, Sandeep. G, Sanal Kumar. V.R.

Abstract:

Numerical studies have been carried out using a two dimensional code to examine the influence of pressure / thrust transient of solid propellant rockets at liftoff. This code solves unsteady Reynolds-averaged thin-layer Navier–Stokes equations by an implicit LU-factorization time-integration method. The results from the parametric study indicate that when the port is narrow there is a possibility of increase in pressure / thrust-rise rate due to relatively high flame spread rate. Parametric studies further reveal that flame spread rate can be altered by altering the propellant properties, igniter jet characteristics and nozzle closure burst pressure without altering the grain configuration and/or the mission demanding thrust transient. We observed that when the igniter turbulent intensity is relatively low the vehicle could liftoff early due to the early flow choking of the rocket nozzle. We concluded that the high pressurization-rate has structural implications at liftoff in addition to transient burning effect. Therefore prudent selection of the port geometry and the igniter, for meeting the mission requirements, within the given envelop are meaningful objectives for any designer for the smooth liftoff of solid propellant rockets.

Keywords: Igniter Characteristics, Solid Propellant Rocket, SRM Liftoff, Starting Thrust Transient.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1080778

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References:


[1] V.R. Sanal Kumar, B.N. Raghunandan, T. Kawakami, H.D. Kim, T. Setoguchi, and S. Raghunathan, " Boundary-Layer Effects on Internal Flow Choking in Dual-Thrust Solid Rocket Motors," AIAA Journal of Propulsion and Power, Vol.24, No.2, March-April 2008.
[2] V.R. Sanal Kumar, and B.N. Raghunandan, "Ignition Transient of Dualthrust Motors - A Review," 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Atlanta, Georgia, USA, 28 July - 1 August 2012, Paper No. AIAA 2012-4043.
[3] V.R. Sanal Kumar, "Thermoviscoelastic Characterization of a Composite Solid Propellant Using Tubular Test," Journal of Propulsion and Power, Vol. 19, No. 3, pp. 397-404, 2003.
[4] H. Ikawa, and F.S. Laspesa, "Ignition/Duct Overpressure Induced by Space Shuttle Solid Rocket Motor Ignition," Journal of Spacecraft and Rockets, Vol. 22, No. 4, pp. 481, 1985.
[5] G.D. Luke, M.A. Eager, and H.A. Dwyer, "Ignition Transient Model for Large Aspect Ratio Solid Rocket Motors," AIAA Paper 96-3273, 1996.
[6] S. Alestra, I. Terrasse, and B. Troclet, "Identification of Acoustic Sources at Launch Vehicle Lift-Off Using an Inverse Method," AIAA Paper 2002-926, 2002.
[7] M. Salita, M., "Modern SRM Ignition Transient Modeling (Part 1): Introduction and Physical Models," AIAA Paper 2001-3443, 2001.
[8] V.R. Sanal Kumar, B.N. Raghunandan, H.D. Kim, A. Sameen, T. Setoguchi, and S. Raghunathan, "Starting Transient Flow Phenomena in Inert Simulators of SRM swith Divergent Ports," Journal of Propulsion and Power, Vol. 22, No. 5, pp. 1138-1141, 2006.
[9] V.R. Sanal Kumar, B.N. Raghunandan, H.D. Kim, A. Sameen, T. Setoguchi, and S. Raghunathan "Studies on Internal Flow Choking in Dual-Thrust Motors," Journal of Spacecraft and Rockets, Vol. 43, No. 5, pp. 1140-1143, Sept.-Oct. 2006.
[10] B.N. Raghunandan, V.R. Sanal Kumar, C. Unnikrishnan, and C. Sanjeev, "Flame Spread with Sudden Expansions of Ports of Solid Rockets," Journal of Propulsion and Power, Vol. 17, No. 1, pp. 73-78, 2001.
[11] B.N. Raghunandan, N.S. Madhavan, C. Sanjeev, and V.R. Sanal Kumar, "Studies on Flame Spread with Sudden Expansions of Ports of Solid Propellant Rockets Under Elevated Pressure," Defence Science Journal, Vol. 46, No. 5, pp. 417-423, Nov. 1996.
[12] A. Peretz, K.K. Kuo, L.H. Caveny, and M. Summerfield, "Starting Transient of Solid Propellant Rocket Motors with High Internal Gas Velocities," AIAA Journal, Vol. 11, No. 12, 1973, pp. 1719-1729.
[13] D.L. Baker, "Method of predicting chamber pressure transients during the ignition of solid propellant rocket motors," United Technology Center, Sunnyvale, California, UTC TM - 14 - 62 - UZ, March 1962.
[14] L.H.Caveny, and K.K.Kuo, and B.W. Shackelford, "Thrust and ignition transient of the space shuttle solid rocket motor," Journal of Spacecraft and Rockets, Vol.17., Nov-Dec. 1980, pp 489-494.
[15] D.R. Manson, S.K. Folkman, and M.A. Behring, "Thrust Oscillations of the Space Shuttle Solid Rocket Booster Motor During Static Tests," AIAA Paper 79-1138, 1979.
[16] Lemic, Dragan_" Flame spreading over solid rocket propellants during ignition transient", Sci.- Tech. Rev., 52 (3), 33-39, 2002.
[17] N. Lukin, Alexander,"Numerical modeling and method of prevention of the anomalous combustion regimes development in the high-loading density solid propellant rocket motor", Proc. Int. Pyrotech. Semin, 28th, 513-528, 2001.
[18] Cho, In Hyun; Baek, Seung Wook "Numerical analysis of ignition transient in an axisymmetric solid rocket motor equipped with rear ignition system", Combust. Sci. Technol, 152,81-98, 2000.
[19] C. Aswin, S. Srichand Vishnu, D. Aravind Kumar, S. Deepthi, S.K. Kumaresh, M. Arun, and V.R. Sanal Kumar, "Studies on Ignition Delay and Flame Spread in High-performance Solid Rocket Motors," Applied Mechanics and Materials, vol. 232, pp 316-321, 2012.
[20] Report of the Presidential Commission on the Space Shuttle Challenger Accident, June 1986. http://science.ksc.nasa.gov/shuttle/missions/51- l/docs/rogers-commission/table-of-contents.html
[21] T.F. Zien, "Integral Solution of Ablation Problems with Time- Dependent Heat Flux," AIAA Journal, vol. 16,No. 12, 1978, pp. 1287- 1295.