Vol 15, No 2 (2011) > Articles >

Flutter Analysis of RX-420 Balistic Rocket Fin Involving Rigid Body Modes of Rocket Structures

Novi Andria 1


  1. Pusat Teknologi Wahana Dirgantara, Lembaga Penerbangan dan Antariksa Nasional, Bogor 16350, Indonesia



Flutter is a phenomenon that has brought a catastrophic failure to the flight vehicle structure. In this experiment, flutter was analyzed for its symmetric and antisymmetric configuration to understand the effect of rocket rigid modes to the fin flutter characteristic. This research was also expected to find out the safety level of RX-420 structure design. The analysis was performed using half rocket model. Fin structure used in this research was a fin which has semispan 600 mm, thickness 12 mm, chord root 700 mm, chord tip 400 mm, made by Al 6061-T651, double spar configuration with skin thickness of 2 mm. Structural dynamics and flutter stability were analyzed using finite element software implemented on MSC. Nastran. The analysis shows that the antisymmetric flutter mode is more critical than symmetric flutter mode. At sea level altitude, antisymmetric flutter occurs at 6.4 Mach, and symmetric flutter occurs at 10.15 Mach. Compared to maximum speed of RX-420 which is 4.5 Mach at altitude 11 km or equivalent to 2.1 Mach at sea level, it can be concluded that the RX-420 structure design is safe, and flutter will not occur during flight.

Keywords: fin flutter, Nastran, rigid body modes, rocket, RX-420
Published at: Vol 15, No 2 (2011) pages: 107-114

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N. Andria, R.H. Triharjanto, Optimal Design of RX-420 Fin Using Flutter Analysis, Proceedings Regional Conference of Mechanical and Aerospace Technology, FTMD ITB, Bali, Indonesia, 2010, paper list 504.

S.H. Pourtakdoust, N. Assadian, Scientia Iranica 11 (2004) 26.

R. Kamakoti, Ph.D Dissertation, Graduate School of the University of Florida, USA, 2004.

M.W. Keheo, NASA Technical Memorandum 4720, Dryden Flight Research Center, Edwards, California, 1995.

J.J. McNamara, P.P. Friedmann, 48th AIAA/ASME/ASCE/AHS Structures, Structural Dynamics, and Materials Conference, AIAA Series, Honolulu, Hawaii, April 2007, p.2013.

E.H. Dowell (Ed.), A Modern Course in Aeroelasticity, Kluwer Academic Publishers, Netherlands, 1980, p.480.

R.L. Bisplinghoff, H. Ashley, R.L. Halfman, Aeroelasticity, Addison-Wesley Publishing Company, New York, 1957, p.855.

Y.C. Fung, An Introduction to the Theory of Aeroelasticity, Dover Publications, New York, 2008, p.498.

W.P. Rodden, Static Aeroelastic dan Flutter (OnSite Training), University of Kansas, Kansas, 1992.

W.P. William, E.H. Johnshon, MSC/NASTRAN Aeroelastic Analysis User’s Guide (Version 68), The Macneal-Schwendler Corporation, Los Angeles, 1994.

W.P. William, E.H. Johnshon, MSC/NASTRAN Aeroelastic Analysis Seminar Notes (Version 68), The Macneal-Schwendler Corporation, Los Angeles, 1995.

O. Seresta, Ph.D Dissertation, Aerospace Engineering, Faculty of the Virginia Polytechnic Institute and State University, USA, 2007, p.53.

W.A. Silva, U.S. Patent No. 0243448A1, 2 Oct. 2008.

W.T. Thomson (Ed.), Theory of Vibration with Applications, vol. 1, Prentice Hall, New York, 1993, p.546.

J.R. Wright, J.E. Cooper, Introduction to Aircraft Aeroelasticity and Loads, John Wiley and Sons

Ltd., Wiltshire, 2007, p.499.

K. Davidson, D.J. McTavish, D.R. Greatrix, Can. Aeronaut. Space J. 53 (2007) 85.

B.B. Prananta, J.J. Meijer, J.V. Muijden, Static Aeroelastics Simulation Using CFD Comparison with Linear Method, International Forum on Aeroelasticity and Structural Dynamics, Amsterdam, 2003, p.14.

H. Rabia, R. Jarlas, Aeroelastic Investigation of A Missile Configuration, Report FOI-R-0474-SE, FOI-Swedish Defence Research Agency, Division of Aeronautics, FFA, Stockholm, 2002.

G. Yang, S. Obayashi, J. Nakamichi, Aileron Flutter Calculation for A Supersonic FuselageWing Configuration, ICAS Congress, 2002.

J.M. Brandon, S.D. Derry, E.H. Heim, R.M. Hueschen, B.J. Bacon, Ares-I-X Stability and Control Flight Test: Analysis and Plans, AIAA, NASA Langley Research Center, 2008.

L. Fornasier, H. Rieger, U. Tremel, E.V.D. Weide, 40th AIAA Aerospace Science Meeting and Exhibit, Reno, Nevada, 2002, p.0949-Z.

D. Voracek, E. Pendleton, E. Reichenbach, K. Griffin, L. Welch, NASA Technical Memorandum 210741, Dryden Flight Research Center, Edwards, California, 2003.

C.C. Flanigan, Role of Structural Analysis for Space Ship One and the Ansari X-Prize, MSC. Software VPD Conference, Huntington Beach, California, 2006.

M. Fujino, H. Oyama, 44th AIAA/ASME/ASCE/AHS Structures, Structural Dynamics, and Materials Conference, AIAA Series, Norfolk, Virginia, 2003, p.1942.

S. Chae, Ph.D Dissertation, School of Aerospace Engineering, Georgia Institute of Technology, USA, 2004, p.52.