Abstract
The aerodynamic characteristics of nine configurations of supersonic continuous deflectable nose guided missiles have been investigated. The optimized geometry was achieved based on the accuracy of confliction with constant target in ground to ground mission. The studied configurations consist of a spherical nose tip, a tangent ogive, one set of stabilizing tail fines and a cylindrical body whose midsection is flexible to form an arc of a circle. So the cylindrical body consists of a fixed part in the vicinity of the nose, middle flexible part and main body with stabilizers. The effects of fixed length (Fix = 0, 1.5, 3Cal) and flexible length (Flex = 1, 2.5, 5Cal) parameters on the aerodynamics and flight dynamics of guided missile have been studied. A code has been developed to solve full Navier-Stokes equations using finite volume and Runge-Kutta time stepping techniques and modified Baldwin-Lomax turbulence model. Multi-block technique was also used to solve the main body and fin parts flow fields. Further, a 3 degree of freedom code along with a pure pursuit guidance subroutine was developed to compare planar flight dynamics of missiles. It was found that although the missiles with bigger lengths for fixed and flex parts show more maneuverability, but this is not favorable for all missile missions as sometimes it decreases the confliction accuracy. Flight dynamic analysis shows that a change in initial launch angle may shift the favorite configuration. This means only the aerodynamic defined aim functions cannot completely supersede flight dynamic analysis in geometric optimization. Further, the thrust vector moment is an important portion of total control moment as it enhances the hitting accuracy and also decreases the importance of geometry.
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Abbas Khalghani received the B.S. from the Ferdowsi University of Mashhad, Iran, in 1988 and his M.S. in Mechanical Engineering from University of Tehran, Iran, in 2000. He is currently a Ph.D. student at Ferdowsi University of Mashhad. His research interests include experimental aerodynamics, CFD and flight dynamics.
Mahmoud Pasandideh Fard is an Associate Professor of Mechanical and Aerospace Eng. at Ferdowsi University of Mashhad. He received his B.Sc. and M.Sc. in Mechanical engineering from Ferdowsi university of Mashhad, Iran, in 1985 and 1988. He received his Ph.D. in Aerospace Engineering in 1998 from Sydney University of Australia. He currently teaches and researches at the university. His research interests are include computational low and high speed aerodynamics, boundary layer flows, hydrodynamics, cavitation and super-cavitation, turbulence modeling and supersonic projectiles.
Mohammad Hassan DJavareshkian received his Ph.D. from Imperial College, University of London in 2006, in field of CFD. Since 2008 he has taught in the Department of Mechanical Engineering, Ferdowsi University of Mashhad Research areas of interest are CFD, gas dynamics, oscillatory flows and aerodynamics.
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Khalghani, A., Pasandideh-Fard, M. & Djavareshkian, M.H. Aerodynamic shape study of supersonic surface to surface missiles with continuous flexible nose. J Mech Sci Technol 30, 3183–3192 (2016). https://doi.org/10.1007/s12206-016-0512-z
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DOI: https://doi.org/10.1007/s12206-016-0512-z