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UID:0-347@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20181231T163000

DTEND;TZID=Asia/Jerusalem:20181231T173000

DTSTAMP:20230527T135047Z

URL:https://aerospace.technion.ac.il/events/nonlinear-aerodynamic-effects-
 on-static-aeroelasticity-of-flexible-missiles/

SUMMARY:Nonlinear Aerodynamic Effects on Static Aeroelasticity of Flexible 
 Missiles
DESCRIPTION:Lecturer:Dmitry Tihomirov\n Faculty:Department of Aerospace Eng
 ineering\n Institute:Technion – Israel Institute of Technology\n Locatio
 n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr
 act: \n Details: \n The general trend in missile development is towards lo
 nger\, faster\, high-maneuverability missiles. This makes missiles increas
 ingly more flexible and therefore more susceptible to aeroelastic effects\
 , such as static and dynamic aeroelastic instability\, and stability probl
 ems due to thrust misalignment. While most past problems of missile aeroel
 asticity were of control surfaces flutter\, modern missile configurations 
 experience static aeroelastic phenomena\, which are not addressed much in 
 the literature. The current study focuses on nonlinear aerodynamic effects
  on the flight of elastic missiles and examines these effects for a range 
 of angle of attack and Mach number values. The investigation is based on s
 tatic aeroelastic analyses of flexible missile configurations that are per
 formed using linear and nonlinear aerodynamic models.  The nonlinear aero
 elastic solution is based on the solution of the Navier-Stokes equations o
 n the elastically deformed missile in a Computational Fluid Dynamics (CFD)
  code. It serves to study the load distribution over the missile\, the res
 ulting deformed shape of the missile\, and the integral aerodynamic coeffi
 cients compared to those computed with linear aerodynamics.\nThe study pro
 poses a computationally efficient approach for the aeroelastic analysis of
  flexible missiles via a Nonlinear Strip Model (NSM). In the NSM\, the non
 linear aerodynamic force coefficients in each strip (segment) over the mis
 sile's body are computed for the rigid configuration. A database of coeffi
 cients\, computed for various Mach numbers and angle of attack values\, is
  used together with the structural modal model to provide the aeroelastic 
 solution.\nThe test case of this study is that of a generic\, flexible mis
 sile configuration in various flight conditions. The elastic deformation o
 f the missile's body significantly reduces the stability of the configurat
 ion\, which\, at some conditions\, becomes unstable. Nonlinear aerodynamic
  effects further reduce the missile's stability and are critical for accur
 ate prediction of the stability margin. The NSM accurately predicts the no
 nlinear aeroelastic solution without relying on a computational expensive 
 aeroelastic simulation in a CFD code.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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DTSTART:20181028T010000

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