Nonlinear Structural, Nonlinear Aerodynamic Model for Static Aeroelastic Problems

AIAA Journal ◽  
2019 ◽  
Vol 57 (5) ◽  
pp. 2158-2170 ◽  
Author(s):  
Etay Kantor ◽  
Daniella E. Raveh ◽  
Rauno Cavallaro
Keyword(s):  
Aerodynamic Model ◽  
Nonlinear Structural ◽  
Nonlinear Aerodynamic

Identification of a nonlinear aerodynamic model of the F-14 aircraft

1995 ◽  
Vol 18 (6) ◽  
pp. 1292-1297 ◽  
Author(s):  
Thomas L. Trankle ◽  
Stephen D. Bachner
Keyword(s):  
Aerodynamic Model ◽  
Nonlinear Aerodynamic ◽  
F 14

scholarly journals Trajectory Estimation of Hypersonic Glide Vehicle Based on Analysis of Aerodynamic Performance

2019 ◽  
Vol 37 (6) ◽  
pp. 1102-1110
Author(s):  
Yunpeng Cheng ◽  
Xiaodong Yan ◽  
Feng Cheng
Keyword(s):  
High Speed ◽  
Engineering Calculation ◽  
Aerodynamic Performance ◽  
The State ◽  
Aerodynamic Parameter ◽  
Trajectory Estimation ◽  
Aerodynamic Model ◽  
Proposed Model ◽  
Improve Accuracy ◽  
Nonlinear Aerodynamic

Due to high speed and high maneuverability of hypersonic glide vehicles (HGVs), the state estimation of such targets has always been a research hotspot. In order to improve accuracy of the trajectory estimation, a nonlinear aerodynamic parameter model for target estimation based on aerodynamic performance analysis is proposed. Firstly, the dynamic characteristics of the hypersonic glide vehicle during the hypersonic gliding stage was analyzed. Then, aiming at HTV-2-liked vehicle, the engineering calculation method was used to form the reference aerodynamic model for the target estimation. Secondly, a deviation model described by first-order Markov process was introduced to compensate the uncertainties of the unknown maneuver information from the target. Finally, extended Kalman filter was utilized to estimate the state of the target. The simulation results show that the proposed model is able to improve the accuracy of acceleration estimation for the HTV-2-liked hypersonic gliding vehicles.

Nonlinear Aeroelastic Behavior of Slender Wings Considering a Static Stall Model Based on Wagner Function

2013 ◽  
Vol 325-326 ◽  
pp. 172-179
Author(s):  
D. Badiei ◽  
M.H. Sadr ◽  
Sh. Shams
Keyword(s):  
Equations Of Motion ◽  
Linear Part ◽  
Beam Theory ◽  
Structural Equations ◽  
Aeroelastic Response ◽  
Linear Elastic ◽  
Model Based ◽  
Aerodynamic Model ◽  
Lift Curve ◽  
Nonlinear Aerodynamic

The aeroelastic behavior of high aspect ratio wings in an incompressible flow is investigated. The nonlinear nonplanar bending-bending-twisting motions of beam theory is used for the structural equations assuming large deformations with small strains, small Poisson effects, inextensional beam theory, and linear elastic material characteristics by neglecting warping and shear deformation. An Unsteady nonlinear aerodynamic static stall model based on the Wagner function is introduced and then is used for determination of aerodynamic loading of the wing. In this aerodynamic model, the static lift curve vs. angle of attack is approximated by a piece-wise curve and for each linear part of this curve a corrected Wagner theory is used. Combining these two types of formulation yields fully nonlinear integro-differentials aeroelastic equations of motion. The governing equations will be solved to predict the nonlinear aeroelastic response of a wing in the stall and post stall regions using Galerkin's method and a numerical method without the need of adding any aerodynamic state-space variables and their corresponding equations. The obtained equations are solved for some test cases and the obtained results are compared with the results given in the literature. Also a study is done to show effects of nonlinear aerodynamic static stall model on the limit cycle oscillations.

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