TY - JOUR
T1 - A method for nonlinear aeroelasticity trim and stability analysis of very flexible aircraft based on co-rotational theory
AU - Wang, Wei
AU - Zhu, Xiaoping
AU - Zhou, Zhou
AU - Duan, Jingbo
N1 - Publisher Copyright:
© 2016 Elsevier Ltd.
PY - 2016/4/1
Y1 - 2016/4/1
N2 - Very flexible aircraft with high aspect ratio wings subjected to aerodynamic loads undergoes large deformation, which will lead to distinct changes on the mass distributions, stiffness characteristics and aerodynamic characteristics of the complete aircraft. The aeroelasticity and flight dynamics of such aircrafts are nonlinear and the linear elastic theory model cannot be used. A new method is developed for the analysis of nonlinear aeroelasticity and flight dynamics of very flexible aircraft through combining the co-rotational beam theory with the modified ONERA dynamic stall model. Based on a form of co-rotational technique which is external to the element, a spatial two-node beam element, which depicts the geometrically nonlinear dynamic characteristics of the flexible wing, is developed. Both tangential stiffness matrix and mass matrix of the beam element are formulated to establish the nonlinear dynamic equations. In addition, the modified ONERA dynamic stall model is adapted to evaluate the unsteady nonlinear aerodynamic loading of the very flexible wing. Using the present method, the nonlinear aeroelastic response, trim and stability characteristics of a very flexible aircraft are predicted in this paper. The obtained results show a good agreement to the literature, which indicates that the present method is accurate and efficient.
AB - Very flexible aircraft with high aspect ratio wings subjected to aerodynamic loads undergoes large deformation, which will lead to distinct changes on the mass distributions, stiffness characteristics and aerodynamic characteristics of the complete aircraft. The aeroelasticity and flight dynamics of such aircrafts are nonlinear and the linear elastic theory model cannot be used. A new method is developed for the analysis of nonlinear aeroelasticity and flight dynamics of very flexible aircraft through combining the co-rotational beam theory with the modified ONERA dynamic stall model. Based on a form of co-rotational technique which is external to the element, a spatial two-node beam element, which depicts the geometrically nonlinear dynamic characteristics of the flexible wing, is developed. Both tangential stiffness matrix and mass matrix of the beam element are formulated to establish the nonlinear dynamic equations. In addition, the modified ONERA dynamic stall model is adapted to evaluate the unsteady nonlinear aerodynamic loading of the very flexible wing. Using the present method, the nonlinear aeroelastic response, trim and stability characteristics of a very flexible aircraft are predicted in this paper. The obtained results show a good agreement to the literature, which indicates that the present method is accurate and efficient.
KW - Co-rotational approach
KW - Flight dynamics
KW - Geometrically nonlinearity
KW - Nonlinear aeroelasticity
KW - Trim
KW - Very flexible aircraft
UR - http://www.scopus.com/inward/record.url?scp=84958745248&partnerID=8YFLogxK
U2 - 10.1016/j.jfluidstructs.2016.01.009
DO - 10.1016/j.jfluidstructs.2016.01.009
M3 - 文章
AN - SCOPUS:84958745248
SN - 0889-9746
VL - 62
SP - 209
EP - 229
JO - Journal of Fluids and Structures
JF - Journal of Fluids and Structures
ER -