TY - GEN
T1 - Dynamics modeling and simulation of small flexible wing aircraft
AU - Yang, Chen
AU - Zhengjie, Wang
AU - Meifang, Guo
AU - Yuanhang, Wang
N1 - Publisher Copyright:
© 2014 Swinburne University of Technology, Australia.
PY - 2015/1/23
Y1 - 2015/1/23
N2 - Small flexible wing aircraft (FWA) is a kind of flexible aircraft which uses distributed actuators to deform the wing so as to get a better aerodynamic shape and generate control forces and torques. The elastic vibration of the wing will have a great influence on rigid-body degrees of freedom (DoF) for the aircraft. The 6-DoF model of flight dynamics, which is under the traditional rigid-body assumption, cannot describe coupling effects of the rigid-body and elastic degrees of freedom. To solve this problem, the aircraft needs to be taken as an elastomer free in space to establish its dynamic model, which is studied based on the second class Lagrange's equation in this paper. By this modeling method, complete kinetic equations of FWA are derived under the mean axes condition, and the unsteady aerodynamic is included in the equations. Unsteady aerodynamic is calculated by two-dimensional Theodorsen's theory. And strip theory assumption is used to simplify the calculation. To analyze the influence of the unsteady aerodynamic on the structure vibration of the wing, the time-domain response characteristics of wing structure with and without unsteady aerodynamic are compared in this paper by numerical calculation. And the results show that the unsteady aerodynamic will cause great damping effect.
AB - Small flexible wing aircraft (FWA) is a kind of flexible aircraft which uses distributed actuators to deform the wing so as to get a better aerodynamic shape and generate control forces and torques. The elastic vibration of the wing will have a great influence on rigid-body degrees of freedom (DoF) for the aircraft. The 6-DoF model of flight dynamics, which is under the traditional rigid-body assumption, cannot describe coupling effects of the rigid-body and elastic degrees of freedom. To solve this problem, the aircraft needs to be taken as an elastomer free in space to establish its dynamic model, which is studied based on the second class Lagrange's equation in this paper. By this modeling method, complete kinetic equations of FWA are derived under the mean axes condition, and the unsteady aerodynamic is included in the equations. Unsteady aerodynamic is calculated by two-dimensional Theodorsen's theory. And strip theory assumption is used to simplify the calculation. To analyze the influence of the unsteady aerodynamic on the structure vibration of the wing, the time-domain response characteristics of wing structure with and without unsteady aerodynamic are compared in this paper by numerical calculation. And the results show that the unsteady aerodynamic will cause great damping effect.
KW - Aeroelasticity
KW - Flexible Wing Aircraft
KW - Mean Axes
KW - Unsteady Aerodynamic
UR - http://www.scopus.com/inward/record.url?scp=84923518482&partnerID=8YFLogxK
U2 - 10.1109/ICMIC.2014.7020771
DO - 10.1109/ICMIC.2014.7020771
M3 - Conference contribution
AN - SCOPUS:84923518482
T3 - Proceedings of 2014 International Conference on Modelling, Identification and Control, ICMIC 2014
SP - 310
EP - 315
BT - Proceedings of 2014 International Conference on Modelling, Identification and Control, ICMIC 2014
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 6th International Conference on Modelling, Identification and Control, ICMIC 2014
Y2 - 3 December 2014 through 5 December 2014
ER -
