Authors: Shuo Zhang; Zhengjie Wang; Wenming Dong
Addresses: Mechatronics School, 5th Zhongguancun South St, Haidian District, Beijing, China ' Mechatronics School, 5th Zhongguancun South St, Haidian District, Beijing, China ' Mechatronics School, 5th Zhongguancun South St, Haidian District, Beijing, China
Abstract: Morphing wings can be more stable and more robust to gust in the flow of low Reynolds number compared with normal fixed wings. In contrast to big airplanes, small ones with morphing wings can rely on passive wing deformation to reduce disturbance rather than active control by multi-control surfaces. Engineering modelling for the prototype in the paper ignores aeroelastic effect because of the small deformation amount in terms of static aeroelasticity and high modal frequency in terms of dynamic aeroelasticity. Aerodynamic coefficients are determined through flight test and software calculation. An accurate trim condition is solved using a 6DOF flight model. The preciseness of the trim result is proved by comparing experiment results. The longitudinal and lateral state-space equations benchmarked against trim point is built. Dynamic response of the non-control perturbation motion are analysed.
Keywords: small aerial vehicle; morphing wing; flight experiment; flight dynamic modelling.
International Journal of Modelling, Identification and Control, 2017 Vol.27 No.3, pp.219 - 229
Received: 24 Feb 2016
Accepted: 27 Apr 2016
Published online: 22 Apr 2017 *