Abstract
Calculating hinge moments during the morphing process is a critical aspect in the folding wing design. The deficiencies of the traditional flat-plate aerodynamic model in the calculation are expounded in this work, and a flight simulation platform based on a high-order panel method is established. On the basis of the platform, a typical flight-folding process of the aircraft is simulated, and the results of different aerodynamic models are compared. Results show that airfoil thickness has a great influence on the aerodynamic loading distribution of wing surfaces and thus affects the hinge moments during the folding process. The flat-plate method, which ignores the influence of the airfoil thickness, shows a great simulation error in hinge moment, whereas the high-order panel method can effectively describe the thickness effect and obtain reliable simulation results.
Highlights
As a typical morphing scheme, folding wing has received extensive attention in recent years [1,2,3]
Xu et al [8] developed the doublet lattice method and deduced the suitable aerodynamic influence coefficient (AIC) matrices for the morphing process. e flight-folding process of a folding wing aircraft was simulated by coupling this aerodynamic model with the multibody structural model in a>] integrated the flexible multibody dynamics method (ADAMS), and the general variations of the dynamic parameters during the process were investigated
This paper discovered that when the folding angle was large, serious aerodynamic interference will occur between the wing surfaces due to airfoil thickness, which will affect the hinge moments during the folding process. us, the flat-plate method shows deficiencies in the calculation of the folding wing’s hinge moments
Summary
As a typical morphing scheme, folding wing has received extensive attention in recent years [1,2,3]. Reich et al [5, 6] integrated the flexible multibody dynamics method (ADAMS) and the vortex lattice method (an in-house code) to develop an aeroelastic multibody morphing simulation tool for simulating the morphing process of a folding wing aircraft. On this basis, Scarlett et al [7] conducted a series of wind tunnel simulations on folding wing and investigated the changes in load paths and hinge moments under specific motions. A calculation method of hinge moments for folding wing based on the high-order panel method is presented. The typical flight-folding process of a folding wing aircraft is simulated, and the results of different aerodynamic models are compared
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
