Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process

Abstract

A folding wing morphing aircraft should complete the folding and unfolding process of its wings while in flight. Calculating the hinge moments during the morphing process is a critical aspect of a folding wing design. Most previous studies on this problem have adopted steady-state or quasi-steady-state methods, which do not simulate the free-flying morphing process. In this study, we construct an aeroelastic flight simulation platform based on the secondary development of ADAMS software to simulate the flight-folding process of a folding wing aircraft. A flexible multibody dynamic model of the folding wing structure is established in ADAMS using modal neutral files, and the doublet lattice method is developed to generate aerodynamic influence coefficient matrices that are suitable for the flight-folding process. The user subroutine is utilized, aerodynamic loading is realized in ADAMS, and an aeroelastic flight simulation platform of a folding wing aircraft is built. On the basis of this platform, the flight-folding process of the aircraft is simulated, the hinge moments of the folding wings are calculated, and the influences of the folding rate and the aircraft’s center of gravity (c.g.) position on the results are investigated. Results show that the steady-state method is applicable to the slow folding process. For the fast folding process, the steady-state simulation errors of the hinge moments are substantially large, and a transient method is required to simulate the flight-folding process. In addition, the c.g. position considerably affects the hinge moments during the folding process. Given that the c.g. position moves aft, the maximum hinge moments of the inner and outer wings constantly increase.

Calculation of Hinge Moments for a Folding Wing Aircraft Based on High-Order Panel Method

“…e comparison of the simulation results between the proposed and flat-plate methods [8] is shown in Figure 15.…”

“…e simulation platform in this study is based on study in [8]. Certain necessary modifications are applied to the aerodynamic model to consider the thickness effect.…”

“…e main geometric parameters of the folding wing are listed in Table 1. For more details about the model, refer to [8].…”

“…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. 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 ADAMS, and the general variations of the dynamic parameters (e.g., angle of attack, altitude, deflection angle of ailerons, and hinge moments) during the process were investigated.…”

Comparative Study of Lifting Surface and CFD Methods in the Simulation of Morphing Process of Folding Wing

“…Using this tool, Scarlett et al [7] performed several wind tunnel simulations on the folding wing and studied the variations of hinge moments and load paths under specific motions. Xu et al [8] deduced the time-domain unsteady aerodynamic influence coefficients suitable for the morphing process by the doublet lattice method and integrated this aerodynamic model with the flexible multibody structure model established in Adams to simulate the flight-morphing process of a folding wing. In the simulation, the general variations of the dynamic parameters, including the hinge moment, were investigated.…”