Control system designing for correcting wing-fuselage assembly deformation of a large aircraft

摘要

Purpose - In aircraft wing-fuselage assembly, the distributed multi-point support layout of positioners causes fuselage to deform under gravity load, leading to assembly difficulty and assembly stress. This paper aims to propose a hybrid force position control method to balance aerodynamic shape accuracy and deformation of assembly area, thereby correcting assembly deformation and reducing assembly stress. Design/methodology/approach - Force and position control axes of positioners are selected based on screw theory and ellipsoid method. The position-control axes follow the posture trajectory to align the fuselage posture. To exert force on the fuselage and correct the deformations, the force-control axes follow the contact force derived by using orthogonal experiments and partial least squares regression (PLSR). Finite element simulation and one-dimension deformation correction experiment are conducted to verify the validity of this method. Findings - Simulation results indicate that hybrid force position control method can correct assembly deformation and improve the wing-fuselage assembly quality significantly. Experiment on specimen verifies the effect of this method indirectly. Originality/value - The proposed method gives a solution to solve the deformation problem during aircraft wing-fuselage assembly, thereby reducing assembly stress and improving assembly quality.