The utility model relates to the technical field of gliders, in particular to a carbon beam
composite material wing structure. The airfoil comprises an airfoil main beam and foam
layers located at the two ends of the airfoil main beam, the airfoil is of a structure which is thick in the middle and thin at the two ends on the whole, the airfoil main beam and the foam
layers are wrapped with a layer of airfoil
skin, and the airfoil main beam and the airfoil
handle are connected in an inserted mode and fastened through a binder and a bolt; a weight reduction structure is designed in a non-bearing area of the wing
handle, so that the overall weight of the structure is reduced; the modulus of the high-modulus carbon
fiber main beam can reach 200Gpa, so that the deformation in a bearing state is effectively controlled, and the structural
modal of the airfoil is improved; the high-modulus carbon beams and the wing handles are connected in an inserted mode, bonded through
epoxy glue and connected in a fastened mode through bolts, and the bearing force of the wing surfaces is effectively transmitted to wing
handle connecting points; the outer
skin of the airfoil is made of high-strength carbon
fiber one-way material, the laying direction and number of fibers are designed according to calculated stress, the 0-degree
fiber direction, the 90-degree fiber direction and the + / -45-degree fiber direction are configured, and the
torsional strength of the airfoil is improved on the premise that the bearing requirement is met.