The invention relates to the technical field of aircraft body manufacturing, and provides a method for sealing a composite wing wall panel and a metal wing rib based on a co-bonding process. The method comprises the steps that agap formed by a stringer edge strip of the wing wall panel and the metal wing rib is filled with glass fibers, specifically, the glass fibers form a sealing stopper; the stringer edge strip and the sealing stopper are connected with skin simultaneously in a co-bonding mode, before being cured, resin between the sealing stopper and the stringer edge strip is heated and then naturally flows for filling, and no gap exists after curing of the resin; a stringer, the sealing stopper and the skin form an integral structure; and the matching faces of the sealing stopper andthe metal wing rib are glued and sealed. Compared with the prior art, there is no need to separately manufacture a follow-up mold with theskin theoretical inner profile characteristics for the stopper, only a maintenance rubber stop mold is maintained, resin does not need to be separately cured in a hot pressure tank, and thus the cost is reduced; the sealing glue only needs to be applied to thematching faces of the stopper and the wing rib instead of being applied to the periphery of the stopper, so that the assembly procedure is simplified, and the sealing effect is improved; and the method is simple and practical, and has broad application prospects.