In the optimised design of aerospace vehicles, when the intersection line between two intersecting components undergoes changes due to geometric adjustments, the deformation of surface meshes at the intersection presents a complex challenge. This is crucial for maintaining mesh quality and accurately capturing both geometric and physical phenomena. To address this challenge, this paper proposes a novel surface mesh deformation method for intersecting components, resolving the difficulty of synchronising deformation across intersecting parts. Utilising CAD models described by parametric surfaces and initial meshes as input, the method analyses the topological relationships between components. It employs a topological matching strategy to ensure consistency between the mesh and geometric boundaries before and after deformation. This strategy comprises three core steps: information retrieval, information integration, and topological-geometric matching. For mesh handling at intersection lines, this method recalculates the intersection lines of parametric surfaces based on the CAD model. It then employs an arc-length normalisation method to map mesh points from the old intersection lines onto the new ones. For surface mesh point handling, the component's surface mesh serves as input. Using the displacement of intersection mesh nodes as boundary conditions, the displacement field is solved based on the initial component surface mesh's topological information, thereby achieving smooth deformation of the surface mesh. Finally, the volume mesh is updated based on the new surface mesh. Under the premise of preserving mesh topology at intersections, this method enables automatic updating of both geometric shape and computational mesh. Validation on the wing-fuselage junction of the DLR-F6 configuration demonstrates that this method preserves boundary layer resolution and mesh cell quality without requiring remeshing.