I have an aerospace-grade composite blade model in SolidWorks that includes a metal leading-edge cap and an adhesive layer. My current file shows two critical problems: layers are overlapping and, in other areas, gaps appear between the composite skin, the adhesive film, and the metal cap. I need these issues resolved as soon as possible. Your task is to open my native SolidWorks part (or assembly), identify why the laminate, adhesive, and cap are mis-aligned, and deliver a clean, fully constrained model that mates perfectly through the span and chord. Key expectations • Maintain the existing aerofoil geometry while correcting layer offsets. • Preserve the material stack-up: composite lay-up → adhesive → metal leading edge. • Ensure zero-gap contact and no interpenetration when the model is rebuilt or configurations change. • Return a parametric file so I can adjust ply thicknesses later without breaking the interfaces. I’m working under an ASAP timeline, so fast turnaround and clear communication of what you changed (features, mates, surfaces, etc.) will be appreciated. If you rely on specialized SolidWorks tools such as Surface Knit, Intersect, or Composite Laminate Design, please note that in a short hand-over summary. Send back the corrected SolidWorks file, a brief change log, and one screenshot confirming error-free rebuild.