Good stuff.
Of course, when discussing relative strength and stiffness of jointed composite structure (hull to deck) one must take into consideration classical matrix laminate theory in comparing the basic laminate properties in relation to the joint. It is nearly impossible to ever develop similar properties in the joint as with the base laminate unless you painstakingly interweave each and every layer in a proper proportion taking into account the tensile and shear properties of the plasticizing binder in an effort to match the original laminate, ensuring to employ adequate planar interface area between layers to achieve inter-laminar stress capability summarily equal to or greater than the constituents as proven by fatigue testing over the entire plastic to yield range. If not, that's where failures and stiffness problems will be realized.
When I was developing the vertical stabilizer to empennage joint for the Boeing 787 dreamliner, we learned a about the limitations of composite joints during fatigue testing. Proof is in the pudding.