RE:RE:RE:RE:RE:It's quite funny to watch how the price starts to creep up
Have you been reading up on this ? lol
Matrix is the compliemnt of fibres and resin. It's stiffness in any direction is dictated by fibre orientations (except transverse).
Improvement (25%) in the current Modulus "E" of Epoxy alone does little.
30% in Modulus of the CFRP does help in "Stiffness" when if comes to compression and flexure (bending) since most practical problems have flexure (combination of compression and tension on extremities).
A UTS improvement is dictated by the reinforcing fibres (Uni-directional tape having very high stiffness when comparad to carbon fabric).
The transverse UTS is dictated by the resin. This is a weak link.
The transverse shear strength of CFRP also plays a role in defining the extent of delamination when subjected to CAI. Improvement helps !!!!
Much damage comes from CAI (compression after impact) and the FAA are very stringent on damage tolerance requirements.
Not sure of your percentages in terms of which is better.
However, solving the CAI issues and limiting damage tolerance is paramount.
CAI damage limits design allowables to "notched" values which are much less (could be only up to 25%) of un-notched allowables.
Many researchers and R&D groups are looking at "stitching" longitudinal fibres together to give more transverse capability but this is limited in production environments.
All of your suggestions are only marginal in terms of where we need to go.