CFRP uses macro-scale continuous carbon fibers (measured in microns) as the primary load-bearing reinforcement, engineered with precise fiber orientation strategies across ply angles. CNRP (MWCNT-based) uses nanoscale carbon tubes (10+ nm diameter) as matrix modifiers rather than primary load-bearing fiber architectures. This means CNRPs in their current disclosed form are more likely to serve as hybrid additions to existing CFRP systems — improving matrix toughness and interlaminar properties — rather than standalone replacements for woven or unidirectional carbon fiber plies in primary aircraft structures.

Carbon fiber laminates can accumulate charge and exhibit poor out-of-plane (z-direction) conductivity, creating lightning-strike vulnerability. Boeing's Z-Conductivity Improvement patent (2017) directly addresses this by integrating inter-ply electrical connections during the manufacturing process to provide lightning protection without weight-adding supplemental materials. Traditional metal meshes used for lightning protection on CFRP panels add appreciable weight, partially offsetting the mass savings from replacing aluminum structures.

The CFRP Surface Table patent from Nippon Oil Corporation (2005) establishes key intrinsic material properties of high-modulus CFRP: tensile moduli in the range of 490–950 GPa, combined with low thermal expansion and low areal weight. These properties — high specific stiffness and near-zero coefficient of thermal expansion — are foundational reasons CFRP is preferred in precision aerospace structures such as wing skins, control surfaces, and structural frames.

Direct contact between carbon fiber and aluminum creates galvanic cells. Toray Industries' Light Metal/CFRP Structural Members patent (2000) discloses an adhesive layer of 10–500 μm thickness with volume resistivity exceeding 1×10¹³ Ω·cm and adhesive strength of at least 15 MPa at room temperature, used to bond CFRP to light metal surfaces. The patent explicitly claims improved electrolytic corrosion resistance along with simultaneous weight reduction, strength improvement, and enhanced impact energy absorption.

CNRP materials, as represented by MWCNT-enhanced thermoplastics, show promise in electrical conductivity and matrix-level mechanical improvement but have no aircraft-primary-structure-specific patents in the provided dataset, indicating a substantial maturity gap. The LG Chem patent (2017) is positioned for general molded articles rather than specifically for primary aircraft structure. CFRP, by contrast, has decades of aerospace qualification data and is in production use on major aircraft programs.

SABIC Global Technologies' Multiple Ply Layered Composite patents (2017) describe a global optimization unit employing Mixed Integer Nonlinear Programming (MINLP) to simultaneously optimize fiber alignment angles across plies, targeting minimum areal weight and cost. The approach outperforms trial-and-error and heuristic algorithms, generating composite layup designs that traditional design methods cannot achieve. For aircraft applications, where even a 1 kg reduction in structural mass translates to measurable fuel savings over the aircraft lifecycle, this optimization methodology is directly commercially relevant.