Graphene-Enabled Aerospace Components: Evidence, Anisotropic Transport, and Mission-constrained Engineering

Aerospace adoption of graphene and related two-dimensional carbon materials is determined not by their exceptional constituent properties in isolation but by the admissibility of finished components under coupled mechanical, electrical, thermal, environmental, reliability, manufacturing and mass constraints. We develop a detailed, evidence-bounded engineering analysis anchored in two distinct published programmes: graphene-spray-functionalized carbon-fibre/polyether-ether-ketone (CF/PEEK) laminates and a separately modelled multifunctional aircraft floor-beam electrical-power concept.

Published 0.25 wt% graphene specimens exhibited apparent electrical-conductivity multipliers of 2.23 longitudinally, 3.52 transversely and 3.04 through thickness, but were characterized with two-terminal instrumentation; contact-separated intrinsic conductivities and component-scale terminations remain unidentified. Mean compression-shear strength declined from 57.18 to 45.39 MPa in the same experimental programme, with increased void formation.

The aircraft-system case developed a 28 V, 30 W electrical duty and moved from a 4.5 m member to a 2.75 m electrically active length with a reported 0.875-ohm design response. Primary-source reconciliation reveals that the same study’s tabulated 50-mm electrode fit yields 0.6718 ohm at 2.75 m, not 0.875 ohm, and its model defines total CFRP resistance to include contact contributions. The reason for this numerical discrepancy cannot be established unambiguously from the stated fitted configuration.

We derive exact distinct limits for fixed-current, constant-power and constant-impedance loads (0.914667, 0.882653 and 0.947841 ohm respectively, assuming a 3.5% drop) without attributing a particular load law to aircraft equipment. The calculated margin of a reported configuration is not a verified physical system margin until its electrical boundary and reported model values are reconciled.

A source-grounded conventional AWG20 reference and a boundary-condition-sensitive axial heat model demonstrate why isolated conductivity multipliers cannot determine a system-level winner. The analysis then integrates classical-laminate-theory structural vetoes, interface and manufacturing variability, corrosion and repair durability, heat-shield ablation physics, lightning-protection assessment, harsh-environment optics, and life-cycle break-even accounting.

All computational outputs distinguish measured inputs, derived consequences, and illustrative physical parameters. No physical experiments, qualified material allowables, or flight-design approvals are claimed. The resulting paper is an expansive theoretical engineering synthesis with a tightly bounded, falsifiable aircraft-electricity case study rather than an experimentally verified graphene breakthrough.