Structural damping model for composite rotorcraft blades with carbon nanotube interlayers

Research output: Contribution to journalArticlepeer-review

Abstract

Traditional lag dampers used in rotorcraft applications are unable to produce adequate levels of damping for high-speed coaxial compound rotorcraft that use rigid, hingeless blades. The current paper shows the possibility of having an intrinsic passive damping solution through the use of carbon nanotubes (CNTs) embedded in the interlayer region of a carbon-fiber-reinforced epoxy composite laminate. The CNTs are assumed to have a reversible stick–slip damping mechanism in the composite. The dissipation caused by the slip between the CNTs and the epoxy matrix is proportional to the slippage length of the CNTs. A laminated composite model is used to simulate a spar with alternating plies and CNT interlayers. The model is used to predict the stresses, strains, and damping associated with the plies and interlayers. The laminated composite damping model is validated by comparing the predictions with experimental results from the literature. The model is used to demonstrate the effect of the CNT interlayers on the damping of the composite blade. The effects of blade rotational speed and key CNT parameters (such as aspect ratio and critical shear stress on the damping of the blade) are also investigated. Loss factors of over 8 and 6% were observed with optimally configured parameters for soft and stiff in-plane rotors, respectively (0.138% for the baseline blade). Overall, the results suggest significant damping augmentation is achievable from the use of CNT interlayers in carbon/epoxy blades.

Original languageEnglish (US)
Pages (from-to)1539-1547
Number of pages9
JournalAIAA journal
Volume59
Issue number5
DOIs
StatePublished - 2021

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this