Modeling of Polymer/Carbon nanotube nanocomposite to estimate structural damping in a rotorcraft blade

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

The development of next-generation rotorcraft requires advancement in certain key areas such as cruise speed, payload, range, along with cost considerations. Coaxial and tiltrotors are two promising candidates for future of high speed vertical flight. Traditional lag dampers are unable to produce adequate levels of damping for the rigid fiber composite blades of coaxial rotorcraft. A promising approach for achieving lightweight damping in composite blades is to add carbon nanotubes (CNTs) to the matrix material. The current investigation aims to predict the damping behavior of a rotating beam that represents a simplified fiber reinforced polymer/CNT nanocomposite blade. The developed model takes in account different physical variables such as the critical shear stress (τ c) for slip onset of the CNTs and CNT aspect ratio (l/d), volume fraction (ν CNT), and orientation. The study first looks at a case where the nano-inclusions are aligned with the direction of loading for the rotor blade. The model predicts maximum damping for low τ c in combination with relatively low l/d. The damping trend increases with increase in ν CNT of the nano-inclusions. A damping ratio of 7.3% and 8% was observed with optimally configured parameters for aligned and randomly oriented CNTs respectively. Overall, the results suggest significant damping augmentation from the CNTs.

Original languageEnglish (US)
Title of host publication33rd Technical Conference of the American Society for Composites 2018
PublisherDEStech Publications Inc.
Pages1601-1620
Number of pages20
ISBN (Electronic)9781510872073
StatePublished - Jan 1 2018
Event33rd Technical Conference of the American Society for Composites 2018 - Seattle, United States
Duration: Sep 24 2018Sep 27 2018

Publication series

Name33rd Technical Conference of the American Society for Composites 2018
Volume3

Other

Other33rd Technical Conference of the American Society for Composites 2018
CountryUnited States
CitySeattle
Period9/24/189/27/18

Fingerprint

Carbon Nanotubes
Carbon nanotubes
Nanocomposites
Polymers
Damping
Fibers
Composite materials
Turbomachine blades
Shear stress
Aspect ratio
Volume fraction
Rotors

All Science Journal Classification (ASJC) codes

  • Mechanics of Materials
  • Surfaces, Coatings and Films
  • Metals and Alloys

Cite this

Prakash, K., Smith, E., & Bakis, C. E. (2018). Modeling of Polymer/Carbon nanotube nanocomposite to estimate structural damping in a rotorcraft blade. In 33rd Technical Conference of the American Society for Composites 2018 (pp. 1601-1620). (33rd Technical Conference of the American Society for Composites 2018; Vol. 3). DEStech Publications Inc..
Prakash, Keerti ; Smith, Edward ; Bakis, Charles E. / Modeling of Polymer/Carbon nanotube nanocomposite to estimate structural damping in a rotorcraft blade. 33rd Technical Conference of the American Society for Composites 2018. DEStech Publications Inc., 2018. pp. 1601-1620 (33rd Technical Conference of the American Society for Composites 2018).
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abstract = "The development of next-generation rotorcraft requires advancement in certain key areas such as cruise speed, payload, range, along with cost considerations. Coaxial and tiltrotors are two promising candidates for future of high speed vertical flight. Traditional lag dampers are unable to produce adequate levels of damping for the rigid fiber composite blades of coaxial rotorcraft. A promising approach for achieving lightweight damping in composite blades is to add carbon nanotubes (CNTs) to the matrix material. The current investigation aims to predict the damping behavior of a rotating beam that represents a simplified fiber reinforced polymer/CNT nanocomposite blade. The developed model takes in account different physical variables such as the critical shear stress (τ c) for slip onset of the CNTs and CNT aspect ratio (l/d), volume fraction (ν CNT), and orientation. The study first looks at a case where the nano-inclusions are aligned with the direction of loading for the rotor blade. The model predicts maximum damping for low τ c in combination with relatively low l/d. The damping trend increases with increase in ν CNT of the nano-inclusions. A damping ratio of 7.3{\%} and 8{\%} was observed with optimally configured parameters for aligned and randomly oriented CNTs respectively. Overall, the results suggest significant damping augmentation from the CNTs.",
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Prakash, K, Smith, E & Bakis, CE 2018, Modeling of Polymer/Carbon nanotube nanocomposite to estimate structural damping in a rotorcraft blade. in 33rd Technical Conference of the American Society for Composites 2018. 33rd Technical Conference of the American Society for Composites 2018, vol. 3, DEStech Publications Inc., pp. 1601-1620, 33rd Technical Conference of the American Society for Composites 2018, Seattle, United States, 9/24/18.

Modeling of Polymer/Carbon nanotube nanocomposite to estimate structural damping in a rotorcraft blade. / Prakash, Keerti; Smith, Edward; Bakis, Charles E.

33rd Technical Conference of the American Society for Composites 2018. DEStech Publications Inc., 2018. p. 1601-1620 (33rd Technical Conference of the American Society for Composites 2018; Vol. 3).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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N2 - The development of next-generation rotorcraft requires advancement in certain key areas such as cruise speed, payload, range, along with cost considerations. Coaxial and tiltrotors are two promising candidates for future of high speed vertical flight. Traditional lag dampers are unable to produce adequate levels of damping for the rigid fiber composite blades of coaxial rotorcraft. A promising approach for achieving lightweight damping in composite blades is to add carbon nanotubes (CNTs) to the matrix material. The current investigation aims to predict the damping behavior of a rotating beam that represents a simplified fiber reinforced polymer/CNT nanocomposite blade. The developed model takes in account different physical variables such as the critical shear stress (τ c) for slip onset of the CNTs and CNT aspect ratio (l/d), volume fraction (ν CNT), and orientation. The study first looks at a case where the nano-inclusions are aligned with the direction of loading for the rotor blade. The model predicts maximum damping for low τ c in combination with relatively low l/d. The damping trend increases with increase in ν CNT of the nano-inclusions. A damping ratio of 7.3% and 8% was observed with optimally configured parameters for aligned and randomly oriented CNTs respectively. Overall, the results suggest significant damping augmentation from the CNTs.

AB - The development of next-generation rotorcraft requires advancement in certain key areas such as cruise speed, payload, range, along with cost considerations. Coaxial and tiltrotors are two promising candidates for future of high speed vertical flight. Traditional lag dampers are unable to produce adequate levels of damping for the rigid fiber composite blades of coaxial rotorcraft. A promising approach for achieving lightweight damping in composite blades is to add carbon nanotubes (CNTs) to the matrix material. The current investigation aims to predict the damping behavior of a rotating beam that represents a simplified fiber reinforced polymer/CNT nanocomposite blade. The developed model takes in account different physical variables such as the critical shear stress (τ c) for slip onset of the CNTs and CNT aspect ratio (l/d), volume fraction (ν CNT), and orientation. The study first looks at a case where the nano-inclusions are aligned with the direction of loading for the rotor blade. The model predicts maximum damping for low τ c in combination with relatively low l/d. The damping trend increases with increase in ν CNT of the nano-inclusions. A damping ratio of 7.3% and 8% was observed with optimally configured parameters for aligned and randomly oriented CNTs respectively. Overall, the results suggest significant damping augmentation from the CNTs.

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Prakash K, Smith E, Bakis CE. Modeling of Polymer/Carbon nanotube nanocomposite to estimate structural damping in a rotorcraft blade. In 33rd Technical Conference of the American Society for Composites 2018. DEStech Publications Inc. 2018. p. 1601-1620. (33rd Technical Conference of the American Society for Composites 2018).