Experimental validation of a fluidic pitch link model

Shawn M. Treacy, Christopher D. Rahn, Edward Smith, Conor Marr

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

Abstract

In order to reduce vibration, researchers have been exploring alternatives to conventional rigid pitch links. One viable passive vibration reduction device is the fluidic pitch link. By replacing rigid pitch links on rotorcraft with fluidic pitch links, changes can be made to the blade torsional impedance. At high frequencies, the pitch link impedance can be tuned to change the blade pitching response to higher harmonic loads. Although all have not been demonstrated simultaneously, fluidic pitch links have been shown to be able to reduce rotor power and all six hub forces and moments. A positive impact on aeroelastic stability from several fluidic pitch link designs has been shown for hover and forward flight. This paper will focus on validating the model that has been used in previous research via matching experimental and simulation results. A prototype fluidic pitch link has been designed, built, and tested at LORD Corporation. Displacement, load, and pressure were recorded during testing. Frequency and time response results were compared between simulation and experiment to validate the model. Three different fluid circuits were used, and the model was able to accurately predict performance for each of them with the exception of inaccuracy at low frequency due, in part, to the frequency dependence of the elastomer. An additional fourth circuit was tested that included a needle valve. The model did not accurately predict results across the entire range of valve positions, but the model was able to accurately match the dynamic stiffness amplitude using empirical parameters from a parameter study.

Original languageEnglish (US)
Title of host publication43rd European Rotorcraft Forum, ERF 2017
PublisherAssociazione Italiana di Aeronautica e Astronautica (AIDAA)
Pages1455-1468
Number of pages14
Volume2
ISBN (Print)9781510865389
StatePublished - Jan 1 2017
Event43rd European Rotorcraft Forum, ERF 2017 - Milan, Italy
Duration: Sep 12 2017Sep 15 2017

Other

Other43rd European Rotorcraft Forum, ERF 2017
CountryItaly
CityMilan
Period9/12/179/15/17

Fingerprint

fluidics
Fluidics
blades
Networks (circuits)
Elastomers
Needles
Frequency response
impedance
rotary wing aircraft
vibration
Rotors
hubs
Stiffness
time response
elastomers
needles
Fluids
frequency response
rotors
Testing

All Science Journal Classification (ASJC) codes

  • Control and Systems Engineering
  • Aerospace Engineering
  • Instrumentation
  • Electrical and Electronic Engineering

Cite this

Treacy, S. M., Rahn, C. D., Smith, E., & Marr, C. (2017). Experimental validation of a fluidic pitch link model. In 43rd European Rotorcraft Forum, ERF 2017 (Vol. 2, pp. 1455-1468). Associazione Italiana di Aeronautica e Astronautica (AIDAA).
Treacy, Shawn M. ; Rahn, Christopher D. ; Smith, Edward ; Marr, Conor. / Experimental validation of a fluidic pitch link model. 43rd European Rotorcraft Forum, ERF 2017. Vol. 2 Associazione Italiana di Aeronautica e Astronautica (AIDAA), 2017. pp. 1455-1468
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Treacy, SM, Rahn, CD, Smith, E & Marr, C 2017, Experimental validation of a fluidic pitch link model. in 43rd European Rotorcraft Forum, ERF 2017. vol. 2, Associazione Italiana di Aeronautica e Astronautica (AIDAA), pp. 1455-1468, 43rd European Rotorcraft Forum, ERF 2017, Milan, Italy, 9/12/17.

Experimental validation of a fluidic pitch link model. / Treacy, Shawn M.; Rahn, Christopher D.; Smith, Edward; Marr, Conor.

43rd European Rotorcraft Forum, ERF 2017. Vol. 2 Associazione Italiana di Aeronautica e Astronautica (AIDAA), 2017. p. 1455-1468.

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

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Treacy SM, Rahn CD, Smith E, Marr C. Experimental validation of a fluidic pitch link model. In 43rd European Rotorcraft Forum, ERF 2017. Vol. 2. Associazione Italiana di Aeronautica e Astronautica (AIDAA). 2017. p. 1455-1468