Aeroelastic stability of folding tiltrotor aircraft in cruise flight with composite wings

Jason C. Slaby, Edward Smith

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

1 Citation (Scopus)

Abstract

The presence of a folded rotor pylon on the end of the wing for a stop/fold rotorcraft has an effect on the structural response at high speed cruise. A forward swept wing would be required for the stopping and folding process as well as the high speed flight. Divergence velocity of a forward swept wing can be greatly decreased in a standard metallic isotropic wing structure because the bending will cause the angle of attack to increase and cause a feedback of bending and twisting. The addition of the rotor pylon influenced the lift and drag to the wingtip depending on the shape and placement of the pylon. The shape of the pylon on the wing tip was found to have a greater influence on the divergence velocity, than the location of the pylon relative to the wing. Changing the shape of the pylon decreased the divergence velocity by over 15% while changing the location of the pylon only affected the divergence by 4%. The addition of the pylon drag on the deflecting wing caused a torque that had the largest influence on the divergence velocity from the pylon. Depending on the sweep of the wing the drag force reduced the divergence velocity from 25%-60%. Composite tailoring was used to lessen the loss by inducing a bending-torsion coupling in the opposite direction by stiffening the structure off axis. The main concern of the composite tailoring was to maintain the bending and torsional stiffness on the wing. When composite tailoring was included, while maintaining the effective stiffnesses, the divergence velocity was maintained at a value greater than the loss from the lift or drag caused by the pylon.

Original languageEnglish (US)
Title of host publication52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
DOIs
StatePublished - Dec 1 2011
Event52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference - Denver, CO, United States
Duration: Apr 4 2011Apr 7 2011

Publication series

NameCollection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
ISSN (Print)0273-4508

Other

Other52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
CountryUnited States
CityDenver, CO
Period4/4/114/7/11

Fingerprint

Aircraft
Composite materials
Drag
Swept wings
Rotors
Stiffness
Angle of attack
Torsional stress
Torque
Feedback

All Science Journal Classification (ASJC) codes

  • Architecture
  • Materials Science(all)
  • Aerospace Engineering
  • Mechanics of Materials
  • Mechanical Engineering

Cite this

Slaby, J. C., & Smith, E. (2011). Aeroelastic stability of folding tiltrotor aircraft in cruise flight with composite wings. In 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference [AIAA 2011-2171] (Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference). https://doi.org/10.2514/6.2011-2171
Slaby, Jason C. ; Smith, Edward. / Aeroelastic stability of folding tiltrotor aircraft in cruise flight with composite wings. 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 2011. (Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference).
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title = "Aeroelastic stability of folding tiltrotor aircraft in cruise flight with composite wings",
abstract = "The presence of a folded rotor pylon on the end of the wing for a stop/fold rotorcraft has an effect on the structural response at high speed cruise. A forward swept wing would be required for the stopping and folding process as well as the high speed flight. Divergence velocity of a forward swept wing can be greatly decreased in a standard metallic isotropic wing structure because the bending will cause the angle of attack to increase and cause a feedback of bending and twisting. The addition of the rotor pylon influenced the lift and drag to the wingtip depending on the shape and placement of the pylon. The shape of the pylon on the wing tip was found to have a greater influence on the divergence velocity, than the location of the pylon relative to the wing. Changing the shape of the pylon decreased the divergence velocity by over 15{\%} while changing the location of the pylon only affected the divergence by 4{\%}. The addition of the pylon drag on the deflecting wing caused a torque that had the largest influence on the divergence velocity from the pylon. Depending on the sweep of the wing the drag force reduced the divergence velocity from 25{\%}-60{\%}. Composite tailoring was used to lessen the loss by inducing a bending-torsion coupling in the opposite direction by stiffening the structure off axis. The main concern of the composite tailoring was to maintain the bending and torsional stiffness on the wing. When composite tailoring was included, while maintaining the effective stiffnesses, the divergence velocity was maintained at a value greater than the loss from the lift or drag caused by the pylon.",
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Slaby, JC & Smith, E 2011, Aeroelastic stability of folding tiltrotor aircraft in cruise flight with composite wings. in 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference., AIAA 2011-2171, Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Denver, CO, United States, 4/4/11. https://doi.org/10.2514/6.2011-2171

Aeroelastic stability of folding tiltrotor aircraft in cruise flight with composite wings. / Slaby, Jason C.; Smith, Edward.

52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 2011. AIAA 2011-2171 (Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference).

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

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N2 - The presence of a folded rotor pylon on the end of the wing for a stop/fold rotorcraft has an effect on the structural response at high speed cruise. A forward swept wing would be required for the stopping and folding process as well as the high speed flight. Divergence velocity of a forward swept wing can be greatly decreased in a standard metallic isotropic wing structure because the bending will cause the angle of attack to increase and cause a feedback of bending and twisting. The addition of the rotor pylon influenced the lift and drag to the wingtip depending on the shape and placement of the pylon. The shape of the pylon on the wing tip was found to have a greater influence on the divergence velocity, than the location of the pylon relative to the wing. Changing the shape of the pylon decreased the divergence velocity by over 15% while changing the location of the pylon only affected the divergence by 4%. The addition of the pylon drag on the deflecting wing caused a torque that had the largest influence on the divergence velocity from the pylon. Depending on the sweep of the wing the drag force reduced the divergence velocity from 25%-60%. Composite tailoring was used to lessen the loss by inducing a bending-torsion coupling in the opposite direction by stiffening the structure off axis. The main concern of the composite tailoring was to maintain the bending and torsional stiffness on the wing. When composite tailoring was included, while maintaining the effective stiffnesses, the divergence velocity was maintained at a value greater than the loss from the lift or drag caused by the pylon.

AB - The presence of a folded rotor pylon on the end of the wing for a stop/fold rotorcraft has an effect on the structural response at high speed cruise. A forward swept wing would be required for the stopping and folding process as well as the high speed flight. Divergence velocity of a forward swept wing can be greatly decreased in a standard metallic isotropic wing structure because the bending will cause the angle of attack to increase and cause a feedback of bending and twisting. The addition of the rotor pylon influenced the lift and drag to the wingtip depending on the shape and placement of the pylon. The shape of the pylon on the wing tip was found to have a greater influence on the divergence velocity, than the location of the pylon relative to the wing. Changing the shape of the pylon decreased the divergence velocity by over 15% while changing the location of the pylon only affected the divergence by 4%. The addition of the pylon drag on the deflecting wing caused a torque that had the largest influence on the divergence velocity from the pylon. Depending on the sweep of the wing the drag force reduced the divergence velocity from 25%-60%. Composite tailoring was used to lessen the loss by inducing a bending-torsion coupling in the opposite direction by stiffening the structure off axis. The main concern of the composite tailoring was to maintain the bending and torsional stiffness on the wing. When composite tailoring was included, while maintaining the effective stiffnesses, the divergence velocity was maintained at a value greater than the loss from the lift or drag caused by the pylon.

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Slaby JC, Smith E. Aeroelastic stability of folding tiltrotor aircraft in cruise flight with composite wings. In 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 2011. AIAA 2011-2171. (Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference). https://doi.org/10.2514/6.2011-2171