aeroelastic gust modelling
TRANSCRIPT
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Funded by the European Union
Aeroelastic Gust ModellingDiPaRT 18.11.15
Dr Robert Cook and Dr Chris WalesUniversity of Bristol
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Funded by the European Union
AeroGust Partners
• University of Bristol
• Institut National De Recherche En Informatique Et En Automatique (INRIA)
• Stichting Nationaal Lucht - En Ruimtevaartlaboratorium (NLR)
• Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)
• University of Cape Town
• Numerical Mechanics Applications International SA (NUMECA)
• Optimad engineering s.r.l.
• University of Liverpool
• Airbus Defence and Space
• Dassault Aviation SA
• Piaggio Aero Industries SPA
• Valeol SAS
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Funded by the European Union
The AeroGust Project• EU funded Horizon 2020 project
• Collaboration between industry and academia
• Inspiration from Flight Path 2050
• Maintaining and extending industrial leadership
Background• Market trend for adoption of more flexible structures, novel design configurations and higher flight speeds
• Pushing limits of linear analyses
• Process relies on wind tunnel data from predicted cruise geometry
• Gust loads considered relatively late in design procedure – design space limited
• Extension of aerospace technologies to wind turbine design
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Funded by the European Union
AeroGust Work Packages
• WP1: Management, Dissemination and Exploitation
• WP2: Understanding the Nonlinearities of Gust Interaction
• WP3: Reduced reliance on wind tunnel data
• WP4: Adapting the loads process for non-linear and innovative structures
• WP5: Data Collection and Comparison
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Funded by the European Union
AeroGust Work Packages
• WP1: Management, Dissemination and Exploitation
• WP2: Understanding the Nonlinearities of Gust Interaction
• WP3: Reduced reliance on wind tunnel data
• WP4: Adapting the loads process for non-linear and innovative structures
• WP5: Data Collection and Comparison
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Funded by the European Union
WP2: Understanding the Nonlinearities of Gust Interaction
• Investigate aerodynamic nonlinearities due to aircraft-gust responses
- compare the computational capability of different approaches
• Investigate classical gust definitions
- develop new models incorporating compressibility effects
• Investigate the impact of structural nonlinearities on aircraft-gust responses
• Investigate the interaction of aerodynamic and structural nonlinearities in aircraft-gust responses
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Funded by the European Union
77
Civil transport
Military – high speed
Wind turbine
UAV-high AR
Potential Test Cases
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Funded by the European Union
WP3: Reduced Reliance on Wind Tunnel Data
• Recreate the industrial loads process
- Using CFD to generate the experimental corrections
• Assess Impact of Underlying Assumptions of the Current Loads Process
• Extend the Current Process
- Highly flexible structures
- Innovative structures
• Include Uncertainty in Aerodynamic and Structural Models
- Impact on gust loads
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Funded by the European Union
• ROMs for Gusts
- Implementation and development of aerodynamic ROMs
- Use of small amounts of high quality numerical or experimental data to improve accuracy and range of aerodynamic ROMs
- Aeroelastic ROMs
• Hybrid ROM/High Fidelity Methods.
- Accuracy, cost, robustness and range of applicability will be investigated
• Uncertainty Methods for ROM Development
WP4: Adapting the Loads Process for Non-linear and Innovative Structures
Full Order
ROM
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Preliminary Investigations• Aeroelastic analyses on highly flexible wing
• Considered Hodges’ HALE UAV wing for analysis
• Intrinsic beam methodology with VLM/UVLM
• Considerable differences observed for follower, non-f, and linear analyses
• Code validated against NASTRAN/other UoB codes
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Preliminary Investigations• Comparisons of aeroelastic analyses to traditional linear approaches
• Linear aeroelastic analyses become poor, even at relatively low AoA
• Nonlinear aeroelastic models show considerable sensitivity to drag modelling
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Funded by the European Union
Preliminary Investigations – Dynamic Model
Current Work
Exact Patil (et al)Error
8 Elements Error
16 Elements Error
32 Elements Error
rad/s rad/s rad/s rad/s rad/s
2.24 2.25 0.18% 2.25 0.42% 2.24 0.05% 2.24 -0.04%
14.06 14.61 3.77% 14.87 5.46% 14.21 1.06% 14.05 -0.05%
31.05 31.15 0.32% 31.15 0.32% 31.07 0.08% 31.05 0.02%
31.72 31.74 0.07% 31.85 0.43% 31.74 0.06% 31.71 -0.03%
39.36 44.01 10.58% 46.09 14.61% 40.56 2.98% 39.35 0.00%
• Eigenmodes can be calculated
• Good agreement with exact solution
• Dynamic solver agrees with modal results
1st Bending
2nd Bending
1st Torsion
Fore-Aft Bending
3rd Bending
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Funded by the European Union
stitched VLM
components
rapid &
robust
unsteady
VLM
Loads DatabaseCFD or
experiment
Target
High T-tail
Prop wash
Strut
braced
universal
correction
process /
matrices
Rapid Loads evaluation
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Funded by the European Union
UVLM correction process𝐶0 + 𝐶𝑤𝑤𝑏 + 𝑤𝑤 = 𝐴Γ
Map CFD loads on to UVLM mesh
Iterate correction matrices calculation due to interaction with wake
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UVLM gust
• Vertical 1-cosine gust
• U∞ = 162m/s
• Gust gradient = 30ft
• Gust velocity = 5.21 m/s
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UVLM rigid pitch
• Rigid pitching UAV wing
• U∞ = 162m/s, K=0.2
1 degrees 2 degrees 4 degrees
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Funded by the European Union
Acknowledgement
This work has been funded from the European Union's Horizon 2020 research and innovation programme under grant agreement No 636053