Adaptive Feedforward Control for Gust Loads Alleviation

Zeng, Jie; Moulin, Boris; Callafon, Raymond de; Brenner, Marty

doi:10.2514/6.2008-6373

Cited by 3 publications

(1 citation statement)

References 11 publications

(7 reference statements)

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“…Figures 20-45 show the responses obatined at various angle of attacks. A system identification technique called polyMAX [46][47][48] is used to assess the damping and frequency of the lift (FZ) response. The sign convention of damping (used here) for stable system is positive and for an unstable system is negative.…”

Section: A Flutter Boundary Of Joined Wingmentioning

confidence: 99%

Dynamic Nonlinear Aeroelastic Analysis of the Joined Wing Configuration

Bhasin¹,

Chen²,

Wang³

et al. 2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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The unsteady vortex lattice method (UVLM) is coupled via OpenFSI with MD Nastran's dynamic nonlinear structural solver to study the aeroelastic response of the joined wing configuration in a subsonic regime. Initially, a number of static nonlinear structural analyses are performed on the nonlinear beam model to investigate the nonlinearities associated with the structure. The primary reason for the investigation of the structural nonlinearities is to make intelligible the aeroelastic response of the structure. After a successful validation of UVLM.OpenFSI, a panel based aerodynamic model is splined with the structural model for accurate transfer of forces and displacements at every time step via OpenFSI. A new boundary value problem is solved for the modified aerodynamic model at every time step. Evolution of the wake and its aerodynamic effects are well accounted for. Time domain responses of the lift generated by the joined wing configuration under various loading conditions is obtained. The flutter boundary of the joined wing configuration is calculated by interpolating between the dampings values evaluated for stable and unstable time domain responses. Also presented is the time domain response of the joined wing configuration when subjected to external excitations, predicting the onset of flutter and the post flutter behavior.

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Section: A Flutter Boundary Of Joined Wingmentioning
confidence: 99%

Dynamic Nonlinear Aeroelastic Analysis of the Joined Wing Configuration
Bhasin¹,
Chen²,
Wang³
et al. 2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
3
0
8
0
View full text Add to dashboard Cite

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LIDAR-based FX-RLS feedforward control for wind turbine load mitigation
Wang
¹
,
Johnson
²
,
Wright
³

2011
Proceedings of the 2011 American Control Conference
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16
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Hybrid adaptive control for gust load alleviation
Bian
¹
,
Li
²
,
Qin
³

et al. 2015
2015 34th Chinese Control Conference (CCC)
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Adaptive Feedforward Control for Gust Loads Alleviation

Cited by 3 publications

References 11 publications

Dynamic Nonlinear Aeroelastic Analysis of the Joined Wing Configuration

Dynamic Nonlinear Aeroelastic Analysis of the Joined Wing Configuration

LIDAR-based FX-RLS feedforward control for wind turbine load mitigation

Hybrid adaptive control for gust load alleviation

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