Active Flutter Suppression-A Flight Test Demonstration

Roger, Kenneth L.; Hodges, G.; Felt, Larry

doi:10.2514/3.59833

Cited by 71 publications

(21 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…On this basis, Fehren et al [5] proposed an improved scheme in 2001 and increased the number of piezoelectric actuators to 14. Besides, some other organizations are also concerned about the vibration of wind tunnel models. Up to now, a great many of convincing results has been obtained in thousands of attempts [6][7][8][9][10][11][12][13][14][15]. And in term of algorithms, classical PD is still the most popular and practical control algorithm in engineering although it has some limitations, especially when the control objects are different, the parameters of the controller are difficult to adjust automatically to adapt to the changing of the external environment.…”

Section: Introductionmentioning

confidence: 99%

Active Vibration Control of the Sting Used in Wind Tunnel: Comparison of Three Control Algorithms

Shen

Dai

Chen

et al. 2018

Shock and Vibration

View full text Add to dashboard Cite

In wind tunnel tests, cantilever stings are often used as model-mount in order to reduce flow interference on experimental data. In this case, however, large-amplitude vibration and low-frequency vibration are easily produced on the system, which indicates the potential hazards of gaining inaccurate data and even damaging the structure. is paper details three algorithms, respectively, Classical PD Algorithm, Artificial Neural Network PID (NNPID), and Linear Quadratic Regulator (LQR) Optimal Control Algorithm, which can realize active vibration control of sting used in wind tunnel. e hardware platform of the first-order vibration damping system based on piezoelectric structure is set up and the real-time control software is designed to verify the feasibility and practicability of the algorithms. While the PD algorithm is the most common method in engineering, the results show that all the algorithms can achieve the purpose of over 80% reduction, and the last two algorithms perform even better. Besides, self-tuning is realized in NNPID, and with the help of the Observer/Kalman Filter Identification (OKID), LQR optimal control algorithm can make the control effort as small as possible. e paper proves the superiority of NNPID and LQR algorithms and can be an available reference for vibration control of wind tunnel system.

show abstract

Section: Introductionmentioning

confidence: 99%

Active Vibration Control of the Sting Used in Wind Tunnel: Comparison of Three Control Algorithms

Shen

Dai

Chen

et al. 2018

Shock and Vibration

View full text Add to dashboard Cite

show abstract

“…5,6 A similar configuration was also used in the first flight test beyond flutter speed, conducted in 1973 on a modified B-52 aircraft. 7 The control system on that aircraft involved two single feedback loops that fed back filtered vertical acceleration signals, acquired on the wing, to control surfaces located nearby (outboard ailerons and flaperons). Collocated acceleration feedback is also proposed in various other publications concerned with flutter suppression, e. g. Refs.…”

Section: Introductionmentioning

confidence: 99%

Robust Control Design for Active Flutter Suppression

Theis

Pfifer

Seiler

2016

AIAA Atmospheric Flight Mechanics Conference

View full text Add to dashboard Cite

Flutter is an unstable oscillation caused by the interaction of aerodynamics and structural dynamics. It can lead to catastrophic failure and therefore must be strictly avoided. Weight reduction and aerodynamically efficient high aspect ratio wing design reduce structural stiffness and thus reduce flutter speed. Consequently, the use of active control systems to counter these adverse aeroservoelastic effects becomes an increasingly important aspect for future flight control systems. The paper describes the process of designing a controller for active flutter suppression on a small, flexible unmanned aircraft. It starts from a greybox model and highlights the importance of individual components such as actuators and computation devices. A systematic design procedure for an H∞-norm optimal controller that increases structural damping and suppresses flutter is then developed. A second key contribution is the development of thorough robustness tests for clearance in the absence of a high-fidelity nonlinear model.

show abstract

“…Furthermore, this approach does nothing to extend the operating envelope of the vehicle. Active control of aeroelastic instabilities has been studied for many years, and has been shown to increase flutter speed in flight tests [4]. More recently, Strganac et al [5] used a nonlinear adaptive controller to stabilize LCO in a rigid wind-tunnel wing section with nonlinear stiffness.…”

Section: Introductionmentioning

confidence: 99%

Transonic Aeroelastic Instability Suppression for a Swept Wing by Targeted Energy Transfer

Hubbard

Fontenot

McFarland

et al. 2014

Journal of Aircraft

View full text Add to dashboard Cite

Targeted energy transfer is studied as a means for suppression of transonic aeroelastic instabilities of a wind-tunnel swept wing, with a focus on designing a lightweight nonlinear energy sink that improves the critical flutter condition. The aeroelastic response modes of the wing with a nonlinear energy sink coupled to the tip are identified and tested for robustness using a medium-fidelity computational aeroelasticity model, and confirm that robust suppression of transonic aeroelastic instabilities is achievable. Accordingly, a nonlinear energy sink is designed based on a parametric study, and its transonic aeroelastic effects are studied using medium-and high-fidelity models. The results of both models indicate an improvement in stability over a broad range of conditions; the high-fidelity model predicts an approximately 40% increase in the dynamic pressure at the critical stability condition. Finally, a prototype winglet-mounted nonlinear energy sink is modeled to examine its aeroelastic effects. The results show that the nonlinear-energy-sink design is robust, but the winglet design plays a critical role that must be considered in the overall effect.

show abstract

Active Flutter Suppression-A Flight Test Demonstration

Cited by 71 publications

References 1 publication

Active Vibration Control of the Sting Used in Wind Tunnel: Comparison of Three Control Algorithms

Active Vibration Control of the Sting Used in Wind Tunnel: Comparison of Three Control Algorithms

Robust Control Design for Active Flutter Suppression

Transonic Aeroelastic Instability Suppression for a Swept Wing by Targeted Energy Transfer

Contact Info

Product

Resources

About