The kinematics of the rigid feedback linkage, the impedance of the hydraulic servomechanism and the flutter occurrence

Ursu, Ioan; Carafoli, Elie

doi:10.13111/2066-8201.2012.4.3.6

Cited by 4 publications

(2 citation statements)

References 4 publications

(2 reference statements)

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“…The model proposed (figure 7b) achieves the control after three state variables (incident angles, twist a top wing and aerial speed vector) involving superior dynamic characteristics and performances [9], [10], [11]. To avoid the separated treatment of the differential elements H 2 (D) from (8) …”

Section: Incas Bulletin Volume 5 Issue 2/ 2013mentioning

confidence: 99%

The analysis of the flying wing in morphing concept

Prisacariu¹,

Universitatii²

2013

INCAS BULLETIN

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Section: Incas Bulletin Volume 5 Issue 2/ 2013mentioning

confidence: 99%

The analysis of the flying wing in morphing concept

Prisacariu¹,

Universitatii²

2013

INCAS BULLETIN

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“…The authors would like to mention, based on their own experience in the field, the risk of triggering the flutter if the impedance (also called dynamic stiffness) of the hydraulic servomechanism in the flight control chain has negative damping [16][17][18][19]. On 24 November 1977, an IAR 93 Eagle aircraft crashed due to tail flutter (see [20]).…”

Section: Introduction 1directions For Aircraft Wing Vibrations Attenu...mentioning

confidence: 99%

A Smart Wing Model: From Design to Testing in a Wind Tunnel with a Turbulence Generator

Ursu,

Tecuceanu,

Enciu

et al. 2024

Aerospace

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The paper concerns the technology of the design, realization, and testing of a flexible smart wing in a wind tunnel equipped with a turbulence generator. The system of smart wing, described in detail, consists mainly of: a physical model of the wing with an aileron; an electric servomotor of broadband with a connecting rod-crank mechanism for converting the rectilinear motion of the servoactuator into the aileron deflection; two transducers: an encoder for measuring the deflection of the control aileron and an accelerometer mounted on the wing to measure its bending and torsional vibrations; a procedure for determining the mathematical model of the wing by experimental identification; a turbulence generator in the wind tunnel; implemented ℋ∞ and LQG algorithms for active control of vibrations. The attenuation experimentally obtained for the aeroelastic vibrations of the wing, but also for those accentuated by the turbulence, reaches values of up to 50%.

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Active robust control for wing vibrations attenuation

et al. 2022

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In this paper a flexible smart wing is presented. The aileron wing with aileron was tested in the INCAS Subsonic Wind Tunnel with the aim of flutter mitigation and vibrations attenuation. The work takes over some of the results of the active anti-flutter control tests performed in the wind tunnel based on the receptance method. More specifically, the mathematical models in the time domain, necessary for the synthesis of control laws, are obtained from experimentally identified transfer functions. The main part of the paper presents the synthesis and analysis of the robustness of the control laws LQG, LQG/LTR, 𝐻𝐻∞ standard and 𝐻𝐻∞ robust from which the optimal solution will be chosen in a later work for the active vibration control tests on this smart wing model.

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The kinematics of the rigid feedback linkage, the impedance of the hydraulic servomechanism and the flutter occurrence

Cited by 4 publications

References 4 publications

The analysis of the flying wing in morphing concept

The analysis of the flying wing in morphing concept

A Smart Wing Model: From Design to Testing in a Wind Tunnel with a Turbulence Generator

Active robust control for wing vibrations attenuation

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