Measurement and Modeling of Aeroelastic Response under Gust

Babbar, Yogesh; Suryakumar, Vishvas S.; Strganac, Thomas W.; Mangalam, Arun S.

doi:10.2514/6.2015-2724

Cited by 9 publications

(5 citation statements)

References 5 publications

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“…8(a). This design was later improved by Matsuzaki et al (50) , Reed (51) , Tang et al (52)(53)(54)(55) , Ricci and Scotti (56) , Neumann et al (57) , Babbar (58,59) , etc., for flutter and gust analyses, as shown in Fig. 8(b).…”

Section: Wind Tunnelmentioning

confidence: 99%

Gust loads on aircraft

Cao

Ismail

2019

Aeronaut. j.

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An important prerequisite for the design, assessment and certification of aircraft and their associated control systems is a quantitative specification of the environment in which the aircraft is intended to operate, for example, atmospheric gust. Gust loads on aircraft may induce detrimental influences such as increased aerodynamic and structural loads, structural deformation and decreased flight dynamic performance. This paper presents a systematic and comprehensive overview of important concepts and applications of gust loads on aircraft. This overview includes a brief research background, concepts, research techniques, influences and load alleviation measures of gust. Finally, we summarise some potential improvements in the future work. It is also recommended to learn from previous experiences to avoid aviation accidents due to flight through atmospheric gusts and turbulence.

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Section: Wind Tunnelmentioning

confidence: 99%

Gust loads on aircraft

Cao

Ismail

2019

Aeronaut. j.

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“…A slender plate with length 2b and width l is placed in an axial compressible flow with a free stream velocity U in the length direction of the plate (see figure (1)). If the plate leading edge is free and the trailing edge is pinned (no reaction moment), then we call that configuration freepinned (see figure (2)). On the other hand, if the leading edge is free and the trailing edge is clamped (there is a reaction moment), then we call that configuration free-clamped (see figure (3)).…”

Section: Problem Descriptionmentioning

confidence: 99%

“…A very important example illustrating the effectiveness of analytical techniques in aeroelasticity is the outstanding work of Theodorsen in the 1950's [22] who used tools from complex analysis to derive formulas of the aerodynamic loads on thin airfoils in incompressible airflow. Until now, a significant number of scientists after Theodorsen have been using his formulas to study different aeroelastic problems (see for example [17,13,21,2]).…”

Section: Introductionmentioning

confidence: 99%

Static stability analysis of a thin plate with a fixed trailing edge in axial subsonic flow: Possio integral equation approach

Serry¹,

Tuffaha²

2018

Applied Mathematical Modelling

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In this work, the static stability of plates with fixed trailing edges in axial airflow is studied using the framework of Possio integral equation. First, we introduce a new derivation of a Possio integral equation that relates the pressure jump along thin plates to their downwash based on the linearization of the governing equations of an ideal compressible fluid. The steady state solution to the Possio equation is used to account for the aerodynamic forces in the steady state plate governing equation resulting in a singular differential-integral equation which is transformed to an integral equation. Next, we verify the solvability of the integral equation based on the Fredholm alternative for compact operators in Banach spaces and the contraction mapping theorem. Then, we derive explicit formulas for the characteristic equations of free-clamped and free-pinned plates. The minimum solutions to the characteristic equations are the divergence speeds which indicate when static instabilities start to occur. We show analytically that free-pinned plates are statically unstable. After that, we move to derive analytically flow speed intervals that correspond to static stability regions for free-clamped plates. We also resort to numerical computations to obtain an explicit formula for the divergence speed of free-clamped plates. Finally, we apply the obtained results on piezoelectric plates and we show that free-clamped piezoelectric plates are statically more stable than conventional free-clamped plates due to the piezoelectric coupling. arXiv:1708.06956v1 [physics.flu-dyn]

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“…17, a control approach based on aerodynamic load feedback using the trailing edge control surface was successfully tested for the suppression of Limit Cycle Oscillations (LCOs) and gust load alleviation. The controller was implemented on the Nonlinear Aeroelastic Test Apparatus (NATA) [18]. Loads were estimated from the LESP using a low-order analytical model [16].…”

Section: Introductionmentioning

confidence: 99%

A Load-Based Feedback Approach for Distributed Aeroservoelastic Control

Suryakumar

Mangalam

Babbar

et al. 2016

AIAA Atmospheric Flight Mechanics Conference

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An approach to aeroservoelastic control for flexible flight vehicles using the Fly-ByFeel (FBF) sensing concept is introduced. An essential feature of this sensing paradigm is the real-time measurement of circulation. Recent experiments have shown that sectional unsteady aerodynamic loads may be accurately estimated using the leading-edge stagnation point (LESP). Experimental demonstrations have also shown the use of this sensing concept for flutter suppression and gust load alleviation using a low-order energy-based approach. This work extends the sectional control formulation to flying wing configurations. Control objectives include suppressing Body-Freedom-Flutter phenomena. Aeroservoelastic control for this case may be accomplished using a spanwise-distributed, co-located sensing and controls architecture. Using load-based feedback, low-order control structures are shown to be effective for flutter suppression. Controller performance comparisons with conventional high-order state-feedback methods are investigated.

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Measurement and Modeling of Aeroelastic Response under Gust

Cited by 9 publications

References 5 publications

Gust loads on aircraft

Gust loads on aircraft

Static stability analysis of a thin plate with a fixed trailing edge in axial subsonic flow: Possio integral equation approach

A Load-Based Feedback Approach for Distributed Aeroservoelastic Control

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