Effect of Fuel Sloshing in the External Tank on the Flutter of Subsonic Wings

Firouz-Abadi, R. D.; Zarifian, P.; Haddadpour, H.

doi:10.1061/(asce)as.1943-5525.0000261

Cited by 23 publications

(19 citation statements)

References 15 publications

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“…In this simplified control modeling, y matrix is basically a zero matrix with non-null elements in [1,2] and [3,5], and respectively equal to 0.05 and 1. To perform the stability and response analysis, the mass, damping and stiffness matrices in Eq.…”

Section: Implementation Of a Proportional Feedback Control Law Using mentioning

confidence: 99%

“…In particular, the effects of sloshing on aircraft aeroelastic flutter stability was considered in Refs. [5,6] where liquid dynamics were modeled by means of EMMs in Ref. [5] and frozen fluid approach in Ref.…”

Section: Introductionmentioning

confidence: 99%

“…[5,6] where liquid dynamics were modeled by means of EMMs in Ref. [5] and frozen fluid approach in Ref. [6].…”

Section: Introductionmentioning

confidence: 99%

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Investigation of Sloshing Effects on Flexible Aircraft Stability and Response

Pizzoli

2020

Aerotec. Missili Spaz.

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The present paper provides an investigation of the effects of linear slosh dynamics on aeroelastic stability and response of flying wing configuration. The proposal of this work is to use reduced order model based on the theory of the equivalent mechanical models for the description of the sloshing dynamics. This model is then introduced into an integrated modeling that accounts for both rigid and elastic behavior of flexible aircraft. The formulation also provides for fully unsteady aerodynamics modeled in the frequency domain via doublet lattice method and recast in time-domain state-space form by means of a rational function approximation. The case study consists of the so-called body freedom flutter research model equipped with a single tank, partially filled with water, located underneath the center of mass of the aircraft. The results spotlight that neglecting such sloshing effects considering the liquid as a frozen mass may overshadow possible instabilities, especially for mainly rigid-body dynamics.

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Section: Implementation Of a Proportional Feedback Control Law Using mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Investigation of Sloshing Effects on Flexible Aircraft Stability and Response

Pizzoli

2020

Aerotec. Missili Spaz.

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“…The influence of sloshing of an internal fluid on the flutter boundary of an aeroelastic system has received scarce attention in the research literature. Firouz‐Abadi et al applied the simplest model for representing the liquid sloshing called the equivalent mechanical system in order to investigate the effect of fuel sloshing on the flutter boundary of a wing‐store configuration in the subsonic regime. Farhat et al addressed the sloshing effects of an internal fluid on the flutter boundary of a wing‐store configuration in subsonic, transonic, and supersonic regimes.…”

Section: Introductionmentioning

confidence: 99%

Sloshing effects on supersonic flutter characteristics of a circular cylindrical shell partially filled with liquid

Zarifian

Ovesy

Firouz-Abadi

2018

Numerical Meth Engineering

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Summary This paper aims to revisit the effect of sloshing on the flutter characteristics of a partially liquid‐filled cylinder. A computational fluid‐structure interaction model within the framework of the finite element method is developed to capture fluid‐structure interactions arising from the sloshing of the internal fluid and the flexibility of its containing structure exposed to an external supersonic airflow. The internal liquid sloshing is represented by a more sophisticated model, referred to as the liquid sloshing model, and the shell structure is modeled by Sanders' shell theory. The aerodynamic pressure loading is approximated by the first‐order piston theory. The initial geometric stiffness due to prestresses in the initial configuration stemming from the fluid hydrostatic pressure, internal pressure, and axial compression load is also considered. The obtained results reveal that the sloshing of the internal fluid has little influence on the supersonic flutter boundary of a cylinder partially filled with liquid, at least for the case considered here. It is also shown that the critical freestream static pressure predicted by the sloshing model is negligibly larger than that calculated by the hydroelastic model of the internal fluid, which means that the sloshing of the internal fluid slightly overestimates the flutter boundary.

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“…Shams et al [11] analyzed the nonlinear aeroelastic of slender wings using a nonlinear structural model coupled with the linear unsteady aerodynamic model. Firouzabadi et al [12] studied the aeroelastic instability of a subsonic wing with an external fuel tank store containing sloshing fuel.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of linear and nonlinear aeroelastic behavior of a cropped delta wing with store in low subsonic flow

Golparvar

Irani

Sani

2015

J Braz. Soc. Mech. Sci. Eng.

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Wing root and tip chord, respectively t w Wing plate thickness kn Numbers of vortex elements on wing in y direction kmm The total number of vortices on both the wing and wake l Wing span m w Wing mass per unit length M s Store mass t Time P Dimensionless aerodynamic pressure q,q State-space vector of structural deformation F a Generalized aerodynamic force vector J Jacobian matrix J 1 , J 2 , J 3 Store aerodynamic parameters U f Dimensionless flutter speed (U f /lw 02) U ∞ Free stream airspeed ρ ∞ Density of air λ Wing taper ratio (c t /c r) Λ Sweep angle of wing AR Aspect ratio of wing Γ Vortex strength x s , y s , z s Position of center of gravity of store x p The distance from the nose to pivot point of store c b Chord of slender bodȳ x s Dimensionless center of gravity of store in x Abstract The present paper aims to investigate flutter phenomenon for cropped delta wing with an external store using numerical and experimental methods in a subsonic and incompressible flight regime. Wing structure is modeled based on von Kármán plate theory. The unsteady vortex lattice method is applied to wing aerodynamic model and a slender-body theory is used for store aerodynamic model. The experimental tests have been conducted in an incompressible subsonic wind tunnel. The comparison indicates a satisfactory agreement between the experimental results and the theoretical analyses. Moreover, the effects of different parameters such as wing thickness, wing aspect ratio, spanwise store position, store mass, the aerodynamics of the store, underwing clearance and store center of gravity on both flutter speed and instability boundary of the wing are studied both analytically and experimentally. Also, the system behaviors and the oscillation amplitude are examined experimentally for post-flutter where time history simulation and phase portrait are obtained for various velocities. The FFT analysis of time history measured data shows that beside the dominant harmonic frequency, both superharmonic and subharmonic frequencies are clearly identifiable. The results obtained from experimental bifurcation diagram indicate the presence of hysteresis loop regions corresponding to the stable LCOs.

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Effect of Fuel Sloshing in the External Tank on the Flutter of Subsonic Wings

Cited by 23 publications

References 15 publications

Investigation of Sloshing Effects on Flexible Aircraft Stability and Response

Investigation of Sloshing Effects on Flexible Aircraft Stability and Response

Sloshing effects on supersonic flutter characteristics of a circular cylindrical shell partially filled with liquid

Experimental investigation of linear and nonlinear aeroelastic behavior of a cropped delta wing with store in low subsonic flow

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