A doublet-lattice method for calculating lift distributions on oscillating surfaces in subsonic flows.

Albano, E. D.; Rodden, William P.

doi:10.2514/3.5086

Cited by 786 publications

(243 citation statements)

References 3 publications

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“…The modal parameters, such as generalized mass, natural frequencies, and mode shapes, of the wing were obtained from the MSC Nastran result file through direct data abstraction. The aerodynamic influence coefficient matrix [7], the surface spline interpolation [8], and the flutter analysis were computed in a flutter analysis/ aeroservoelastic analysis package written in C++ in Microsoft Visual Studio 2008. The linear algebra computation was completed by using the IT++ software package.…”

Section: Illustrative Examplementioning

confidence: 99%

Flutter Analysis: Using Piecewise Quadratic Interpolation with Mode Tracking and Wind-Tunnel Tests

Huang

Qian

Zhao

et al. 2010

Journal of Aircraft

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= reference length of half-chord b j = breakpoint of the jth segment c 0 , c 1 , c 2 , c 3 , c 4 = coefficients of interpolation polynomial D = generalized damping matrix fV = cubic spline function of flow velocity f i = frequency corresponding to the flow velocity at the ith step g = added structural damping for k method Im = imaginary part of complex number j = sequence number of segment K = generalized stiffness matrix k = reduced frequency k j = the jth reduced frequency in which the generalized aerodynamic matrix is computed M = Mach number M = generalized mass matrix n = number of reduced frequencies for computing aerodynamic influence matrices n a = number of frequency data in a set p = Laplace variable Q s p = rational function approximation for generalized aerodynamic matrix Q 0 j , Q 1 j , Q 2 j = complex-valued coefficient matrices of the jth segment q = vector of generalized coordinates V = flow velocity V i = flow velocity at the ith step = flow density

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Section: Illustrative Examplementioning

confidence: 99%

Flutter Analysis: Using Piecewise Quadratic Interpolation with Mode Tracking and Wind-Tunnel Tests

Huang

Qian

Zhao

et al. 2010

Journal of Aircraft

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“…The doublet lattice-based [35] aerodynamic mesh, shown in Fig. 1b, is composed of 1000 panels, with 764 on the wing, 180 on the horizontal tail and 66 on the vertical tail.…”

Section: A Structural and Aerodynamic Modelsmentioning

confidence: 99%

Gust Load Alleviation for a Regional Aircraft Through a Static Output Feedback

Fonte

Ricci

Mantegazza

2015

Journal of Aircraft

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The paper presents the design of a symmetric, active, gust load alleviation system for a regional transport aircraft, based on a static output feedback with a constrained structure. The design is carried out on a comprehensive finite state aeroservoelastic model, including sensor units and actuator transfer functions, and verified by taking into account saturated control positions, rates, and hinge moments. The controller is designed within a quadratic optimal framework, through a second-order Hessian-based optimization algorithm, exploiting block diagonal Schur transformations of the closed-loop state equations and performance weightings. An accurately chosen worst discrete gust and a reference flight condition provide a baseline design, which is significantly effective in alleviating continuous turbulence loads. Such a reference design proves itself robust enough to alleviate atmospheric loads over the complete flight envelope and is eventually further improved and robustified through a simple bilinear q∞−M∞ algebraic scheduling

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“…The Doublet-Lattice Method [1], in particular, has long been the fundamental tool of the aeroelastic community, and has provided a robust approach for non-stationary aerodynamic prediction, although simpler approaches based on strip theory and indicial functions are still used at the conceptual level [2]. However, the applicability of the existing design tools is being stretched as novel concepts are developed and conventional vehicles see their wing stiffness substantially reduced.…”

Section: Introductionmentioning

confidence: 99%

“…Albano and Rodden [1] extended the VLM to harmonically oscillating surfaces for an assumed flat wake. Replacing the vortex sheet by one of (equivalent) oscillating doublets, the Doublet-Lattice Method (DLM) was obtained.…”

mentioning

confidence: 99%

Applications of the unsteady vortex-lattice method in aircraft aeroelasticity and flight dynamics

Murua

Palacios

Graham

2012

Progress in Aerospace Sciences

234

181

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A doublet-lattice method for calculating lift distributions on oscillating surfaces in subsonic flows.

Cited by 786 publications

References 3 publications

Flutter Analysis: Using Piecewise Quadratic Interpolation with Mode Tracking and Wind-Tunnel Tests

Flutter Analysis: Using Piecewise Quadratic Interpolation with Mode Tracking and Wind-Tunnel Tests

Gust Load Alleviation for a Regional Aircraft Through a Static Output Feedback

Applications of the unsteady vortex-lattice method in aircraft aeroelasticity and flight dynamics

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