The organization of behavior: A neuropsychological theory

Aircraft wings are a compromise that allows the aircraft to fly at a range of flight conditions, but the performance at each condition is sub-optimal. The ability of a wing surface to change its geometry during flight has interested researchers and designers over the years as this reduces the design compromises required. Morphing is the short form for metamorphose; however, there is neither an exact definition nor an agreement between the researchers about the type or the extent of the geometrical changes necessary to qualify an aircraft for the title ‘shape morphing.’ Geometrical parameters that can be affected by morphing solutions can be categorized into: planform alteration (span, sweep, and chord), out-of-plane transformation (twist, dihedral/gull, and span-wise bending), and airfoil adjustment (camber and thickness). Changing the wing shape or geometry is not new. Historically, morphing solutions always led to penalties in terms of cost, complexity, or weight, although in certain circumstances, thes...

A Review of Morphing Aircraft

Dynamic fracture mechanics

Probability, Reliability and Statistical Methods in Engineering Design

Past, present and future of nonlinear system identification in structural dynamics

The free vibration of curvilinearly stiffened cylindrical shells is studied by using the finite element method. The first order shear deformation theory (FSDT) is employed for both the shell and the Timoshenko beam modeling. The stiffener is assumed to be perpendicular to the shell. A local coordinate system consisting with the tangential, geodesic and normal directions is introduced to model the stiffener. Interpolation functions are used to build the displacement mapping between the stiffener and the shell nodes to allow the stiffener to be placed anywhere within the shell. Numerical examples shows that the present FE method can obtain precise enough results with a lesser number of elements as compared to the commercial software Nastran.

Free Vibration Analysis of Curvilinearly Stiffened Cylindrical Shells

Damage Identification of Plate Structures Using a Hybrid Genetic-Sensitivity Approach

Elastic Axis Determination and Extraction of Vibration Mode Shapes of a Light Weight Composite Aircraft

Concluding Remarks The results obtained with the calibration tests of the pitch/ yaw and roll mechanism (related to the SDM) were in good accordance with the data published by NAE (IAR), DFVLR (DLR), and FFA, taking into account the different characteristics of the wind tunnels and of the model suspensions. As a consequence, the research program has been extended to different model configurations, developed with the aim of investigating their aerodynamic behavior in a wide maneuvering field.

Shape sensitivities and approximations of modal response of laminated skew plates

The time finite element method (TFM) is employed for parametric identification of nonlinear structural dynamic systems. An advantage of TFM is the ease with which one can calculate the sensitivity of the transient response with respect to various design parameters, a key requirement for gradient-based parameter identification schemes. The method is simple, because one obtains the sensitivities of the response to system parameters by differentiating the algebraic equations, not original differential equations. These sensitivities are used in the Levenberg-Marquardt iterative direct method to identify parameters for nonlinear single- and two-degree-of-freedom systems. The measured response was simulated by integrating the example nonlinear systems using the given values of the system parameters. The accuracy and the efficiency of the present method are compared to a previously available approach that employs a multistep method to integrate nonlinear differential equations. It is seen, for the same accuracy, that the present approach requires fewer data points.

Parametric identification of nonlinear structural dynamic systems using time finite element method

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