Structural health monitoring using genetic fuzzy systems pawar prashant m ganguli ranjan
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The simulated measurements are obtained using an aeroelastic analysis of the composite rotor blade based on the finite element in space and time with physics-based damage modes that are then linked to the life consumption of the blade. Active vibration reduction in the modern helicopters is influenced by various properties of composite rotor blades. Most of the bending stiffness loss is observed in the fiber breakage damage mode. Renowned for their scope, range and authority, the new editions have been significantly developed in terms of both contents and scope. Due to surface features, minimum film height is developed which helps to increase pressure as well as load-carrying capacity. Helicopter rotor blades are made of fiber-reinforced composite materials that are prone to matrix cracking. A dragonfly inspired flapping wing is investigated in this paper.

Phenomenological models of material degradation for homogenous and composite materials are used. A finite element model is used to obtain the mode shapes of a damaged fixedâ€”fixed beam, and the damaged mode shapes are expanded using a spatial Fourier series and the effect of damage on the harmonics is investigated. The fuzzy logic approach is thus able to extract maximum information from very limited and uncertain data. The approach is from a modern perspectiveâ€”it dwells on surrogate modelling and non-gradient-based algorithms and at the same time emphasizes classical methods for pedagogical reasons. This approach of manufacturing photos results in increment in quality as well as profit of artisan. Various rotor configurations with different elastic couplings with appropriate actuator placement are used to investigate the hub vibration characteristics.

Widely used for power generation, gas turbine engines are susceptible to faults due to the harsh working environment. The propagation of uncertainties is also demonstrated in the estimation of structural responses of composite beams. Numerical studies show that damage detection using Fourier coefficients and neural networks has the capability to detect the location and damage size accurately. Numerical simulations are conducted to evaluate the performance of proposed micromixers by solving the Navierâ€”Stokes equation and convectionâ€”diffusion equation. The effects of matrix cracking are introduced through the changes in the extension, extension-bending and bending matrices of composites, whereas the effect of uncertainties are introduced through the stochastic properties obtained from previous experimental and analytical studies. The nonlinear governing equations of motion of the smart flapping wing are obtained using the Hamilton's principle. Each method is demonstrated through numerical simulations that can be easily performed by the reader.

It provides a thorough understanding of the concepts of optimization necessary for a robust design of technical systems. Thin walled composite beam structures are prone to damage which results in change in the performance of these structures. The selection of a starting population and a mating pool is explained. It will also be useful for computer scientists and applied mathematicians interested in the application of genetic fuzzy systems to engineering problems. The genetic operators of crossover and mutation are illustrated with examples. The material and fabrication uncertainties are introduced using Monte Carlo simulation using the stochastic properties obtained from previous experimental work.

The model-based measurements are contaminated with noise to simulate real data. Using these change in frequencies due to matrix cracking, a genetic fuzzy system for crack density and crack location detection is generated. His papers have been cited over 1500 times in Scopus and his h-index is 23, which are exceptional numbers in aerospace. Current ideas, requirements, and approaches are explored from the perspective of major large airframe manufacturers and aircraft subsystem manufacturers. An aeroelastic analysis of the helicopter rotor based on finite elements in space and time is used to study the effects of key damage modes in a composite rotor in forward flight. On the other hand, technologies proposed by expert researchers may find applications in different regions. Research on the modelling of typical rotor system faults using aeroelastic analysis is discussed and the use of damage detection algo- rithms based on neural network, fuzzy logic, and system identification is pointed out.

Using rotating frequencies lowers the success rate for small damage because the centrifugal stiffening caused by rotation counters the stiffness reduction caused by structural damage. Numerical results showing the effects of material and geometric uncertainties on the aeroelastic response and hub vibration behavior of composite rotor blades are illustrated and important conclusions are drawn based on the observations. The measurements used for health monitoring are the first four flap transverse bending frequencies of the rotor blade. Numerical results show that a notable vibration reduction can be achieved for all the combinations of composite rotor blades. He is an Associate Fellow of the American Institute of Aeronautics and Astronautics. Current paper is an attempt to make this process simple and easy for working with or without electricity.

A newly developed single crystal piezoceramic material is introduced as an actuator material in order to exploit its relatively high shear actuation authority. The efficiency and fault tolerance of biogas plant depends on the proper mixing of the sludge in the digester. Governing equations of composite rotor blades with surface bounded piezoceramic actuators are obtained using Hamilton's principle. The damaged helicopter rotor is modeled using a finite element simulation which solves the rotor blade equations and vehicle trim equations. The numerical attempts are made using Taguchi's orthogonal array L27.

The design optimization problem is formulated to maximize the surface and domain velocities in the digester by varying the geometries and locations of flaps. Typically, the measured data is contaminated with noise and the number of measurements is also often few. . Experiments are performed to validate simulation results in terms of flow rate versus frequency and flow rate versus back pressure. It is observed that the success rate of the genetic fuzzy system in the presence of noise is dependent on crack density level of damage , number of 90 plies, angle of constraining layer , and noise level. The genetic fuzzy system combines the uncertainty representation characteristics of fuzzy logic with the learning ability of genetic algorithm.

The predictions of the numerical simulations concerning flow rate versus diffuser length, neck width, a height of chamber and diameter of the chamber, etc. Maximum decrease in frictional power loss and frictional torque is observed for partially grooving along 90Â°-360Â° region. Finally, work on the health monitoring of composite helicopter rotors is discussed and inverse problem solution and life prediction issues are addressed. The effect of matrix cracks is included in an analytical model of composite box-beam. To enable this experience, the book has several solved examples, some of them non-trivial, besides many unsolved problems for the student to work out.