Vibration of anti‐symmetric angle‐ply composite plates under random excitation

Doğan, Vedat

doi:10.1108/00022660710780605

Cited by 5 publications

(4 citation statements)

References 15 publications

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“…Moreover, is more difficult to move the complete blade in a higher harmonic motion compared to moving one or two trailing edge flaps placed on the rotor blade. Thakkar and Ganguli (2004, 2006a, 2007 studied the possibility of using shear mode of the piezoelectric materials for twisting a rotor blade modeled as a rectangular section beam and a box beam. They used the fact that the shear strain coefficient of piezoelectric materials is much higher than the direct strain coefficient and therefore can lead to higher actuation authority.…”

Section: Smart Helicopter Rotormentioning

confidence: 99%

“…Composite materials have a high level of scatter with a coefficient of variance ranging from 5 to 12 percent for the Young's modulus, Poisson ratios and shear modulus. Monte‐Carlo simulations were used for these numerical results (Dogan, 2007). Figures 16 and 17 show the dispersion in flap and torsion tip response around the rotor disk, respectively.…”

Section: Helicopter Dynamicsmentioning

confidence: 99%

See 1 more Smart Citation

Rotorcraft research in India: recent developments

Ganguli

2010

Aircraft Eng & Aerospace Tech

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If you would like to write for this, or any other Emerald publication, then please use our Emerald for Authors service information about how to choose which publication to write for and submission guidelines are available for all. Please visit www.emeraldinsight.com/authors for more information. About Emerald www.emeraldinsight.comEmerald is a global publisher linking research and practice to the benefit of society. The company manages a portfolio of more than 290 journals and over 2,350 books and book series volumes, as well as providing an extensive range of online products and additional customer resources and services.Emerald is both COUNTER 4 and TRANSFER compliant. The organization is a partner of the Committee on Publication Ethics (COPE) and also works with Portico and the LOCKSS initiative for digital archive preservation. AbstractPurpose -The purpose of this paper is to discuss published research in rotorcraft which has taken place in India during the last ten years. The helicopter research is divided into the following parts: health monitoring, smart rotor, design optimization, control, helicopter rotor dynamics, active control of structural response (ACSR) and helicopter design and development. Aspects of health monitoring and smart rotor are discussed in detail. Further work needed and areas for international collaboration are pointed out. Design/methodology/approach -The archival journal papers on helicopter engineering published from India are obtained from databases and are studied and discussed. The contribution of the basic research to the state-of-the-art in helicopter engineering science is brought out. Findings -It is found that strong research capabilities have developed in rotor system health and usage monitoring, rotor blade design optimization, ACSR, composite rotor blades and smart rotor development. Furthermore, rotorcraft modeling and analysis aspects are highly developed with considerable manpower available and being generated in these areas. Practical implications -Two helicopter projects leading to the "advanced light helicopter" and "light combat helicopter" have been completed by Hindustan Aeronautics Ltd These helicopter programs have benefited from the basic research and also provide platforms for further basic research and deeper industry academic collaborations. The development of well-trained helicopter engineers is also attractive for international helicopter design and manufacturing companies. The basic research done needs to be further developed for practical and commercial applications. Originality/value -This is the first comprehensive research on rotorcraft research in India, an important emerging market, manufacturing and sourcing destination for the industry.

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Section: Smart Helicopter Rotormentioning

confidence: 99%

Section: Helicopter Dynamicsmentioning

confidence: 99%

Rotorcraft research in India: recent developments

Ganguli

2010

Aircraft Eng & Aerospace Tech

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“…Vibration and stability behaviour of cross-ply and angle-ply laminated shells are analysed using power series expansion (Matsunaga, 2007a(Matsunaga, , 2007b method. Vibration behaviour of anti-symmetric angle-ply laminated plate is analysed (Dogan, 2007) under random excitation in the framework of FSDT type plate kinematics. Buckling behaviour of imperfect laminated plate is obtained (Shen, 1997) based on HSDT mid-plane kinematics.…”

Section: Introductionmentioning

confidence: 99%

Thermal buckling and vibration analysis of laminated composite curved shell panel

Katariya

Panda

2016

Aircraft Eng & Aerospace Tech

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Purpose -The purpose of this paper is to develop a general mathematical model for laminated curved structure of different geometries using higher-order shear deformation theory to evaluate in-plane and out of plane shear stress and strains correctly. Subsequently, the model has to be validated by comparing the responses with developed simulation model (ANSYS) as well as available published literature. It is also proposed to analyse thermal buckling load parameter of laminated structures using Green-Lagrange type non-linear strains for excess thermal distortion under uniform temperature loading. Design/methodology/approach -Laminated structures known for their flexibility as compared to conventional material and the deformation behaviour are greatly affected due to combined thermal/aerodynamic environment. The vibration/buckling behaviour of shell structures are very different than that of the plate structures due to their curvature effect. To model the exact behaviour of laminated structures mathematically, a general mathematical model is developed for laminated shell geometries. The responses are evaluated numerically using a finite element model-based computer code developed in MATLAB environment. Subsequently, a simulation model has been developed in ANSYS using ANSYS parametric design language code to evaluate the responses. Findings -Vibration and thermal buckling responses of laminated composite curved panels have been obtained based on proposed model through a customised computer code in MATLAB environment and ANSYS simulation model using ANSYS parametric design language code. The convergence behaviour are tested and compared with those available in published literature and ANSYS results. Finally, the investigation has been extended to examine the effect of different parameters (thickness ratios, curvature ratios, modular ratios, number of layers and support conditions) on the free vibration and thermal buckling responses of laminated curved structures. Practical implications -The present paper intends to give sufficient amount of numerical experimentation, which may lead to help in designing of finished product made up of laminated composites. Most of the aerospace, space research and defence organisation intend to develop low cost and high durable products for real hazard conditions by taking combined loading and environmental conditions. Further, case studies might lead to a lighter design of the laminated composite panels used in high-performance systems, where the weight reduction is the major parameter, such as aerospace, space craft and missile structures. Originality/value -In this analysis, the geometrical distortion due to temperature is being introduced through Green-Lagrange sense in the framework of higher-order shear deformation theory for different types of laminated shells (cylindrical/spherical/hyperboloid/elliptical). A simulation-based model is developed using ANSYS parametric design language in ANSYS environment for different geometries and loading condition and compared with the numeri...

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“…Extending the search towards the application of SS and MCS in AMRO work shows equally scant results. Most MCS applications are based around the design and test of aircraft components and systems as outlined by Dogan (2007) on Direct Simulation MC methods, whilst Mathaisel (2005), proposes the development of a Lean architecture for transforming AMRO facilities without applying any statistical-based analysis techniques.…”

Section: Introductionmentioning

confidence: 99%

Reducing turn-round variability through the application of Six Sigma in aerospace MRO facilities

Thomas

Mason‐Jones

Davies³

et al. 2015

Journal of Manufacturing Technology Management

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If you would like to write for this, or any other Emerald publication, then please use our Emerald for Authors service information about how to choose which publication to write for and submission guidelines are available for all. Please visit www.emeraldinsight.com/authors for more information. About Emerald www.emeraldinsight.comEmerald is a global publisher linking research and practice to the benefit of society. The company manages a portfolio of more than 290 journals and over 2,350 books and book series volumes, as well as providing an extensive range of online products and additional customer resources and services.Emerald is both COUNTER 4 and TRANSFER compliant. The organization is a partner of the Committee on Publication Ethics (COPE) and also works with Portico and the LOCKSS initiative for digital archive preservation. AbstractPurpose -The purpose of this paper is to outline the application of a Six Sigma (SS) methodology as a means of reducing supply chain risk in aerospace maintenance repair and overhaul (MRO) functions. In this contribution the LSS method is used to estimate the economic impact on the selection of the most appropriate maintenance strategy pertaining to aircraft display units (DUs) as well as providing a reduction in turn round time (TRT) variation of the DUs. Design/methodology/approach -The paper develops a SS approach which includes the development of the Monte Carlo technique as a mechanism to identify the most cost effective MRO strategy whilst simultaneously reducing variability in TRT servicing of the DUs. This application enabled the authors to obtain further proof of concept and also to apply a number of focused quality improvement techniques to systematically reduce TRT variation. Findings -An effective development of the SS approach is proposed and the effectiveness of the method is subsequently evaluated highlighting the benefits to the host organisation. The SS methodology demonstrates that it is possible to identify the most cost effective MRO strategy and thus suggests a suitable DU replacement policy which in turn allows engineers to develop the appropriate maintenance schedules for the company. Practical implications -The design, development and implementation of this SS methodology offers an approach to achieving a more cost effective MRO strategy whilst reducing TRT variability which can lead to greater predictability of operations which in turn enables the company to effectively synchronise supply with demand. The paper offers practicing maintenance managers and engineers a practical example for increasing productive efficiency and output. Originality/value -This SS strategy contributes to the existing knowledge base on maintenance systems and subsequently disseminates this information in order to provide impetus, guidance and support towards increasing the development companies in an attempt to move the UK manufacturing sector towards world class manufacturing performance.

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Vibration of anti‐symmetric angle‐ply composite plates under random excitation

Cited by 5 publications

References 15 publications

Rotorcraft research in India: recent developments

Rotorcraft research in India: recent developments

Thermal buckling and vibration analysis of laminated composite curved shell panel

Reducing turn-round variability through the application of Six Sigma in aerospace MRO facilities

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