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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Advances in aircraft and spacecraft science
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Volume 3, Issue 3 - Jul 2016
Volume 3, Issue 2 - Apr 2016
Volume 3, Issue 1 - Jan 2016
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Cylindrical bending of multilayered composite laminates and sandwiches
Sayyad, Atteshamuddin S. ; Ghugal, Yuwaraj M. ;
Advances in aircraft and spacecraft science, volume 3, issue 2, 2016, Pages 113~148
DOI : 10.12989/aas.2016.3.2.113
In a whole variety of higher order plate theories existing in the literature no consideration is given to the transverse normal strain / deformation effects on flexural response when these higher order theories are applied to shear flexible composite plates in view of minimizing the number of unknown variables. The objective of this study is to carry out cylindrical bending of simply supported laminated composite and sandwich plates using sinusoidal shear and normal deformation plate theory. The most important feature of the present theory is that it includes the effects of transverse normal strain/deformation. The displacement field of the presented theory is built upon classical plate theory and uses sine and cosine functions in terms of thickness coordinate to include the effects of shear deformation and transverse normal strain. The theory accounts for realistic variation of the transverse shear stress through the thickness and satisfies the shear stress free conditions at the top and bottom surfaces of the plate without using the problem dependent shear correction factor. Governing equations and boundary conditions of the theory are obtained using the principle of minimum potential energy. The accuracy of the proposed theory is examined for several configurations of laminates under various static loadings. Some problems are presented for the first time in this paper which can become the base for future research. For the comparison purpose, the numerical results are also generated by using higher order shear deformation theory of Reddy, first-order shear deformation plate theory of Mindlin and classical plate theory. The numerical results show that the present theory provides displacements and stresses very accurately as compared to those obtained by using other theories.
Turbomachinery design by a swarm-based optimization method coupled with a CFD solver
Ampellio, Enrico ; Bertini, Francesco ; Ferrero, Andrea ; Larocca, Francesco ; Vassio, Luca ;
Advances in aircraft and spacecraft science, volume 3, issue 2, 2016, Pages 149~170
DOI : 10.12989/aas.2016.3.2.149
Multi-Disciplinary Optimization (MDO) is widely used to handle the advanced design in several engineering applications. Such applications are commonly simulation-based, in order to capture the physics of the phenomena under study. This framework demands fast optimization algorithms as well as trustworthy numerical analyses, and a synergic integration between the two is required to obtain an efficient design process. In order to meet these needs, an adaptive Computational Fluid Dynamics (CFD) solver and a fast optimization algorithm have been developed and combined by the authors. The CFD solver is based on a high-order discontinuous Galerkin discretization while the optimization algorithm is a high-performance version of the Artificial Bee Colony method. In this work, they are used to address a typical aero-mechanical problem encountered in turbomachinery design. Interesting achievements in the considered test case are illustrated, highlighting the potential applicability of the proposed approach to other engineering problems.
Thermo-oxidation behaviour of organic matrix composite materials at high temperatures
Cinquin, Jacques ; Colin, Xavier ; Fayolle, Bruno ; Mille, Marion ; Terekhina, Svetlana ; Chocinski-Arnault, Laurence ; Gigliotti, Marco ; Grandidier, Jean-Claude ; Lafarie-Frenot, Marie-Christine ; Minervino, Matteo ; Cluzel, Christophe ; Daghia, Federica ; Ladeveze, Pierre ; Zhang, Fangzouh ;
Advances in aircraft and spacecraft science, volume 3, issue 2, 2016, Pages 171~195
DOI : 10.12989/aas.2016.3.2.171
The present paper is a review of the main activities carried out within the context of the COMPTINN' program, a joint research project founded by a FUI program (Fonds
) in which four research teams focused on the thermo-oxidation behaviour of HTS-TACTIX carbon-epoxy composite at 'high' temperatures (
). The scientific aim of the COMPTINN' program was to better identify, with a multi-scale approach, the link between the physico-chemical mechanisms involved in thermo-oxidation phenomena, and to provide theoretical and numerical tools for predicting the mechanical behaviour of aged composite materials including damage onset and development.
Beating phenomena in spacecraft sine testing and an attempt to include the sine sweep rate effect in the test-prediction
Nali, Pietro ; Bettacchioli, Alain ;
Advances in aircraft and spacecraft science, volume 3, issue 2, 2016, Pages 197~209
DOI : 10.12989/aas.2016.3.2.197
The Spacecraft (S/C) numerical sine test-predictions are usually performed through Finite Element Method (FEM) Frequency Response Analysis (FRA), that is the hypothesis of steady-state responses to harmonic excitation to the S/C base is made. In the test practice, the responses are transient and may be significantly different from those predicted through FRA. One of the most significant causes of discrepancy between prediction and test consists in the beating phenomena. After a brief overview of the topic, the typical causes of beating are described in the first part of the paper. Subsequently, focus is made on the sine sweep rate effect, which often leads to have beatings after the resonance of weakly damped modes. In this work, the approach illustrated in the literature for calculating the sine sweep rate effect in the case of Single-Degree-Of-Freedom (SDOF) oscillators is extended to Multi-Degrees-Of-Freedom (MDOF) systems, with the aim of increasing the accuracy of the numerical sine test-predictions. Assumptions and limitations of the proposed methodology are detailed along the paper. Several assessments with test results are discussed and commented.
Nonlinear model based particle swarm optimization of PID shimmy damping control
Alaimo, Andrea ; Milazzo, Alberto ; Orlando, Calogero ;
Advances in aircraft and spacecraft science, volume 3, issue 2, 2016, Pages 211~224
DOI : 10.12989/aas.2016.3.2.211
The present study aims to investigate the shimmy stability behavior of a single wheeled nose landing gear system. The system is supposed to be equipped with an electromechanical actuator capable to control the shimmy vibrations. A Proportional-Integrative-Derivative (PID) controller, tuned by using the Particle Swarm Optimization (PSO) procedure, is here proposed to actively damp the shimmy vibration. Time-history results for some test cases are reported and commented. Stochastic analysis is last presented to assess the robustness of the control system.
Mechanical architecture and loads definition for the design and testing of the Euclid spacecraft
Calvi, Adriano ; Bastia, Patrizia ;
Advances in aircraft and spacecraft science, volume 3, issue 2, 2016, Pages 225~242
DOI : 10.12989/aas.2016.3.2.225
Euclid is an astronomy and astrophysics space mission of the European Space Agency. The mission aims to understand why the expansion of the Universe is accelerating and what is the nature of the source responsible for this acceleration which physicists refer to as dark energy. This paper provides both an overview of the spacecraft mechanical architecture and a synthesis of the process applied to establish adequate mechanical loads for design and testing. Basic methodologies and procedures, logics and criteria which have been used with the target to meet a compliant, "optimised" design are illustrated. The strategy implemented to limit the risk for overdesign and over-testing without jeopardizing the design margins is also addressed.