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Applied Composite Materials: An International Journal for the Science and Application of Composite Materials (v.12, #1)
Advanced Design Problems in Aerospace Engineering, Delft, The Netherlands
by C. A. J. R. Vermeeren (pp. 1-2).
Multi-Disciplinary Design Philosophy for Aircraft Fuselages. Part I by A. Beukers; M. J. L. van Tooren; Th. de Jong (pp. 3-11).
A short discussion is given to show the potential to improve aircraft fuselages with the application of a multi-disciplinary design philosophy.
Keywords: multi-disciplinary design; aircraft fuselages
Two Simple Design Problems, Which Illustrate the Multi-Disciplinary Concept. Part II by Th. de Jong; A. Beukers; M. J. L. van Tooren (pp. 13-19).
Th. Jong, A. Beukers and M. J. L. van Tooren [1, 2] considered two simple design problems, which illustrate the multi-disciplinary design concept.
Keywords: multi-disciplinary design; composite; aluminium; tension; buckling
Integration of Acoustics and Mechanics in a Stiffened Shell Fuselage. Part III by L. A. Krakers; M. J. L. van Tooren; K. Zaal; C. A. J. R. Vermeeren (pp. 21-35).
To explore the possibilities of a multidisciplinary fuselage design, first the mechanical properties of a stiffened fuselage are discussed. This gives an idea of the available room to vary the structural parameters of such a fuselage. Section 1 describes the design window of a CFRP stiffened fuselage. This design window is created by the possible CFRP fuselage designs (by varying the frame pitch and skin thickness) which are lighter than the lightest aluminium stiffened fuselage. In the remainder of Part III the integration of acoustical insulation in a stiffened shell fuselage is discussed resulting in a design strategy for optimal integration.
Keywords: multi-disciplinary design; stiffened fuselage structure; sound transmission loss
Integration of Mechanics and Acoustics in a Sandwich Fuselage. Part IV by M. J. L. van Tooren; L. A. Krakers; A. Beukers (pp. 37-51).
Until now only the stiffened skin structural concept has been discussed. A different structural concept is the sandwich concept. Sandwiches consist out of layers. The outer layers are called facings and are generally thin and of high density. These facings are supposed to resist most of the edgewise loads and flat-wise bending moments. The inner layer is called the core and is generally rather thick and of low density. The task of the core is to separate and stabilize the two facings, transmit shear between the facings and provide most of the shear rigidity. For sandwich panels no stiffeners are needed. Therefore no mass will be lost in stiffeners resulting in a relative high value of mass per unit area of the skin which results in a better TL according to the mass law. Also the core can be made of a material with high insulation properties (acoustic and thermal). The number of discrete stiffeners can then be minimized, since they are only required at places where high concentrated forces have to be introduced (wing, landing gear, etc.) or diverted (from cut-outs). This can reduce the production and maintenance cost. So it can be concluded that the sandwich concept offers great potential for multidisciplinary fuselage design. In this part the integration of structural and acoustical aspects will be discussed. First the structural aspect will be discussed followed by the acoustical aspect. Finally the possibilities to integrate these aspects are explained.
Keywords: sandwich fuselage structure; sound transmission loss; integration
Application of a Visco-Elastic Layer. Part V by A. Beukers; M. J. L. van Tooren; L. A. Krakers (pp. 53-57).
Short discussion of the possibilities of applying a visco-elastic layer in an aluminium and a carbon/epoxy fuselage structure to improve the sound transmission properties.
Keywords: visco-elastic layer; fuselage structure; sound transmission loss; loss factor