Static Analysis of rotodomed Aircraft Part II: Result

Numerical results from a finite element analysis of rotodomed aircraft are presented. Automatic Multistage Substructuring Scheme (AMSS) in CSA/NASTRAN has been effectively used in the modelling of rotodomed aircraft. The results presented correspond to four critical load cases - one vertical gust load case Vs and the other three side load cases. Detailed numerical results for these loading cases are presented in the form of tables containing displacements and stresses at salient points on the structure. In addition, deformed shapes, stress contours etc. of different components are also presented. It is found that the stresses in platform, pylons and fuselage are well within the allowable limits except for a few points in the region of intersection of pylons with the fuselage. The finite element sub-structuring modelling details of the rotodomed aircraft were reported in an earlier report

Heuristic design with load gradients and neural network optimisation for composite laminated plates

SIGLEAvailable from British Library Document Supply Centre-DSC:DX189020 / BLDSC - British Library Document Supply CentreGBUnited Kingdo

Static buckling and free vibration analysis of composite/ sandwich plates using improved transverse shear stiffness

A simple 4-noded quadrilateral shear-flexible plate element has been developed for the analysis of layered Composite/Sandwich laminates. The element is free from shear-locking and mechanisms. An improved transverse shear representation of the element stiffness makes it suitable for the analysis of either composite or sandwich plates. The accuracy of the element for the Static, Stability and Free Vibration analyses of Composite/Sandwich plates has been illustrated through extensive numerical examples. The element has been developed for use in a Laminate Design and Analysis Assistant (LAMDA) expert system