Laminate Plate With Point Load

1 the left end of the plate is terminated to the left of the point load a b and 2 the left end of the plate is terminated to the right of the point load a b.

Laminate plate with point load. The follow web pages contain engineering design calculators that will determine the amount of deflection and stress a flat plate of known thickness will deflect under the specified load and distribution. The piezoelectric actuator is assumed to be pzt g 1195 with the material properties 17 of young s modulus e pe 63 gpa poisson s ratio v pe 0 3 density ρ pe 7 600 kg m 2 piezoelectric constant d 31 1 9 10. External loads can be applied as body forces such as gravity and they can be applied as surface tractions in which case they correspond to the stresses σ zx σ zy and σ zz evaluated at z t 2 as shown in the next section. End load equivalent distributed point loads loads in shell.

The loads have the units of force per unit area and. 45 90 71 12 90 58 28 90 for uni axial bi axial and shear loading respectively. Plate at a given point. The dimensions of the composite laminate plate are length a 0 38 m width b 0 3 m thickness t p 1 5876 mm.

Many of the stress and deflection equations and calculators referenced from. Laminated composite plates david roylance department of materials science and engineering massachusetts institute of technology cambridge ma 02139 february 10 2000 introduction. The broad majority of ply or lamina materials obey hooke s law and hence all of their stresses and strains may be related by a system of linear equations. The pareto sets for maximum fundamental frequency and effective stiffness are located around the upper boundary of miki s diagram which corresponds to laminates with different ratios of 0 and 90 layers.

D moment load applied to shell l d. 0 2548e 10 0 3554e 12 0 1639e 16 0 7218d 10 0 7125d 19 0 6022d 16. Flat plates stress deflection equations and calculators. A loads in shell.

Composite laminates may be regarded as a type of plate or thin shell structure and as such their stiffness properties may be found by integration of in plane stress in the direction normal to the laminates surface. Hence each point corresponds to a specific laminate angle which lie on the intervals. When it s needed use of black isotropic analogs are useful for design studies. The plate is loaded in compression in the length direction.

The compressive load is measured as well as the length change between two points originally a distance of 25 4 mm 1 0 in apart above and below the hole. The thickness of the plate is sufficient that out of plane displacements of the plate can be ignored. Laminate plate theory nutshell lpt has a matrix formalism which. Two scenarios are considered and they are.