Ch 7. Stress Analysis Multimedia Engineering Mechanics PlaneStress PrincipalStresses Mohr's Circlefor Stress Failure PressureVessels
 Chapter 1. Stress/Strain 2. Torsion 3. Beam Shr/Moment 4. Beam Stresses 5. Beam Deflections 6. Beam-Advanced 7. Stress Analysis 8. Strain Analysis 9. Columns Appendix Basic Math Units Basic Equations Sections Material Properties Structural Shapes Beam Equations Search eBooks Dynamics Fluids Math Mechanics Statics Thermodynamics Author(s): Kurt Gramoll ©Kurt Gramoll

 MECHANICS - CASE STUDY Introduction Aircraft Fuselage Loading A new passenger plane is being designed with a composite fuselage skin. The fibers will be placed in four different directions; 1) along the length of the fuselage or longitudinal (long) direction, 2) around the circumferential (circ) direction, 3) 30o from the longitudinal fibers, and 4) -30o from the longitudinal fibers. The skin is made from multiple layers of graphite reinforced epoxy, but the fibers are only placed in the four directions as described. What is known: The stress in the longitudinal direction, σlong, is 50 ksi. The stress in the circumferential direction, σcirc, is 25 ksi. The twisting of the fuselage causes a shear stress, τtwist of 25 ksi. Question What is the normal and shear stress in the direction of the 30o and -30o fibers? Approach Using the stress analysis equations, rotate the stress state to plus and minus 30 degrees.

Practice Homework and Test problems now available in the 'Eng Mechanics' mobile app
Includes over 400 problems with complete detailed solutions.
Available now at the Google Play Store and Apple App Store.