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The degree of damage tolerance used in the design of the DC-10 fuselage pressure shell is discussed with reasons for its selection. Analysis methods are presented for the prediction of the residual strength of damaged, stiffened panels, based on the matrix force solution of an idealized structure combined with fracture mechanics equations. The results of 20 different configurations are included. A description of the development test program to verify the analytical techniques and to substantiate the fail-safe strength of the fuselage shell is given together with the results for many of the tests.
airplanes, damage, tolerance (mechanics), aircraft panels, fuselages, reinforcement (structures), stiffening, cracking (fracturing), fatigue (materials), failure, fracture strength, axial stress, loads (forces), residual stresses, tests
Senior engineer scientist, Douglas Aircraft Co., McDonnell Douglas Corp., Long Beach, Calif.