For 2-1 only

The circumferential (hoop) stress, h, is given as h=2tpD. The fuselage skin of the Comet was a high-strength aluminum alloy, 0.91mm thick. The fuselage was approximately 3.7m in diameter and 33m long. Standard atmospheric pressure is 1.013105Pa. (a) At (a), determine the hoop stress in the fuselage in Prob. 1-1 at the cruising altitude of 10,000m(32,800ft). (b) Assume that design details introduce a stress concentration of 3.0. Compute the maximum stress developed. 1. This problem is related to the Comet (jet plane) disasters. The atmospheric air pressure in cm of Hg as a function of altitude in kilometers, h, can be expressed as: p=768.45h+0.285h2 The Comet's cruising altitude was 10km, about twice the cruising altitude of commercial propeller-driven transport planes. Assume that the cabin in the Comet was maintained at a pressure equivalent to that at an altitude of 2.37km. Determine the differential between the external pressure and the cabin pressure in MPa units. This differential is the pressure the fuselage must support