Exhaust nozzle segmented basesheet and production method thereof

A basesheet (52) for use in an aircraft gas turbine engine exhaust nozzle includes a plurality of basesheet segments (80) extending between longitudinally extending spaced apart basesheet leading and trailing edges (56 and 58), respectively, of the basesheet (52). Right and left hand basesheet side edges (60 and 62), respectively, extend longitudinally between the basesheet leading and trailing edges (56 and 58). Each basesheet segment (80) has a panel body (92) defined between a pair of segment side edges (84 and 86) longitudinally extending between segment leading and trailing edges (88 and 90), respectively. Stiffeners having leading and trailing edge ribs (96 and 97) at the segment leading and trailing edges (88 and 90) of aft and forward ones (105 and 109) of the basesheet segments (80), respectively, extend widthwise across the panel body (92) between the segment side edges (84 and 86). The leading and trailing edge ribs (96 and 97) are joined together only at intermediate sections (110) of the stiffeners which are centered between left and right hand expansion sections (116 and 118), respectively, of the stiffener (106). In the expansion sections (116 and 118) the side leading edge flanges (144) of the leading edge ribs (96) have rolled over tabs (148) bent inwardly towards the panel bodies (92).