| 摘要 |
<p>#CMT# #/CMT# The method involves coupling a structural section (1) to a stiffener (2) to be protected. The section is provided with an upper section (11) extending at distance from an edge (20) of the stiffener and arranged in form of an envelope adapted to absorb impacts on the edge by plastic deformation, a lower section (12) framing lateral flanks and an intermediate section bearing partially on the edge to minimize propagation of impact forces to the lower section. The lower section is coupled demountably by detachment of fasteners (3) without deformation of the structural section. #CMT# : #/CMT# The lower section of the structural section includes lower walls featuring a notch filled with mastic. The material of the structural section is chosen from alloys based on aluminum and alloys based on titanium or epoxy aramide. An independent claim is also included for a protection device for protecting stiffeners of a composite panel. #CMT#USE : #/CMT# Method for protecting stiffeners of a composite panel (claimed) of a wing or ventral beam box section used in aeronautical application. #CMT#ADVANTAGE : #/CMT# The structural section is provided with the upper section arranged in form of the envelope adapted to absorb impacts on the edge of the stiffener by plastic deformation and the intermediate section bearing partially on the edge so as to minimize propagation of impact forces to the lower section, where the lower section is coupled demountably by detachment of fasteners without deformation of the structural section, thus protecting the stiffener by absorbing edge impacts without propagation of impact energy to the protected stiffener, and hence reducing influence of damage tolerance criterion. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a partial perspective view of a titanium-based alloy structural section with a double-lobe upper section. 1 : Structural section 2 : Stiffener 3 : Fasteners 11 : Upper section 12 : Lower section 20 : Edge.</p> |
