FUSELAGE AIRCRAFT WITH INTEGRATED energy absorbing designs DEFORMATION AND AIRCRAFT WITH SUCH fuselage

摘要

1. The fuselage of an aircraft with an integrated deformation energopogloschayushey structure, - wherein the fuselage (1) has a ring-shaped frames (10; 110; 210) and interconnecting the frames (10; 110; 210) spars (12) and forming a liner (16 ; 116; 216) of the fuselage outer skin (14), - wherein the inside of the fuselage (1) is provided with at least one lower floor structure (3; 103; 203) that has several connected with an associated frame attachment (10; 110; 210) transverse beams (32; 132; 232) and connecting them to each other the longitudinal beams (4, 5, 30; 104, 105; 204, 205) sex, u n Rich in beneath the bottom floor structure (3; 103; 203) of the lower region of the fuselage is formed by a deformation structure, characterized in that the deformation structure includes a first neuprugodeformiruemuyu middle area (20; 120; 220) and respectively a second left-handed or right-handed neuprugodeformiruemuyu region (26 , 28; 126, 128; 226, 228) of greater rigidity in the vertical direction, than the average oblast.2. Fuselage according to claim 1, characterized in that the corresponding neuprugodeformiruemaya region (26, 28; 126, 128; 226, 228) of greater rigidity in the vertical direction has at least one elongated downward beyond the transverse beams (32; 132; 232) of the bottom sexual structure (3; 103; 203) the longitudinal beam (4, 5; 104, 105; 204, 205) the floor, which in their upper region connected with the transverse beams (32; 132; 232) sexual structure (3; 103; 203 ) and which is connected to the frames (10, in its lower region; 110; 210) of the fuselage (1) .3. Fuselage according to claim 1, characterized in that located between the two second neuprugodeformiruemymi regions (26, 28; 126, 128; 226, 228) neuprugodeformiruemaya first region (20; 120; 220) is in the form of absorbing