Energy-absorbing structural element made of a composite material and aircraft fuselage having said absorber

摘要

An aircraft fuselage has at least one reinforcement frame (13), at least one crossbar (14) and at least one energy-absorbing structural element (2) that includes a compression beam (21) having a longitudinal axis Z and oriented substantially in the direction of compression forces to be absorbed upon an impact, the compression beam being attached at a first end (213) thereof to the crossbar (14) and at a second end (214) thereof to the reinforcement frame (13). The compression beam (21) is attached at least one of its ends (213, 214) via a shoulder bracket (22), wherein the shoulder bracket further has the function of cutting the compression beam (21) in case of an impact.

主权项

1. An aircraft fuselage primary structure comprising:
a skin (11), at least one reinforcing fuselage frame (13), at least one crossmember (14) attached to said at least one reinforcing fuselage frame (13), and at least one structural element (2) of elongate shape, comprising a compression beam (21) of longitudinal axis Z made of composite material, said material comprising plies of continuous fibers held in place by a resin, said compression beam, the axis of which is directed substantially in a direction of compressive forces that are to be absorbed in the event of an impact, being attached at a first end (213) to the crossmember (14), and at a second end (214) to the reinforcing fuselage frame (13), wherein the compression beam (21) is attached, at least at one of the first and second ends (213, 214), by a gusset plate (22), said gusset plate comprising: guide means (223) for guiding the beam (21) substantially along its longitudinal axis Z, a cutting element (224) for cutting the compression beam (21) into at least two strips, in the direction of the longitudinal axis Z, and a clearance groove (225) for each of said at least two strips.