Patent ID: 8678315

Claim:
A strut system for the stabilisation of a shell of an aerodynamic aircraft component in a commercial aircraft, comprising: a pair of connection supports connected to the inside of the shell and opposing each other, struts extend between and connected to the connection supports to form a latticework structure, which struts at nodal points arranged on the ends are connected to the connection supports, wherein an area extension of the latticework structure is aligned in such a manner relative to a middle plane of symmetry that the struts, formed with an open symmetrical cross section, as well as the cross section of the connection supports, are arranged so as to be symmetrical to the aforesaid, wherein the connection supports are connected to the shell, on both sides of the plane of symmetry by rows of spaced apart, individual, mounting brackets provided on the connection support, which rows extend towards the shell, wherein a pair of opposite mounting brackets each comprise an L-shaped cross section and are jointly affixed in a non-detachable manner to the connection support and to the shell, wherein the nodal point comprises nodal plates that are symmetrically opposite each other on both sides of the end region of the strut and of the adjoining connection support, which nodal plates in relation to material and geometry are constructed in such a manner that a non-rigid component connection due to a gap between the strut and the connection support arises.