The invention relates to a spoiler for an aircraft, comprising a panel structure (1), the panel structure comprising: an area member (2), especially a skin member, that defines an areal expanse with a first surface (3) and an opposite second surface (4) and having a thickness (5) between the first and second surfaces (3, 4); and a plurality of elongate stiffener members (6) which are attached to the area member (2) and extend over at least one of the first and second surfaces (3, 4); wherein at least one of the stiffener members (6) is bifurcated at a bifurcation point (P) into two or more branch stiffener members (6'). The invention also provides a method of producing such a spoiler.
КОНСТРУКЦИЯ ПАНЕЛИ И СООТВЕТСТВУЮЩИЙ СПОСОБ
2017-04-20
Patent
Electronic Resource
Russian