| 摘要 |
FIELD: transport.SUBSTANCE: invention relates to aircraft tail, particularly, to load application zones of horizontal and vertical tail-planes. Aircraft tail with load application zone comprises tail-plane load take-up elements jointed with the fuselage structural elements. Structural elements are composed of the skin, two adjacent bearing frames and third frame connected with one of the latter. Said frames have two lateral elements and one base element, their cross-section having a closed shape. Horizontal tail-plane load take-up element represents the first fitting composed by torsion box with sidewalls and cover arranged crosswise between bearing frames and connected therewith. Vertical tail-plane load take-up elements represent the second fittings connected with the frames. Frames and fittings are made of composite.EFFECT: optimum distribution of load and weight, simplified design.9 cl, 11 dwg |
