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
| Title | Year | Author | Number |
|---|---|---|---|
| HIGH LOADED AIRCRAFT FUSELAGE FRAME WITH FRAMED STRUCTURED WALL | 2012 |
|
RU2607894C2 |
| FITTINGS FOR TRANSPOSITION OF AIRCRAFT HORIZONTAL STABILISER | 2009 |
|
RU2517931C2 |
| AIRCRAFT MAINFRAME MADE FROM COMPOSITE MATERIAL | 2007 |
|
RU2448865C2 |
| AIRCRAFT TAIL UNIT ATTACHMENT CONNECTORS | 2010 |
|
RU2524803C2 |
| COMPOSITE HAT-SHAPED STIFFENING CROSS-SECTION, COMPOSITE STIFFENED HAT-SHAPED CROSS-SECTION OF PRESSURE BULKHEADS AND METHODS OF THEIR MANUFACTURE | 2013 |
|
RU2641959C2 |
| AIRCRAFT HORIZONTAL STABILISER SURFACE | 2009 |
|
RU2539308C2 |
| AIRCRAFT PRESSURE BULKHEAD ASSEMBLY STRUCTURE | 2010 |
|
RU2522538C2 |
| MECHANICALLY DISTRIBUTED POWER PLANT AND METHOD OF AIRCRAFT OPERATION CONTROL | 2019 |
|
RU2743903C2 |
| AIRFRAME OF MULTIMODE MONOPLANE | 1997 |
|
RU2173654C2 |
| AIRCRAFT TAIL, METHOD OF ITS ASSEMBLY AND AIRCRAFT WITH SUCH TAIL | 2011 |
|
RU2570981C2 |
