FIELD: aircraft engineering.
SUBSTANCE: aircraft or spacecraft fuselage comprises outer skin 100 with arched inner contour and structural element 200. Said element arched stiffener 202 to fit in outer skin inner shape and transverse element 204 to interconnect two arched sections 206, 206' of rib arc in crosswise direction that features higher stiffness of said rib.
EFFECT: improved absorption of overloads.
20 cl, 7 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| SHELL SEGMENT FOR MAKING AIRCRAFT FUSELAGE COMPARTMENT SECTION | 2010 |
|
RU2494007C1 |
| AIRCRAFT OR SPACECRAFT STRUCTURAL COMPONENT AND AIRFRAME | 2008 |
|
RU2475411C2 |
| PRESSURE BULKHEAD AND METHOD FOR DIVISION OF INTERIOR SPACE OF AIRCRAFT OR SPACECRAFT | 2008 |
|
RU2471672C2 |
| AIRLINER TIGHT FUSELAGE COMPARTMENT SKIN FROM POLYMER COMPOSITE AND METHOD OF ITS FABRICATION | 2011 |
|
RU2475412C1 |
| SYSTEM OF AIRCRAFT FUSELAGE TWO SECTIONS AND CONNECTION STRUCTURE FOR FUSELAGE SKIN CONNECTION | 2008 |
|
RU2479466C2 |
| HULL | 2005 |
|
RU2384462C2 |
| AIRCRAFT FUSELAGE STRUCTURE AND MANUFACTURING METHOD | 2007 |
|
RU2435700C2 |
| AIRCRAFT FUSELAGE WITH INTEGRATED POWER-ABSORBING STRAINING STRUCTURE AND AIRCRAFT WITH SUCH FUSELAGE | 2011 |
|
RU2565165C2 |
| METHOD OF DEVICE FOR PRODUCTION OF CYLINDRICAL STRUCTURAL COMPONENTS | 2008 |
|
RU2488488C2 |
| STRUCTURAL COMPONENT AND METHOD FOR STRUCTURAL COMPONENT MANUFACTURING | 2010 |
|
RU2519111C2 |
