Abstract: There is provided a panel member capable of restraining an increase in weight of a wing panel while restraining wasteful work in the manufacturing process, an aircraft main wing, and a method for forming the panel member. A wing panel 10 is formed with ridges 20 each having a dimension larger than the machining tolerance in the boundary portions between areas A1, A2, . . . . Therefore, the worker who handles the wing panel 10 can visually confirm the step portions of the areas A1, A2, . . . easily. Thereby, if a flaw or the like is found in the areas A1, A2, . . . , corrective actions can be properly taken on the actually existing flaw without mistaking the flaw for the step portion of the areas A1, A2, . . . .

Abstract: An opening portion of a vent member is prevented from being blocked, and thus ventilation is reliably performed. A plurality of opening portions (40A, 40B) are formed in a single vent stringer (20), and thus even in a case where one of the opening portions (40A, 40B) is blocked, ventilation is secured by the other opening portion. At this time, since the opening portions (40A, 40B) are formed in surfaces different from each other in the vent stringer (20), a possibility that both the opening portions (40A, 40B) may be simultaneously blocked is less.

Abstract: An airframe panel for aircraft having stringers and ribs which enables reduction of the workload of the shimming operation includes a plurality of stringers provided on the inner surface of a lower skin along the spanwise direction of a wing, and a plurality of ribs provided along the chordwise direction of the wing. In a part of the panel in which a rib is provided, a flat support surface connects the two adjacent stringers. In another part of the panel in which no rib is provided, a stepped surface connects the two adjacent stringers where the stepped surface includes a thin-walled groove, and thick-walled bases to be connected to the stringers located at both sides of the groove.

Abstract: There is provided a wing panel having improved formability at the time when the wing panel is curvedly formed by the peen forming method, and an aircraft main wing provided with the said wing panel. For a stringer member 20, a base part 21 is formed, and the neutral axis position N in the cross-sectional direction is located on the wing panel 11 side from the center position C in the height direction of a web part 22. When the peen forming method is carried out by projecting metal shots to a portion near a flange part 23 in the tip end portion of the stringer member 20, the tensile strain developing in the portion near a flange part 23 acts in a state in which the moment length around the neutral axis position N is kept long.

Abstract: There is provided a panel member capable of restraining an increase in weight of a wing panel while restraining wasteful work in the manufacturing process, an aircraft main wing, and a method for forming the panel member. A wing panel 10 is formed with ridges 20 each having a dimension larger than the machining tolerance in the boundary portions between areas A1, A2, . . . . Therefore, the worker who handles the wing panel 10 can visually confirm the step portions of the areas A1, A2, . . . easily. Thereby, if a flaw or the like is found in the areas A1, A2, . . . , corrective actions can be properly taken on the actually existing flaw without mistaking the flaw for the step portion of the areas A1, A2, . . . .

Abstract: A narrow prepreg sheet 20N is bonded along a ridge C, and wide prepreg sheet 20W is bonded to other portions, whereby the wide prepreg sheet 20W having no cut line is bonded to both side portions of the ridge C. In a portion in which a spar 10 is curved, the narrow prepreg sheet 20N is bonded in an axial direction of the spar 10 while divided into plural pieces, and a length of the narrow prepreg sheet 20N is adjusted according to a radius of curvature of the curved portion in the axial direction of the spar 10, whereby various radii of curvature are easily dealt with.

Abstract: An opening portion of a vent member is prevented from being blocked, and thus ventilation is reliably performed. A plurality of opening portions (40A, 40B) are formed in a single vent stringer (20), and thus even in a case where one of the opening portions (40A, 40B) is blocked, ventilation is secured by the other opening portion. At this time, since the opening portions (40A, 40B) are formed in surfaces different from each other in the vent stringer (20), a possibility that both the opening portions (40A, 40B) may be simultaneously blocked is less.

Abstract: An object of the invention is to provide a low-cost closing member for an opening having an excellent lightning protection capability. In a door body 30, an outer surface 31a of a plate part 31 is formed by a composite material layer 60, and a side of an inner surface 31b and a flange part 32 are formed by a metallic material layer 61. The door body 30, a clamp ring 40, and an opening 12 of a wing panel 11 are electrically connected by surface bonding of conductive materials in a butt section of an abutment surface 34 of the door body 30 and a tapered surface 40c of the clamp ring 40 and a butt section of a tapered surface 40d of the clamp ring 40 and an abutment surface 14 of the opening 12.

Abstract: In order to provide an airframe panel for aircraft having stringers and ribs which enables reduction of the workload of the shimming operation, an airframe panel for aircraft of the present invention includes a plurality of stringers 15 provided on the inner surface of a lower skin 13 along the spanwise direction of a wing, and a plurality of ribs 17 provided along the chordwise direction of the wing. In a part of the panel in which a rib 17 is provided, a flat support surface 15c connects the two adjacent stringers 15. In another part of the panel in which no rib 17 is provided, a stepped surface connects the two adjacent stringers 15 where the stepped surface includes a thin-walled groove 16, and thick-walled bases 15a to be connected to the stringers 15 located at both sides of the groove 16.

Abstract: There is provided a wing panel having improved formability at the time when the wing panel is curvedly formed by the peen forming method, and an aircraft main wing provided with the said wing panel. For a stringer member 20, a base part 21 is formed, and the neutral axis position N in the cross-sectional direction is located on the wing panel 11 side from the center position C in the height direction of a web part 22. When the peen forming method is carried out by projecting metal shots to a portion near a flange part 23 in the tip end portion of the stringer member 20, the tensile strain developing in the portion near a flange part 23 acts in a state in which the moment length around the neutral axis position N is kept long.

Abstract: An object of the invention is to provide a low-cost closing member for an opening having an excellent lightning protection capability. A door body 30, a clamp ring 40 made of a composite material, and an opening 12 of a wing panel 11 made of the composite material are electrically connected by surface bonding of conductive materials in a butt section of an abutment surface 34 of the door body 30 and a tapered surface 40c of the clamp ring 40 and a butt section of a tapered surface 40d of the clamp ring 40 and an abutment surface 14 of the opening 12.

Abstract: A vent stringer 20 is formed by a pair of ribs 21 rising in the direction perpendicular to an inner surface 11a of a wing panel 11, and a cover 22 provided in the tip end portions of the ribs 21. With rivets 23 unexposed to an outer surface 11b of the wing panel 11, a spark is prevented from occurring in a fuel tank 30, which is provided in a main wing 10, through the rivet 23 at the time of a lightning strike. Formed by being machined integrally with the wing panel 11, the rib 21 is formed with high accuracy so as to match the curved shape of the wing panel 11. The cover 22 has only to be formed by curving a strap member so as to match the shapes of the wing panel 11 and the ribs 21.

Abstract: An object of the invention is to provide a low-cost closing member for an opening having an excellent lightning protection capability. In a door body 30, an outer surface 31a of a plate part 31 is formed by a composite material layer 60, and a side of an inner surface 31b and a flange part 32 are formed by a metallic material layer 61. The door body 30, a clamp ring 40, and an opening 12 of a wing panel 11 are electrically connected by surface bonding of conductive materials in a butt section of an abutment surface 34 of the door body 30 and a tapered surface 40c of the clamp ring 40 and a butt section of a tapered surface 40d of the clamp ring 40 and an abutment surface 14 of the opening 12.

Abstract: An object of the invention is to provide a low-cost closing member for an opening having an excellent lightning protection capability. A door body 30, a clamp ring 40 made of a composite material, and an opening 12 of a wing panel 11 made of the composite material are electrically connected by surface bonding of conductive materials in a butt section of an abutment surface 34 of the door body 30 and a tapered surface 40c of the clamp ring 40 and a butt section of a tapered surface 40d of the clamp ring 40 and an abutment surface 14 of the opening 12.

Abstract: A narrow prepreg sheet 20N is bonded along a ridge C, and wide prepreg sheet 20W is bonded to other portions, whereby the wide prepreg sheet 20W having no cut line is bonded to both side portions of the ridge C. In a portion in which a spar 10 is curved, the narrow prepreg sheet 20N is bonded in an axial direction of the spar 10 while divided into plural pieces, and a length of the narrow prepreg sheet 20N is adjusted according to a radius of curvature of the curved portion in the axial direction of the spar 10, whereby various radii of curvature are easily dealt with.

Abstract: There is provided a panel member capable of restraining an increase in weight of a wing panel while restraining wasteful work in the manufacturing process, an aircraft main wing, and a method for forming the panel member. A wing panel 10 is formed with ridges 20 each having a dimension larger than the machining tolerance in the boundary portions between areas A1, A2, . . . Therefore, the worker who handles the wing panel 10 can visually confirm the step portions of the areas A1, A2, . . . easily. Thereby, if a flaw or the like is found in the areas A1, A2, . . . , corrective actions can be properly taken on the actually existing flaw without mistaking the flaw for the step portion of the areas A1, A2, . . . .

Abstract: There is provided a wing panel having improved formability at the time when the wing panel is curvedly formed by the peen forming method, and an aircraft main wing provided with the said wing panel. For a stringer member 20, a base part 21 is formed, and the neutral axis position N in the cross-sectional direction is located on the wing panel 11 side from the center position C in the height direction of a web part 22.

Abstract: A vent stringer 20 is formed by a pair of ribs 21 rising in the direction perpendicular to an inner surface 11a of a wing panel 11, and a cover 22 provided in the tip end portions of the ribs 21. With rivets 23 unexposed to an outer surface 1 lb of the wing panel 11, a spark is prevented from occurring in a fuel tank 30, which is provided in a main wing 10, through the rivet 23 at the time of a lightning strike. Formed by being machined integrally with the wing panel 11, the rib 21 is formed with high accuracy so as to match the curved shape of the wing panel 11. The cover 22 has only to be formed by curving a strap member so as to match the shapes of the wing panel 11 and the ribs 21.