Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
  • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
  • B64C1/12—Construction or attachment of skin panels
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
  • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
  • B64C1/064—Stringers; Longerons
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
  • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
  • B64C1/065—Spars
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
  • B64C2001/0054—Fuselage structures substantially made from particular materials
  • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/40—Weight reduction

Definitions

• the invention relates to a fuselage cell structure for an aircraft, wherein the trunk cell structure is formed with a plurality of skin panels, longitudinal stiffeners and transverse stiffeners, in particular frames, creating a plurality of longitudinal and / or transverse sutures, wherein at least one skin panel double-shelled and at least one skin panel is executed monolithic.
• Known embodiments of aircraft fuselage cells are generally formed with monolithic skin panels.
• the monolithic skin panels can be made with metallic materials and / or with fiber composites.
• For stiffening the monolithic skin panels are a plurality of spaced parallel to each other in the direction of flight extending longitudinal stiffeners and Spantprofile as transverse stiffeners, which are arranged in the transverse direction to the direction of flight provided.
• the production of the longitudinal stiffeners and the frame segments and their attachment to a monolithic skin field mean a considerable manufacturing effort.
• Fuselage cells with skin panels in double-shell construction are generally found on smaller aircraft types.
• planar and / or at least partially curved sandwich elements are used, in which an inner and an outer cover layer are provided by a core structure, for example in the form of a honeycomb core, a hard foam core or a folded honeycomb core to create a defined distance connected to each other.
• the cover layers may be formed with composite fiber materials, with metallic materials or hybrid materials such as glare ®.
• An ideal double-shell design has the particular advantage that less or no longitudinal stiffeners and ribs are required for stiffening the fuselage cell, thereby the production costs can be reduced and weight advantages can arise.
• a reduction in the thermal primary insulation of double-skin skin fields is possible.
• the object of the invention is to provide a fuselage cell in hybrid construction, in which flat and / or at least simply curved skin panels in monolithic and double-shell construction to create longitudinal and / or transverse seams by power flow optimized interfaces are combined so that there are weight savings , wherein at the same time the production cost is reduced.
• Skin fields are combined into a complex fuselage cell structure.
• a complete fuselage section can be constructed with double-shelled skin fields and an adjoining fuselage section can be designed exclusively with monolithic skin panels.
• the longitudinal tab provided with an inclined step in the interface between a double-skin skin panel and a monolithic skin panel in the longitudinal seam region, forces originating from the two cover layers of the sandwich member can be produced. merged and introduced into the monolithic skin field.
• the longitudinal tab ensures completion of the core structure of the double-shelled skin panel.
• a plurality of load transitions are provided, which serve for load transfer between the longitudinal stiffeners arranged on the monolithic skin panel and a cover sheet of the skin panel executed in double-shell construction.
• Longitudinal flange is connected to an inner cover layer of a double-skin skin panel and the second longitudinal flange is connected to an outer cover layer of the double-skin skin panel, and the second longitudinal flange means of a tab and / or a profile, in particular by means of a T-Prof ⁇ ls, with a monolithic skin field under creation a longitudinal seam is connected.
• the monolithic skin panel is joined on the inside to the second longitudinal flange of the longitudinal tab.
• the outer cover layer of the double-shelled skin panel bridges the outside between the impact between the second longitudinal flange and the monolithic skin panel.
• At least one bulkhead of a monolithic skin panel has a lower-side recess in the region of a former end and at least one angle is arranged in the region of the former end.
• the angle Due to the angle, a mechanical connection of the frame end to the double-shelled skin panel is made possible, since in the region of the double-shelled skin panel, as a rule, no frame is required.
• the angle may optionally be an integral part of the frame. In the case of one in the area of the double-shelled skin field in relation to the monolithic
• Skin field reduced Spantaniere can thus be a power flow compatible connection of the frame to the double-shelled skin field.
• At least one transverse tab with a first and a second transverse flange is arranged in the region of the at least one transverse seam, wherein the transverse flanges are connected to each other by means of a step largely offset from each other.
• the cross-strap though not primarily, transfers loads between the double-shelled skin panel and the monolithic skin panel. At the same time done by the cross-bar completion of the core structure of the double-skin skin field.
• FIG. 1 is a schematic perspective view of a erfmdungshunt executed longitudinal seam between a double-skin skin panel and a monolithic skin panel
• FIG. 2 is a cross-sectional view of FIG. 1 in the region of the end of the former
• FIG. 3 is a cross-sectional view along the section line HI-III in FIG. 2,
• FIG. 4 shows a schematic perspective view of a transverse seam according to the invention between a monolithic skin panel and a double skin panel with a plurality of load transitions
• FIG. 5 is a detailed sectional view through an inventively executed transverse seam
• 6 shows an embodiment of a transverse seam between a monolithic and a double-skin skin panel with a window integrated in the transverse seam region.
• FIG. 1 shows a perspective view of a longitudinal seam 1 designed according to the invention between a double-skin skin panel 2 and a monolithic skin panel 3 of a fuselage cell produced in hybrid construction, that is to say by a combination of monolithic and double-skin skin panels.
• the double skin panel 2 is formed with a core structure 4, which is provided with an inner cover layer 5 and an outer cover layer 6.
• the outer cover layer 6 is formed with an optional thickening 7 and a skin 8.
• One of the flight direction of the fuselage cell not shown corresponding x-axis 9 is approximately parallel to the longitudinal seam. 1
• the longitudinal seam 1 is essentially formed with a longitudinal tab 10.
• the longitudinal flap 10 has a first flange 11 and a second flange 12, which are approximately parallel to each other offset by means of an inclined web 13 are interconnected.
• the term "parallelism” in the context of the application is not to be understood in the strict sense of planar geometry. Rather, the term “parallel” in this case means that two flat and / or at least partially at least slightly curved surfaces, such as the flanges 11,12 fictitious at least partially uniformly spaced apart in space.
• the two flanges 11, 12 in approximately hollow-cylindrical fuselage cell sections have a substantially simply curved surface geometry
• the flanges 11, 12 in a tail and cockpit region of the fuselage cell generally have a complex spherical, that is, at least in regions doubly curved surface geometry.
• the degree of curvature may vary locally.
• the flanges 11, 12 also have a plane geometry.
• An inclination angle of the web 13 is preferably less than 45 °.
• the first flange 11 is connected in the region of the longitudinal seam 1 with the inner cover layer 5. The connection can for example, by riveting, bolting and / or gluing done.
• the actual connection between the second flange 12 and the monolithic skin panel 3 takes place by means of a T-profile 14 running essentially transversely to the x-axis 9
• the base flange 15 of the T-Prof ⁇ ls 14 is firmly connected both to the second flange 12 and with the monolithic skin panel 3.
• the outer cover layer 6 bridges the region of the longitudinal seam 1 which is formed by the butt joint between the second flange 12 and the monolithic skin panel 3, that is, there is a mechanical connection between the T-profile 14, the second flange 12, the monolithic skin panel 3 and the outer cover layer 6 of the double-skin skin panel 2.
• the connection between the all mentioned components can be done in a known manner by rivets, bolts and / or at least partially adhesive bonds.
• a connecting element is shown in Fig. 1 representatively for all others with the reference numeral 17.
• a rib 18 In approximately transverse to the longitudinal seam 1, a rib 18 extends with a foot flange 19 and a head flange 20, which are interconnected by a perpendicular thereto web 21.
• a former end 22 In the region of a former end 22 there is a lower-side recess 23 in the frame 18 and an angle 24 for connecting the former end 22 to the double-shelled skin panel 2.
• the angle 24 has a first and a second leg 25, 26 which are in contact with the inner cover layer 5 the double-skin skin panel 2 and the former end 22 are connected.
• the legs 25,26 enclose an angle of about 90 °.
• the angle 24 allows a structurally optimal connection of the former end 22 to the double-skin skin panel 2.
• another angle on the other side of the web 21 of the frame 18, opposite to the angle 24 may be provided.
• This pocket-like recess 27 serves to accommodate a not shown in Fig. 1 Verstärkungsprof ⁇ ls to the
• Frame end 22 in addition to the connection to the inner cover layer 5 to connect with the outer cover layer 6 of the double-skin skin panel 2.
• the recess 23 provided on the underside of the spider 18 in the region of the former end 22 enables the height compensation between the double-skin skin panel 2 with a large material thickness and the comparatively thin monolithic skin panel 3.
• FIG. 2 shows a simplified cross-sectional representation through the longitudinal seam 1 according to the invention between the double-skin skin panel 2 and the monolithic skin panel 3.
• the longitudinal seam 1 is formed as a result of the connection of the second (right side) longitudinal flange 12 of the longitudinal tab 10 with the monolithic skin panel 3 through the base flange 15 of the T-profile 14 in conjunction with the longitudinal seam 1 on the underside completely overlapping outer cover layer 6 of the double-skin skin panel 2. Die Connection of the inner cover layer 5 takes place through the first, left-side longitudinal flange 11 of the longitudinal tab 10. By the rigid longitudinal tab 10 in conjunction with the outer cover layer 6 forces that emanate from the cover layers 5.6 of the double-skin skin panel 2, first merged and then at the same time transferred over the top and bottom into the monolithic skin 3.
• the foot flange 19 of the frame 18 is connected to the monolithic skin panel 3 and the former end 22 via the angle 24 at least with the inner cover layer 5 of the double-skin skin panel 2.
• the recess 23 provided in the region of the former end 22 in a lower region of the spider 18 serves to equalize the level between the double-skin skin panel 2 and the monolithic skin panel 3, and moreover permits the transverse passage of the T-profile 14.
• an optional, here parallelepiped-shaped recess 27 or pocket can be embedded.
• the optional recess 27 serves to integrate a hollow body with a suitable cross-sectional geometry, such as a double T-profile 28.
• the double-T-profile 28 can complement the connection shown by the
• Connecting elements at least partially connected areally with the covering skins, for example, be glued. This allows the former end 22 in a mechanically effective manner additionally be connected to the outer cover layer 6 of the double-skin skin panel 2.
• the connecting elements required for the creation of the complete longitudinal seam 1 are not indicated by circles or ellipses but by dash-dotted lines.
• the double-T-profile 28 or a hollow body to be received in the recess 27 can be formed with a metallic material and / or with a fiber composite material.
• FIG. 3 shows a simplified cross-sectional view according to the section line HI-III in FIG. 2.
• the optional foot flange 19 of the spider 18, the first flange 11 of the longitudinal tab 10 and the inner cover layer 5 can be joined together via unspecified fasteners.
• Cover layer 5 and the double-T profile 28 is joined together.
• the outer cover layer 6 of the double-skin skin panel 2 with the double-T-Prof ⁇ l 28 is connected.
• the double-T-Pro Stahl strains 28 as a profile body can be integrated into the recess 27 in the core structure 4 in the double-skin panel 2 for connecting the frame end 22 any conceivable profile shape with a suitable cross-sectional geometry, for example, a rectangular hollow profile.
• the double-T-Pro Stahl 28 thus allows the former end 22 is connected by means of the angle 24 with both the inner cover layer 5 and the outer cover layer 6 of the double-skin skin panel 2, so that a statically effective transfer of forces between the skin fields in Area of the longitudinal seam 1 of the abutting skin panels 2,3 is achieved.
• FIG. 4 illustrates a schematic view of a transverse seam according to the invention between a monolithic skin panel and a double skin panel having a plurality of load transitions.
• a transverse seam 29 exists between a monolithic skin panel 30 and a double-shelled skin panel 31.
• Another double-shelled skin panel 32 is connected to the double-shelled skin panel 31 by means of a double-shelled interface 33.
• the connecting elements used here, in particular rivets and / or bolts, are indicated by small circles.
• the course of the x-axis 9 is synonymous with the direction of flight.
• Disposed on the monolithic skin panel 30 are a plurality of longitudinal stiffeners, not shown, which are approximately parallel to the x-axis 9 and which are provided with a plurality of load transitions, a load transition 34 being representative of all others, with the double skin panel 31 are connected.
• the load transition 34 has at one end via a trapezoidal flange 35, with which the mechanical coupling to the double-skin skin panel 31 takes place. Below the trapezoidal flange 35 extends a substantially parallel to the x-axis 9 extending profile section 36 with an L-shaped cross-sectional geometry, the mechanical
• the load transition 34 is integrally formed.
• an optional transverse tab 37 which has a first transverse flange 38 and a second transverse flange 39, which are interconnected by a substantially vertically extending step 40.
• the transverse flanges 38,39 are approximately parallel spaced apart, wherein a distance of the two transverse flanges 38,39 of the substantially vertical step 40 corresponds.
• the transverse tab 37 is preferably formed in one piece. By the transverse tab 37, a completion of the core structure of the double-skin skin panel 31 is achieved at the same time.
• FIG. 5 illustrates a detailed sectional view through a transverse seam 41 configured according to the invention between a double-skin skin panel 42 and a monolithic skin panel 43.
• the double skin panel 42 comprises a core structure 44 which is provided with an inner cover layer 45 and an outer cover layer 46.
• the outer cover layer 46 comprises a thickening 47 and the actual skin 48.
• a transverse flap 49 which has a first transverse flange 50 and a second transverse flange 51 extending substantially parallel thereto, the two transverse flanges 50, 51 being approximately vertical Level 52 are interconnected.
• a longitudinal stiffener 53 In the region of the monolithic skin panel 43, there is a longitudinal stiffener 53, in whose end section 54 a small vertical offset 55 is provided for height compensation.
• the end portion 54 is located in the region of the transverse seam 41 on the second transverse flange 51.
• the mechanical coupling between the longitudinal stiffener 53 in the region of the monolithic skin panel 43 and the double-shell skin panel 42 is effected by a load transition 56 which has a trapezoidal flange 57 at one end and whose end directed away therefrom terminates in a profile section 58 with a substantially L-shaped cross-sectional geometry ,
• the transverse seam 41 is formed by the trapezoidal flange 57, which is connected to the first transverse flange 50 of the transverse flap 49 and the inner cover layer 45.
• the profile section 58 of the load transition 56 is connected to the second transverse flange 51 and the outer cover layer 46.
• a connection is made between the longitudinal stiffener 53, the second transverse flange 51 and the monolithic skin panel 43 and the end section 54 of the longitudinal stiffener 53.
• a frame 59 and a support bracket 60 are shown in the illustration of FIG. 5, which are likewise connected to the end section 54 of the longitudinal stiffener 53, the second transverse flange 51 and the monolithic skin panel 43 in the region of the transverse seam 41.
• Profile section for example, a double-T profile 62, be integrated to additionally effect in particular a connection of the load transfer 56 to the outer cover layer of the double-skin skin panel 42 (see Fig .. 3).
• the double T-profile 62 may be formed with a metallic material and / or with a fiber reinforced plastic material.
• the connection of the double-T profile 62 to the core structure 44, the cover layers 45, 46 and the load transition 56 can be effected by connecting elements and / or by an adhesive connection carried out at least in regions and / or by foaming.
• the longitudinal stiffener 53 already ends before the transverse seam 41.
• the design of the load transition 56 takes place optionally as an integral component or as a differential component. Integral design of the load transition 56 would be such a way that while trapezoidal flange 57 and profile section 58 are combined in a single component.
• a differential design sees the design of the load transition 56 optionally of two or more components for trapezoidal flange 57, profile section 58 and the connection by means of a separate profile or profile body, which may for example have an L-shaped but also any other conceivable cross-sectional geometry, to the longitudinal stiffener 53rd in front.
• a connection of the load transfer 56 can optionally be made directly to the longitudinal stiffener 53 and / or between two longitudinal stiffeners, with an additional transverse stub for the connection of monolithic and doppelschaligem skin field 43,42 can be used.
• the advantage of this embodiment is, inter alia, that the otherwise necessary for leveling, especially when using fiber composites but manufacturing technology only consuming to be formed offset 55 in the end of the longitudinal stiffener 53 can be omitted.
• FIG. 6 illustrates in a schematic representation an embodiment variant of a transverse seam for
• a monolithic skin panel 70 is connected to a double skin panel 71.
• the double skin panel 71 comprises an inner and an outer cover layer 72, 73, between which a core structure 74 is arranged.
• the core structure 74 including the inner cover layer 72 of the double-skin skin 71 has been removed to create a recess 78 in the double-skin skin 71.
• the geometry of the recess 78 corresponds approximately to a rectangular edge strip immediately adjacent to the transverse seam 77, to which a rectangular area for the window frame 75 adjoins the right-hand side.
• the transverse seam 77 is formed, for example, by means of an internally arranged and secured, but not shown here, crossbolt between the monolithic skin panel 70 and the outer cover layer 73 of the double-skin skin panel 71 exposed in this area.
• the core structure 74 is still present and provided on both sides with the cover layers 72, 73, there are two so-called double-shell window frames 79, 80, which are designed for integration into double-skin skin fields.
• Longitudinal seam 83 also follows the structure of the illustrated in the description of FIGS. 1 to 3 longitudinal seam.
• transverse flap 84 which has two connected to a vertical, step-like web, not provided with a reference number transverse flanges.
• the longitudinal stiffeners 88, 89 of the monolithic skin panel 70 are connected to the double-shell skin panel 71 in the region of the transverse seam 77.
• the longitudinal stiffeners 88, 89 are connected to the trapezoidal flanges 86, 87 by means of non-designated profile sections with a preferably L-shaped cross-sectional geometry (cf., in particular, Fig. 4, reference numeral 36), wherein the profile sections are preferably designed as integral parts of the trapezoidal flanges 86,87.
• the profile sections may be connected by means of suitable connecting elements with the trapezoidal flanges 86, 87.
• the embodiment of the transverse straps 84,85 again follows the configuration of the transverse straps used to provide the transverse seam between a monolithic and a double-skin skin panel in accordance with FIGS. 4 and 5.
• the longitudinal straps 81, 82 and the transverse straps 84, 85 can each end truncated Ideally, mitres should be largely gap-free and fit together.
• the sectional view II shows a schematic cross-sectional view of the window frame 79, 80 inserted into the double skin panel 71, while the
• Sectional view IV is a schematic sectional view through the monolithic Window frame 75 and the outer cover layer 73 of the double-skin skin panel 71 and the monolithic skin panel 70 illustrated.
• window frame 75 Integration of a window frame 75 in the region of the transverse seam 77 above all an "equalization" of the transverse seam 77 in static terms, that is, a more advantageous load flow from the monolithic skin panel 70 into the double skin panel 71 and vice versa.
• window frame 75 is arranged in the region of the recess 78, which was created by removing the core structure 74 and the inner cover layer 72 from the double-skin skin panel 71 in the region of the transverse seam 77.
• the double skin panel 71 constitutes a "pseudo" monolithic skin field, whereby the actually rectilinear transverse seam 77 "carried" into the double skin panel 71 at least in the region of the window frame 75 and the effect of the butt joint between the skin panels 70, 71 is rectified locally in static terms.
• the longitudinal and transverse seams produced in accordance with the invention can be used between monolithic and / or partially monolithic and double-shelled skin fields which are planar and / or in sections.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Aviation & Aerospace Engineering (AREA)
• Body Structure For Vehicles (AREA)
• Laminated Bodies (AREA)
• Tents Or Canopies (AREA)

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Citations (4)

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• 2009
  • 2009-03-17 DE DE102009013585A patent/DE102009013585B4/de not_active Expired - Fee Related
• 2010
  • 2010-03-16 US US13/257,367 patent/US9586668B2/en not_active Expired - Fee Related
  • 2010-03-16 CA CA2755840A patent/CA2755840A1/en not_active Abandoned
  • 2010-03-16 BR BRPI1009128A patent/BRPI1009128A2/pt not_active IP Right Cessation
  • 2010-03-16 WO PCT/EP2010/053331 patent/WO2010106040A2/de active Application Filing
  • 2010-03-16 JP JP2012500215A patent/JP2012520787A/ja active Pending
  • 2010-03-16 CN CN201080021424.6A patent/CN102427998B/zh not_active Expired - Fee Related
  • 2010-03-16 RU RU2011141820/11A patent/RU2482995C1/ru not_active IP Right Cessation
  • 2010-03-16 EP EP10713432A patent/EP2408665A2/de not_active Withdrawn

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