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EP-4389593-B1 - STRUCTURE SYSTEM FOR INSTALLATION INTO A FUSELAGE STRUCTURE

EP4389593B1EP 4389593 B1EP4389593 B1EP 4389593B1EP-4389593-B1

Inventors

  • GOTTUMUKKALA, SWETHA
  • LOHMAR, JENS
  • HEGENBART, MATTHIAS
  • BENTHIEN, HERMANN
  • CZUDAR, ZOLTAN
  • Leising, Vivien
  • ABSHAGEN, SARA
  • ZYBALA, ANDRE

Dates

Publication Date
20260513
Application Date
20221219

Claims (14)

  1. Structure system (2, 96) for installation into a fuselage structure (6) in an interior of an aircraft (116), comprising: at least one first carrier element (18), at least one second carrier element (20, 44), at least one elongate frame element (22) having a first end (24) and a second end (26), at least one first attachment device (16) for attaching the first carrier element (18) to the fuselage structure (6) or to an element coupled with the fuselage structure (6), at least one first coupling device (34, 100) mounted to the first end (24) for coupling the first carrier element (18) to the at least one frame element (22), and at least one second coupling device (42) mounted to the second end (26) for coupling the second carrier element (20, 44) to the at least one frame element (22), wherein the at least one frame element (22) is adapted for holding at least one component (4) to be installed in the interior, wherein the at least one first carrier element (18) is designed for coupling with the at least one first coupling device (34, 100), wherein the at least one second carrier element (20, 44) is designed for coupling with the at least one second coupling device (42), wherein one of the at least one first coupling device (34, 100) and the at least one second coupling device (42) is adapted to snap into the respective carrier element (18, 20, 44), to be moved relative to the respective end of the frame element (22) and to be arrested in a desired relative position thereto, and wherein the other of the at least one of the first coupling device (34, 100) and the second coupling device (42) comprises a fastening element (36) that is adapted to be sticked through the at least one frame element (22) and the respective coupling device (34, 42, 100).
  2. Structure system (2, 96) of claim 1, wherein the second coupling device (42) comprises an elongate compensation element (46) having an outer end (50), which protrudes away from the at least one elongate frame element (22), and an inner end (48), wherein the elongate compensation element (46) is slidably supported in the respective frame element (22) to move the outer end (50) into a variable distance from the second end (26), and wherein a first snap connector (52) is arranged on the outer end (50) that is complementary shaped to a second snap connector (54) arranged in the at least one second carrier element (20, 44).
  3. Structure system (2, 96) of claim 2, wherein the one of the first snap connector (52) and the second snap connector (54) is adapted to receive the other one of the first snap connector (52) and the second snap connector (54) in a first relative rotational position and to hold it in at least one second relative rotational position that is distinct from the first relative rotational position.
  4. Structure system (2, 96) of claim 2 or 3, wherein the second coupling device (42) comprises an arresting element (95) capable of arresting the elongate compensation element (46) relative to the second end (26).
  5. Structure system (2, 96) of claim 4, wherein the arresting element (95) is integrated into the elongate compensation element (46).
  6. Structure system (2, 96) of any of the preceding claims, Wherein one of the first carrier element (18) and the second carrier element (20, 44) comprises at least one rail (98), and wherein the respective coupling device (34, 42, 100) is adapted for being slidably supported by the at least one rail (98) to move the at least one elongate frame element (22) to the respective carrier element (18, 20, 44).
  7. Structure system (2, 96) of claim 6, wherein the respective coupling device (34, 42, 100) and the respective carrier element (18, 20, 44) are connectable independent from the rail (98), and wherein the at least one rail (98) is removable from the respective carrier element (18, 20, 44) after connecting the respective coupling device (34, 42, 100) and the respective carrier element (18, 20, 44).
  8. Structure system (2, 96) of any of the preceding claims, wherein a plurality of consecutive frame elements (22) are connectable through at least one profile component (40) that extends along a plurality of first ends (24) or a plurality of second ends (26).
  9. Structure system (2, 96) of any of the preceding claims, wherein the first attachment device (16) is connectable to or integratable into a cabin seat rail (14) at a bottom side, such that the at least one frame element (22) is placeable underneath and is couplable with the seat rail (14).
  10. Method for mounting structural and equipment components (4) to a fuselage structure in an interior of an aircraft (116), comprising the steps: providing at least one frame element (22) having a first end (24) and a second end (26), attaching at least one component (4) on the at least one frame element (22), moving the at least one frame element (22) into the fuselage structure (6), coupling at least one first coupling device (34, 100) mounted to the first end (24) to a first carrier element (18) attached to the fuselage structure (6) through at least one first attachment device (16), and coupling at least one second coupling device (42) mounted to the second end (26) to a second carrier element (20, 44) attached to the fuselage structure (6), wherein the coupling of one of the at least one first coupling device (34, 100) and the at least one second coupling device (42) includes a snapping into the respective carrier element (18, 20, 44), to be moved relative to the respective end (24, 26) of the frame element (22) and to be arrested in a desired relative position thereto; and wherein the other of the at least one of the first coupling device (34, 100) and the second coupling device (42) comprises a fastening element (36) that is adapted to be sticked through the at least one frame element (22) and the respective coupling device (34, 42, 100).
  11. Method according to claim 10, further comprising sliding an elongate compensation element (46) at the second coupling device (42), which elongate compensation element (46) having an outer end (50) protruding away from the respective frame element (22) and an inner end (48), to move the outer end (50) into a distance from the second end (26), such that a first snap connector (52) arranged on the outer end (50) reaches a complementary shaped second snap connector (54) arranged in the at least one second carrier element (20, 44), and snapping the first snap connector (52) into the second snap connector (54).
  12. Vehicle (116), comprising a fuselage structure (6), at least one component (4) and at least one structure system (2, 96) according to any of the claims 1 to 9 for attaching the at least one component (4) to the fuselage structure (6).
  13. Vehicle (116) according to claim 12, wherein the at least one component (4) comprises a fluid pipe, a duct, or an electric line.
  14. Vehicle (116) according to claim 12 or 13, wherein the vehicle is an aircraft (116), and wherein the structure system (2, 96) is adapted to arrange the at least one component (4) in a triangle region of the aircraft (116).

Description

Technical field The invention relates to a structure system for installation into a fuselage structure in an interior of an aircraft, an installation method as well as an aircraft having at least one such structure system. Background of the invention Commercial aircraft with a fuselage structure and a cabin created therein usually comprise a large variety of installation equipment. This may include, besides others, cabin monuments, passenger seats, in-flight entertainment equipment, stowage compartments and so on. Overhead stowage compartments, for example, are often attached to a framework structure in an upper region of the respective cabin. Often, they are brought into the cabin part by part and are installed one after another. Manufacturing-induced dimensional deviations are compensated by suitable adjustment means, such that the stowage compartments create a harmonic and straight appearance. However, further types of installation equipment can be found inside the interior of the fuselage that are not visible for a passenger, for example system equipment in an underfloor region, i.e. underneath the cabin, for example in the so-called triangle region. The triangle region is arranged between a cargo compartment and the fuselage structure underneath the cabin floor and may exemplarily comprise a plurality of ducts, pipes, and electrical lines. Often, these components are provided one after another into the aircraft and are attached to structural elements in the triangle region, such as the fuselage structure or lateral delimitation of the cargo compartment. Dedicated holders need to be provided and attached and the system components are coupled with the holders directly inside the fuselage. Since the available space is cramped, this part of the installation is cumbersome and time-consuming. Also, providing a plurality of holders for integration into structural elements requires a plurality of different brackets, tools, and other means for an efficient and quick installation. US 8 770 532 B2 relates to a cable retaining ring including a base having at least one mounting opening or at least one mounting projection for connecting the cable retaining ring to a cable support tray, an elongate interior defining a cable retention region, a gap through the ring for allowing a cable to be placed into or removed from the interior, and a slide mounted on the ring and shiftable between a first position substantially blocking the gap to prevent the cable from being placed into or removed from the interior and a second position unblocking the gap. US 9 077 167 B2 relates to an aircraft raceway mounting apparatus comprising an attachment formation for attachment of the apparatus to an aircraft structure, a raceway receiving formation for receiving a raceway, the raceway receiving formation comprising a snap fit formation for retention of a raceway. An aircraft raceway clamping apparatus comprising a concave raceway receiving formation having a raceway support region and a mouth, a bridge member configured to at least partially span the mouth, a clamping member movably mounted to the bridge member to advance into the mouth. Summary of the invention It is thus an object of the invention to provide a mounting system or the like for mounting components into an interior structure of an aircraft or an improved method for installing equipment components into the interior structure of the aircraft. This object is met by the structure system having the features of independent claim 1. Advantageous embodiments and further improvements may be gathered from the sub claims and the following description. According to the invention a structure system for installation into a fuselage structure in an interior of an aircraft is proposed, the system comprising at least one first carrier element, at least one second carrier element, at least one elongate frame element having a first end and a second end, at least one first attachment device for attaching the first carrier element to the fuselage structure or to an element coupled with the fuselage structure, at least one first coupling device mounted to the first end for coupling the first carrier element to the at least one frame element, and at least one second coupling device mounted to the second end for coupling the second carrier element to the at least one frame element, wherein the at least one frame element is adapted for holding at least one component to be installed in the interior, wherein the at least one first carrier element is designed for coupling with the at least one first coupling device, wherein the at least one second carrier element is designed for coupling with the at least one second coupling device, and wherein one of the at least one first coupling device and the at least one second coupling device is adapted to snap into the respective carrier element, to be moved relative to the respective end of the frame element and to be arrested in a desired relative positio