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EP-4174352-B1 - MODULAR LINE ASSEMBLY FOR INSTALLATION IN AN AIRCRAFT FUSELAGE

EP4174352B1EP 4174352 B1EP4174352 B1EP 4174352B1EP-4174352-B1

Inventors

  • Albers, Frederik
  • Pawellek, Sonja
  • SCHNEIDER, FRANK

Dates

Publication Date
20260506
Application Date
20211028

Claims (14)

  1. A modular line assembly (2) for installation in an aircraft fuselage (50), comprising: - a first line section (4) having a first diameter (D1), - at least one second line section (6) having a second diameter (D2), - a set of first line brackets (8), and - a set of second line brackets (10, 38, 47), wherein the first line brackets (8) comprise a first receiving space (12) designed for holding the first line section (4) and a first support portion (14) for attaching the first line brackets (8) to a structural part (16) of the fuselage (50), wherein the first receiving space is designed for enclosing the first line section; and the first line brackets are enclosing the first line section for supporting the first line section on the fuselage, wherein the second line brackets (10, 38, 47) comprise a second receiving space (18, 19) designed for holding the at least one second line section (6) and a second support portion (20, 21) for attaching the second line brackets (10, 38, 47) to the first line section (4), wherein at least one second line section (6) comprises the same or higher flexibility than the first line section (4), and wherein the at least one second line section (6) is attached to the first line section (4) through a plurality of second line brackets (10, 38, 47) that are arranged at a distance to and are independent from the first line brackets (8).
  2. Modular line assembly (2) according to claim 1, wherein at least one second line bracket (10, 38, 47) is arranged between two consecutive first line brackets (8).
  3. Modular line assembly (2) according to claim 1 or 2, wherein the at least one second line section (6) comprises at least one bend (24) in an overlapping region (22) with one of the first line brackets (8) and/or another component (26, 28).
  4. Modular line assembly (2) according to any of the preceding claims, wherein the first diameter (D1) exceeds the second diameter (D2).
  5. Modular line assembly (2) according to any of the preceding claims, wherein the second line brackets (10, 38, 47) comprise a clamp that encloses the first line section (4) in a plier-like manner.
  6. Modular line assembly (2) according to claim 5, wherein the second line brackets (10, 38, 47) comprise a stiction layer (41) in direct contact with a surface (30) of the first line section (4).
  7. Modular line assembly (2) according to any of the preceding claims, wherein the second line brackets (10, 38, 47) are designed for holding a plurality of second line sections.
  8. Modular line assembly (2) according to any of the preceding claims, wherein the second line brackets comprise at least one snap-in connector for holding the at least one second line section.
  9. Modular line assembly (2) according to any of the preceding claims, wherein the second receiving space (18, 19) and the second support portion (20, 21) are provided in a base component (39) and a top component (44), wherein the base component (39) and top component (44) are connectable to each other through a releasable connector (42).
  10. Modular line assembly (2) according to any of the preceding claims, wherein the first line section (4) comprises a vacuum pipe, and wherein the at least one second line section (6) comprises at least one water hose.
  11. Modular line assembly (2) according to any of the preceding claims, wherein the first line section (4) is substantially rigid.
  12. Modular line assembly (2) according to any of the preceding claims, wherein at least one of the at least one second line bracket (10) allows a relative motion of the second line section (6) along a main extension direction of the second line section (6).
  13. An aircraft (48), comprising a fuselage (50) having an interior space, and at least one modular line assembly (2) according to any of the preceding claims.
  14. A method for installing a first line section (4) and at least one second line section (6) in a fuselage (50) of an aircraft (48), comprising: attaching a first line section (4) having a first diameter (D1) to a structural part (16) of the fuselage (50) through first line brackets (8), which comprise a first receiving space (12) designed for holding the first line section (4) and a first support portion (14) for attaching the first line brackets (8) to the structural part (16), wherein the first receiving space is designed for enclosing the first line section; and the first line brackets are enclosing the first line section for supporting the first line section on the fuselage, attaching at least one second line section (6) having a second diameter (D2) to the first line section (4) through second line brackets (10, 38, 47), which comprise a second receiving space (18, 19) designed for holding the at least one second line section (6) and a second support portion (20, 21) for attaching the second line brackets (10, 38, 47) to the first line section (4), wherein at least one second line section (6) comprises a higher flexibility than the first line section (4), and wherein the at least one second line section (6) is attached to the first line section (4) through a plurality of second line brackets (10, 38, 47) that are arranged at a distance to and are independent from the first line brackets (8).

Description

Technical field The invention relates to a line assembly for installation in an aircraft fuselage, an aircraft as well as a method for installing a first line section and at least one second line section in an aircraft. Background of the invention In common commercial aircraft usually galley and sanitary equipment is installed. These require a potable water system for providing fresh water in a sufficient amount and quality. The potable water is commonly stored in a centralized water tank and is distributed via a pipe network. In conventional system architectures stainless steel or titanium pipes having a diameter between 12,7 mm and 19,05 mm (0,5 inches and 0,75 inches) are used. However, high and low pressure potable water pipes are known, which are based on flexible hoses from a plastic material, such as PEEK, wherein the high pressure hoses comprise an outer diameter of e.g. 6 mm. Furthermore, usually a vacuum toilet system is installed, based on a pneumatic transport system, which serves for the hygienic disposal of human waste. For this, the differential pressure between the cabin and outside air is used to convey waste through a titanium pipe, which may comprise a diameter of 50,8 mm (2 inches), to a central waste tank. Still further, usually a waste-water system is installed, which is used to drain waste-water, e.g. from wash basins, via the heated drain masts overboard. Although potable water lines and pipework of the vacuum toilet system are laid in parallel between the water/waste storage tanks and the lavatory monuments, each of these sub-system installations is mounted separately to the aircraft structure with its own brackets. This results in a relatively high number of interface points to the aircraft structure. In case of customer-specific monument positions due to individual cabin layouts, each of these sub-systems needs to be adapted to the new location with a correspondingly high level of effort separately. Above-mentioned water supply hoses allow to reduce the installation effort, weight, and complexity. On the one hand, the elastic properties of such hoses are of high advantage for the installation process. On the other hand, they may require modified bracket distances instead of using conventional bracket distances, which are specified by the spacing between structural elements in the aircraft fuselage, e.g. frame or z-strut spacing. Overall, the common installation method induces high costs in terms of aircraft design and production due to the required installation and customization effort. EP 3 385 163 A1 and US 10,822,774 B2 show an aircraft comprising a highpressure water supply and distribution system. US 2018/0277285 A1 relates to non-conductive support stands and, according to its abstract, provides a support stand made of a non-conductive material and having a saddle, pedestal and a base used to support objects. The pedestal supports the saddle and the base supports the pedestal. The saddle has a support member used to support objects and one or more flanges used to support objects. The saddle, pedestal and base are formed of a non-conductive material. US 4063315 A1 relates to a vacuum toilet system and, according to its abstract, provides a vacuum flush waste disposal system for aircraft; the required vacuum is acquired at altitude through the differential pressure between the aircraft cabin pressure and the ambient pressure above approximately 15,000 feet. When the aircraft is below this altitude or on the ground, the vacuum is provided by a blower. For flushing the toilet bowl, a timing device is initially actuated and functions: to introduce a recirculated flush fluid into a flush ring in the upper portion of the toilet bowl; and to open a drain in the lower portion of the toilet bowl, leading to the vacuum waste line; the waste and flush water are rapidly propelled through the waste line towards a centrally located holding tank, by the differential pressure acting upon it. Once in the holding tank, the waste fluid is filtered out for further use as the recirculated flush fluid. Summary of the invention The object of the invention is to propose an improved installation for lines or similar system installations on board commercial aircraft to avoid at least some of the afore-mentioned constraints. The object is met by a line installation assembly having the features of independent claim 1. Advantageous embodiments and further improvements may be gathered from the subclaims and the following description. A modular line assembly for installation in an aircraft fuselage is proposed, the assembly comprising a first line section having a first diameter, at least one second line section having a second diameter, a set of first line brackets, and a set of second line brackets, wherein the first line brackets comprise a first receiving space designed for holding the first line section and a first support portion for attaching the first line brackets to a structural part of the fusel