Flash FAL Track II

Abstract

Method for mounting an aircraft structure (10) on a mounting frame (1), wherein the mounting frame (1) is not part of an aircraft, and wherein structural parts and / or auxiliary structures of the aircraft structure (10) are mounted on the mounting frame (1) in one step, characterized in that the aircraft structure (10) is a wing structure and that acceptance procedures and / or acceptance tests of the wing structure (10) are carried out on the wing structure (10) fully assembled on the mounting frame (1).

Description

[0001] The present invention relates to a method for assembling an aircraft structure, a method for carrying out repair and / or maintenance work on an aircraft structure and an assembly and transport device for carrying out corresponding methods.

[0002] Generic designs known from the prior art are disclosed, for example, in DE 10 2009 023 391 A1, DE 10 2010 018 272 A1, DE 10 2009 023 393 A1, WO 2007 / 137 812 A1, DE 10 2009 023 401 A1, DE 10 2010 055 995 A1, DE 10 2009 023 400 A1, DE 10 2010 055 962 A1 and DE 10 2012 001 797 A1.

[0003] Methods for assembling aircraft structures onto aircraft are known from the prior art. For example, it is common practice to install devices and components of an aircraft structure or aircraft structure onto an aircraft to be assembled in a final assembly line (FAL) at an aircraft production facility. Devices, component structural parts, and / or auxiliary structures of the aircraft structure are installed directly on the aircraft or aircraft to be assembled. According to the prior art, acceptance tests of the individual components and connections of the aircraft structure are also carried out while the aircraft is fully assembled. The same applies to prior art methods for performing repair and / or maintenance work. Any necessary disassembly of individual components and / or connections is also carried out on the aircraft.

[0004] A disadvantage of the state of the art, such as DE 10 2009 023 391 A1, is that assembling the aircraft in the FAL requires a significant amount of time. This requires assembling all structural components and system devices within the FAL. This results in significant logistical and assembly effort. Similar disadvantages arise when performing repair and / or maintenance work on parts of the aircraft or aircraft structures.

[0005] The object of the present invention is therefore to provide an improved method for assembling aircraft structures and for carrying out corresponding repair and / or maintenance work on aircraft structures.

[0006] This object is achieved according to the invention by a method for mounting an aircraft structure on a mounting frame having the features of claim 1, wherein preferred embodiments are the subject of the subclaims.

[0007] According to claim 1, it is provided that the assembly frame is not part of an aircraft, and wherein structural parts and / or auxiliary structures of the aircraft structure are mounted to the assembly frame in one step. Structural parts and auxiliary structures can be components of the aircraft structure. A track or a carrier, for example, can be used as a structural part of the aircraft structure, and an A-frame, for example, can be used as an auxiliary structure. Mounting the aircraft structure to the assembly frame offers the advantage, for example, that the assembly frame can define the point or position in which structural parts and / or auxiliary structures are to be mounted. An appropriately designed assembly frame makes assembly work easier for the personnel through appropriate positioning.

[0008] According to the inventive embodiment of the method, the aircraft structure is a wing structure, and acceptance procedures and / or acceptance tests of the wing structure are carried out on the wing structure fully assembled on the assembly frame. This advantageously further reduces the time required for final assembly of the aircraft.

[0009] In a preferred embodiment, it is conceivable that, in a further step, systems, and / or devices, and / or electronics, and / or accessories, such as preferably sensors, cables, transmissions, and / or connecting parts, are mounted to the assembled structural parts and / or auxiliary structures and / or to the mounting frame. This advantageously makes it possible to also attach subordinate components of the wing structure to the mounting frame or to the wing structure mounted on the mounting frame, with the aforementioned advantages during assembly.

[0010] In a further preferred embodiment, it is conceivable that in a further step the structural parts, and / or auxiliary structures, and / or systems, and / or devices, and / or electronics, and / or accessories mounted directly or indirectly on the mounting frame are adjusted mechanically and / or electrically.

[0011] Advantageously, the adjustment of the aforementioned components does not have to be carried out within the FAL, which can further shorten the final assembly of the aircraft. In a further preferred embodiment, it is conceivable that in a further step the fully assembled wing structure with or without a mounting frame is attached to a transport device with or without auxiliary structures and / or stiffeners.

[0012] Mounting the wing structure to the transport device can bring corresponding assembly work, which would otherwise be required on the FAL, forward in the production process, so that the work no longer needs to be performed during final assembly. This further shortens the final assembly itself. Using the optional auxiliary structures, it is advantageous to better align the wing structure and position it for assembly. Alternatively or additionally, the aircraft structure is fixed or secured for possible transport, preventing potential damage during transport.

[0013] In a further preferred embodiment, it is conceivable that in a further step the fully assembled wing structure is transported on the transport device with auxiliary structures to an aircraft assembly line.

[0014] This advantageously allows the wing structure to be transported without negatively impacting the wing structure. It is also possible to have the assembly of the wing structure take place at a spatial and temporal distance from the final assembly of the aircraft. This allows the advantages mentioned above regarding shortening the final assembly of the aircraft to be realized. It is also conceivable that economies of scale could be realized through centralized production of the corresponding wing structures, whereby the wing structures can be fed to a variety of different aircraft assembly lines.

[0015] In a further preferred embodiment, it is conceivable that in a further step the fully assembled wing structure is mounted on the aircraft, wherein mechanical, and / or electrical, and / or hydraulic interfaces are connected to one another.

[0016] Interfaces here refer to corresponding connecting elements on the wing structure and the rest of the aircraft, through which the functional and / or static connection between the wing structure and the aircraft is established. The interfaces can also be intended for the operation of movable devices on the wing structure.

[0017] Of course, it is conceivable that the interfaces on the wing structure side are mounted in one step during the assembly of the wing structure on the mounting frame.

[0018] When mounting the fully assembled wing structure on the aircraft, it is further conceivable in a preferred embodiment that no or minimal adjustments, and / or acceptance procedures, and / or acceptance tests, and / or adjustment tests of the wing structure are carried out, and / or that the auxiliary structures are dismantled after mounting the fully assembled wing structure.

[0019] Such tests and / or procedures or adjustments can advantageously be performed beforehand during the assembly of the wing structure, outside of the final assembly of the aircraft. This results in a corresponding time advantage during the final assembly of the aircraft.

[0020] The present invention further relates to a method for carrying out repair and / or maintenance work on a wing structure of an aircraft, wherein • in one step, the wing structure to be repaired and / or maintained is attached to a mounting frame and / or to a transport device, or an auxiliary structure is attached to the wing structure (10) to be repaired and / or maintained; • in a further step, another wing structure is mounted on the aircraft instead of the wing structure to be repaired and / or maintained; and • in a further step, the wing structure to be repaired and / or maintained is repaired and / or maintained.

[0021] The previously described advantages of the present invention relate to the assembly of a structure and can also apply to a possible disassembly of the structure. During the operation of an aircraft, this can relate to the repair and / or maintenance work mentioned as examples. For this reason, these works, if they include corresponding assembly or disassembly steps, are also encompassed by the present invention.

[0022] Advantageously, the aircraft can be used for further flight operations. It is not necessary for the aircraft to remain grounded and unflyable due to the repair and / or maintenance work being carried out.

[0023] All procedural steps whose order is not necessarily logically defined can of course also be carried out in a different order.

[0024] In preferred embodiments, it can be provided that the wing structure comprises at least one highlift, and / or at least one flap, and / or at least one spoiler, and / or at least one slat, and / or at least one wing half or one wing part, and / or an entire wing.

[0025] Depending on requirements, a more or less large part of a wing or parts thereof can be made available to a final assembly line or repaired and / or maintained.

[0026] The present invention is further directed to an assembly and / or transport device for carrying out a method at least according to claim 4 and / or a method at least according to claim 8, wherein at least one wing structure can be mounted in the transport device, and wherein the transport device comprises at least one base plate.

[0027] The base plate serves as a foundation for securely fixing the wing structure or the mounting frame of the wing structure.

[0028] In a further preferred embodiment, it is conceivable that the transport device comprises at least one adjustable strut for coupling the wing structure to the transport device and / or for coupling the wing structure to itself, and / or that the transport device comprises at least one holding point for transport and / or assembly.

[0029] The adjustable strut can advantageously be designed to enable sufficiently precise positioning of the wing structure for assembly. This further accelerates the corresponding positioning of the wing structure during final assembly of the aircraft. Using the strut to couple the wing structure to itself ensures that the geometry of the structure is maintained or kept sufficiently constant with regard to the interface and assembly.

[0030] Further details and advantages of the invention are shown in the following figures. Fig. 1: Aircraft structure on mounting frame during assembly process; and Fig. 2: Aircraft structure on transport device.

[0031] Fig. 1 shows an aircraft structure 10 on a mounting frame 1, wherein the mounting frame 1 is not part of an aircraft, but remains in the assembly area as an assembly aid. Fig. In the situation shown in Figure 1, a structural part or an auxiliary structure of the aircraft structure 10 is assembled by assembly personnel.

[0032] In the illustrated embodiment, this may be an A-frame 3 and a flap 4, which are assembled by the assembly personnel. As can be seen from the figure, tracks 2 of a high-lift assembly unit can also be assembled using the same method.

[0033] The embodiment of the Fig. 1 deals with an integrated unit consisting of structural parts and pre-installed system components. The integrated unit can be assembled directly onto the wing of an aircraft in the final assembly line (FAL) of an aircraft assembly line. Thus, no further subordinate assembly steps in the FAL are necessary beforehand.

[0034] The integrated unit can thus, as in the example of the Fig. 1, represent a general part of a wing. The example of the Fig. 1 shows a landing flap system, in particular a trailing edge (flap system) of a medium passenger aircraft.

[0035] Such a structural system integrated high-lift assembly unit can be referred to as an integrated HL unit. The integrated HL unit can be mounted directly on the wing of an aircraft, and any necessary additional mechanical or electrical separation points of the system components, such as the transmission or electronics, can then be connected.

[0036] For such exemplary HL units, variants of varying complexity are possible.

[0037] In a first variant, an HL unit is conceivable, in which two carriers with integrated devices and auxiliary structures such as A-frames 3 are provided. A landing flap can be already mounted and adjusted, and spoiler flaps and actuators can also be already mounted and adjusted.

[0038] A second variant is conceivable, with an HL unit comprising two supports with integrated equipment and auxiliary structure. A landing flap may already be mounted and adjusted.

[0039] In a third variant, an HL unit is conceivable in which only carriers with integrated devices are provided.

[0040] The variants mentioned above have in common the integration of devices into the structure as well as the calibration and acceptance testing. These steps can be performed by the aircraft structure supplier 10 prior to delivery to FAL.

[0041] Devices 5 that can be mounted on the assembly frame 1 as part of the aircraft structure 10 during the assembly process include GRAs (Geared Rotary Actuators), gearboxes (DDGBs), drive units (PCUs, etc.), and drive shafts / transmissions in the A-frame 3. The A-frame 3 can be mounted on the tracks 2 or integrated into them.

[0042] Furthermore, it is possible to assemble electronics or electronic parts or control units 6 as parts of the aircraft structure 10 according to the method.

[0043] Electrical connectors such as plugs and / or mechanical connectors such as bolts are conceivable as interface parts for connecting the aircraft structure 10 to an aircraft.

[0044] Fig. 2 shows an aircraft structure 10 which is arranged on a transport device 20. The transport device 20 has a base plate 21 on which 3D supports 22 are provided for supporting the aircraft structure 10. In the illustrated embodiment of the Fig. 2, mounting plates 23 are arranged within the aircraft structure 10, on which, for example, assembly personnel can stand. The mounting plates 23 can have access passages for better access by the assembly personnel. By means of the adjustable struts 24, it is possible to precisely and firmly couple the aircraft structure 10 to the transport device 20 and to stabilize the aircraft structure 10.

[0045] Furthermore, the transport device 20 may be provided with holding points 25 for a crane or for connecting to a crane, for example, in an upper region of the transport device 20. Lifting points or lower holding points 26 may also be provided for using the transport device 20 in conjunction with, for example, a lifting truck.

Claims

[1] Method for mounting an aircraft structure (10) on a mounting frame (1), wherein the mounting frame (1) is not part of an aircraft, and wherein structural parts and / or auxiliary structures of the aircraft structure (10) are mounted on the mounting frame (1) in one step, characterized by that the aircraft structure (10) is a wing structure and that acceptance procedures and / or acceptance tests of the wing structure (10) are carried out on the wing structure (10) fully assembled on the assembly frame (1) [2] Method according to claim 1, characterized by that in a further step, systems, and / or devices, and / or electronics, and / or accessories, such as preferably sensors, cables, transmissions and / or connecting parts, are mounted to the mounted structural parts and / or auxiliary structures and / or to the mounting frame (1). [3] Method according to claim 1 or 2, characterized bythat in a further step the structural parts, and / or auxiliary structures, and / or systems, and / or devices, and / or electronics, and / or accessories mounted directly or indirectly on the mounting frame (1) are adjusted mechanically and / or electrically. [4] Method according to one of the preceding claims, characterized by that in a further step the fully assembled wing structure (10) with or without mounting frame (1) is attached to a transport device (20) with or without auxiliary structures and / or stiffeners. [5] Method according to claim 4, characterized by that in a further step the fully assembled wing structure (10) is transported on the transport device (20) with auxiliary structures to an aircraft assembly line. [6] Method according to one of the preceding claims, characterized bythat in a further step the fully assembled wing structure (10) is mounted on the aircraft, wherein mechanical, and / or electrical, and / or hydraulic interfaces are connected to one another. [7] Method according to claim 6, characterized by that when assembling the fully assembled wing structure (10) on the aircraft, no or minimal adjustments, and / or acceptance procedures, and / or acceptance tests, and / or adjustment tests of the wing structure (10) are carried out, and / or that after assembling the fully assembled wing structure (10), the auxiliary structures are dismantled. [8] Method for carrying out repair and / or maintenance work on a wing structure (10) of an aircraft, wherein • in one step, the wing structure (10) to be repaired and / or maintained is attached to a mounting frame (1) and / or to a transport device (20), or an auxiliary structure is attached to the wing structure (10) to be repaired and / or maintained; • in a further step, another wing structure (10) is mounted on the aircraft instead of the wing structure (10) to be repaired and / or maintained; and • in a further step, the wing structure (10) to be repaired and / or maintained is repaired and / or maintained. [9] Method according to claim 8, characterized by that the wing structure comprises at least one highlift, and / or at least one flap, and / or at least one spoiler, and / or at least one slat, and / or at least one wing half or one wing part, and / or an entire wing. [10] Transport device (20) for carrying out a method at least according to claim 4 and / or a method at least according to claim 8, wherein at least one wing structure (10) is attachable to the transport device (20), and wherein the transport device (20) comprises at least one base plate (21) [11] Transport device (20) according to claim 10, characterized by that the transport device (20) comprises at least one adjustable strut (24) for coupling the wing structure (10) to the transport device (20) and / or for coupling the wing structure (10) to itself, and / or that the transport device (20) comprises at least one holding point (25, 26) for transport and / or assembly.

Images