Method for assembling landing gear fairing systems and landing gear components

Abstract

Landing gear fairing system and method for assembling landing gear components. The present invention relates to a landing gear fairing system comprising an annular wall having fastening means, first and second split coupling elements, and first and second connecting members, and a method for assembling landing gear components. Using the present invention, components can be attached to the landing gear without removing the wheels, access to other landing gear components is facilitated, and the cost and time required for maintenance are reduced.

Description

Technical Field

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[0001] The present invention relates to an aircraft landing gear fairing system and a method of assembling the landing gear fairing system.

Summary of the Invention

Problems to be Solved by the Invention

[0002] The aircraft landing gear fairing system aims to reduce the air resistance seen in the landing gears currently installed on most aircraft, as it is the subject of industrial design registration number BR 30 2017 003006 8, and consequently reduce the losses and noise generated during landing and takeoff.

[0003] The reduction of drag due to low turbulence, i.e., the reduction of molecular shear associated with fluid adhesion by counter vortices generated at the upper rear of the fairing system and the combination of the landing gear, enables the retention of energy and, through the use of appropriate materials, until the use of fossil fuels, hydrogen fuels, etc. and the use of electric aircraft, it is possible to obtain overall operational efficiency. Appropriate materials are those with characteristics that satisfy a wide range of technical aspects in the public institution's certification process, for example, mechanical stress, thermal, fatigue, corrosion, etc., and minimize the impact as much as possible by reducing these total additional loads as much as possible and excluding all other unnecessary things.

[0004] One of the problems initially proposed and observed in relation to the structure of the fairing system shown in the aforementioned design registration is that for the attachment of the landing gear in question, many parts of the already installed landing gear need to be removed, and in addition to the lack of appropriate fixing means, it takes a lot of time and a great burden to implement, and in some cases, it may even become impossible to execute.

[0005] Therefore, while the use of the aforementioned aircraft landing gear fairing system is highly advantageous, for the reasons mentioned above, a method is needed to assemble this system without removing multiple parts and without consuming time and resources. [Means for solving the problem]

[0006] The aforementioned objective is achieved by using a fairing system comprising an annular wall having a fixing means, at least one split coupling element, and at least one connecting member. [Effects of the Invention]

[0007] One of the main advantages of the present invention is that it is possible to attach components to the landing gear without removing the wheels, facilitating access to other components of the landing gear and reducing the cost and time required for maintenance.

[0008] Another important advantage of the present invention is the reduction of installation costs, manufacturing costs, and the reduction of the additional final total weight after the components of the landing gear have been installed on the aircraft.

[0009] Another relevant advantage of using the present invention is that air resistance is reduced, and as a result, losses and noise that occur during landing and takeoff are reduced.

[0010] The present invention also has the additional feature of reducing manufacturing costs during mass production due to its advantageous configuration, which requires fewer manufacturing steps for the device. [Brief explanation of the drawing]

[0011] [Figure 1] This is a front view showing the conventional, publicly available, current technology of the landing gear. [Figure 2] This is an exploded perspective view showing a preferred embodiment of the landing gear and fairing system of the present invention. [Figure 3-6]These are perspective views of the assembly of a preferred embodiment of the landing gear fairing system of the present invention, i.e., from a completely disassembled state (Figure 3) to a completely assembled state (Figure 6). [Figure 7] This is a perspective view showing a preferred embodiment of the landing gear with a landing gear fairing system of the present invention. [Figure 8] This is a perspective view showing a preferred embodiment of the landing gear with a landing gear fairing system of the present invention. [Modes for carrying out the invention]

[0012] The present invention will be described in further detail below with reference to the aforementioned drawings.

[0013] Figure 1 shows a conventional landing gear, which is composed of numerous parts, including the wheels and tire sets, that must be removed during maintenance and reassembly. In particular, with this type of landing gear, when the landing gear is operated, so-called air resistance is created. This is a phenomenon seen in most aircraft currently in operation, and it increases fuel consumption and generates considerable noise during landing and takeoff.

[0014] Figure 2 shows a preferred embodiment of the landing gear fairing system of the present invention and how it should be attached to the landing gear.

[0015] Figures 3-6 show the assembly steps of a preferred embodiment of the landing gear fairing system of the present invention. As can be seen in the illustrations, the structure of the fairing system of the present invention has a small number of parts, making it easy to manufacture, assemble, and maintain.

[0016] As shown in the illustration, the assembly process of the fairing system is carried out from the innermost part to the outermost part of the system. The innermost part is formed by at least one split coupling (2, 3), which is divided into an upper part (2a, 3a) and a lower part (2b, 3b) and when joined, as shown in FIGS. 3 and 4, the upper and lower parts surround the axle of the landing gear.

[0017] Subsequently, as shown in FIG. 5, at least one split coupling (2, 3) surrounding the axle of the landing gear is appropriately fixed to the connecting members (4, 5) at the rear of the fairing system by fixing projection parts (2c, 3c).

[0018] Finally, FIG. 6 shows the fairing system already fully assembled, with an approximately quarter - circular section of the annular housing (1) open. The annular housing (1) is provided with fixing means (1a, 1b) at the open end, which are connected to at least one coupling element (2, 3) and at least one connecting member (4, 5).

[0019] Optionally, the fairing system of the present invention comprises two or more split couplings (2, 3).

[0020] Optionally, the fairing system of the present invention comprises two or more connecting members (4, 5).

[0021] The couplings and connecting members used include all forms of couplings, connecting members, fixing fittings, etc. Non - exhaustive examples are bolts, nuts, studs, rivets, adhesives, welding, and fitting, etc.

[0022] As can be easily understood by those skilled in the art, it is also possible to carry out the assembly with a different series of procedures without departing from the scope of the present invention.

[0023] For example, those skilled in the art who have read the present disclosure may optionally start from the first configuration shown in FIG. 3, fix the fixing projection part (2c) of the first coupling element to the first connecting member (4), and then fix the fixing projection part (3c) of the second coupling element to the second connecting member (5). After that, connect the upper part (2a) of the first coupling element (2) to the lower part (2b), and connect the upper part (3a) of the second coupling element (3) to the lower part (3b).

[0024] FIGS. 3 to 5 enable visualization of the preferred shape of the fairing system, more precisely, the shape of the annular housing (1) adapted to receive the first and second coupling elements (2, 3), and the details of the fixing means (1a, 1b) at the ends of the annular housing (1) that enable the connection between the fixing projection parts (2c, 3c) and the first and second connecting members (4, 5).

[0025] The fixing means (1a, 1b), fixing projection parts (2c, 3c), and the first and second connecting members (4, 5), etc. shown in the drawings each have mounting holes provided for the annular housing (1), the first and second coupling elements (2, 3), and the first and second connecting members (4, 5) to be interconnected. However, other connection and coupling methods can also be used.

[0026] FIGS. 7 and 8 show the state where the coupling system is completely attached to the landing gear as in the preferred embodiment of the present invention.

[0027] It should be understood that the above embodiments are for illustrative purposes only, and various changes can be made without departing from the scope of the present invention defined by the appended claims.

Prior Art Documents

Patent Documents

[0028]

Patent Document 1

Claims

1. Landing gear fairing system, An annular housing (1) having fixing means (1a, 1b) at its circumferential ends, A split coupling element (2, 3) including upper parts (2a, 3a), lower parts (2b, 3b), and two fixing protrusions (2c, 3c), At least one connecting member (4, 5) and Equipped with, The fixing means (1a, 1b) of the annular housing (1) are connectable to the fixing projections (2c, 3c) and the at least one connecting member (4, 5). The at least one coupling element (2, 3) is attachable to the axis (A) of the landing gear between its respective upper (2a, 3a) and lower (2b, 3b) parts. Landing gear fairing system.

2. It has two bipartite coupling elements (2, 3), The fairing system according to claim 1.

3. It comprises two connecting members (4, 5), The fairing system according to claim 1 or 2.

4. A method for assembling a landing gear fairing system according to any one of claims 1 to 3, (a) The step of positioning the fairing system on the axle (A) of the landing gear such that the axle of the landing gear is positioned between the upper (2a, 3a) and lower (2b, 3b) of each of the at least one coupling element (2, 3), (b) Connecting the fixing means (1a, 1b) of the annular housing (1) to the fixing projections (2c, 3c) and the at least one connecting member (4, 5), Equipped with, How to assemble the landing gear fairing system.

5. Prior to step (a), the procedure includes the step of connecting at least one connecting member (4, 5) to the fixing projection (2c, 3c). The assembly method according to claim 4.

6. At least one connection is made by one of the following: bolts, nuts, studs, rivets, adhesives, welds, and mating. The assembly method according to any one of claims 1 to 5.

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