Hanging and mounting bracket for airplane power distribution unit body

Abstract

The utility model belongs to the technical field of airplane power distribution unit body suspension installation design, and particularly relates to an airplane power distribution unit body suspension installation support which comprises an airplane body structure connecting edge, a power distribution unit body connecting edge and an inclined supporting edge. The machine body structure connecting edge is vertically connected to a machine body structure through a bolt, and an interference avoiding groove is designed in the machine body structure connecting edge and used for avoiding an interference structure existing on the machine body structure. The root of the power distribution unit body connecting edge is transversely connected to the upper end of the machine body structure connecting edge and is perpendicular to the machine body structure connecting edge, and the upper part is connected with the power distribution unit body through bolts to fix the power distribution unit body; the two ends of the inclined supporting edge are connected with the lower end of the machine body structure connecting edge and the top end of the power distribution unit body connecting edge and are obliquely supported between the machine body structure connecting edge and the power distribution unit body connecting edge to form a stable triangular supporting structure. The inclined supporting edge is provided with an electric wire interface for wiring of the power distribution unit body, and the wiring of the power distribution unit body is restrained and structured.

Description

Technical Field

[0001] This application belongs to the technical field of aircraft power distribution unit suspension installation design, specifically relating to an aircraft power distribution unit suspension installation bracket. Background Technology

[0002] The power distribution unit on an aircraft is responsible for power distribution or control and drive functions in its area, ensuring normal power distribution to electrical equipment in the area, and playing an important role in the aircraft's various functional performances.

[0003] The weight of an aircraft's electrical distribution unit is generally between 10 and 20 kg, and it is quite large. Due to redundancy safety requirements, a large number of units are installed on aircraft, covering areas such as the nose, fuselage, and wings.

[0004] Aircraft electrical distribution units are typically mounted on equipment racks. However, in areas with limited space, such as pressurized compartments and the nose landing bay, equipment racks cannot be installed. In these cases, the electrical distribution units need to be fixed to the fuselage structure using suspension mounting brackets. The suspension mounting brackets must be designed to fit the dimensions of the electrical distribution units to meet installation requirements and to secure them to the fuselage structure. Typical fuselage structures include frames and panels, often containing numerous beams, stringers, and stiffeners, which can affect the stability of the suspension mounting brackets. Furthermore, in areas with severe vibration, the suspension mounting brackets must be designed with sufficient rigidity to support the components and be easy to install and remove for frequent inspection and maintenance of the electrical distribution units. However, current suspension mounting brackets for aircraft electrical distribution units do not adequately meet all the installation needs of the units. Therefore, this application is submitted. Utility Model Content

[0005] The purpose of this application is to provide a suspension mounting bracket for an aircraft power distribution unit to overcome or mitigate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] An aircraft power distribution unit suspension mounting bracket includes an airframe structure connecting side, a power distribution unit connecting side, and an oblique support side;

[0008] The connecting edge of the fuselage structure is vertically connected to the fuselage structure by bolts, and interference avoidance grooves are designed on it to avoid interference structures existing on the fuselage structure;

[0009] The power distribution unit is horizontally connected to the upper end of the body structure connection edge at the root of the connection edge, perpendicular to the body structure connection edge, and the power distribution unit is fixed by bolts at the top.

[0010] The two ends of the diagonal support are connected to the lower end of the body structure connection side and the top end of the power distribution unit connection side. The diagonal support is located between the body structure connection side and the power distribution unit connection side, forming a stable triangular support structure.

[0011] An electrical wiring interface is provided on the slanted support side for the power distribution unit to run cables.

[0012] According to at least one embodiment of this application, in the above-described aircraft power distribution unit suspension mounting bracket, the fuselage structure includes a frame and wall panels.

[0013] According to at least one embodiment of this application, in the above-mentioned aircraft power distribution unit suspension mounting bracket, the interference structures existing on the fuselage structure include beams, stringers, and stiffeners.

[0014] According to at least one embodiment of this application, in the above-mentioned aircraft power distribution unit suspension mounting bracket, the fuselage structure connecting side, the power distribution unit connecting side, and the oblique support side are integrally formed structures.

[0015] According to at least one embodiment of this application, in the above-mentioned aircraft power distribution unit suspension mounting bracket, the fuselage structure connection side and the power distribution unit connection side are angular structures.

[0016] According to at least one embodiment of this application, in the above-mentioned aircraft power distribution unit suspension mounting bracket, multiple vertical ribs are provided inside the angle of the fuselage structure connection side and the power distribution unit connection side.

[0017] This application has at least the following beneficial technical effects:

[0018] A suspension mounting bracket for an aircraft power distribution unit is provided. The bracket is designed to form a stable support structure consisting of a fuselage structure connection side, a power distribution unit connection side, and an oblique support side. This structure suspends and fixes the power distribution unit, meeting the requirements for the rigidity and vibration resistance of the power distribution unit support. The bracket is designed to connect the power distribution unit and the fuselage structure with bolts for easy assembly and disassembly, meeting the needs of frequent inspection and maintenance of the power distribution unit. The fuselage structure connection side is designed with interference avoidance grooves to avoid interference structures such as beams, stringers, and stiffeners on the fuselage structure. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the aircraft power distribution unit suspension mounting bracket provided in the embodiments of this application;

[0020] in:

[0021] 1-Connecting edge of the machine body structure; 2-Connecting edge of the power distribution unit; 3-Diagonal support edge; 4-Electric wiring interface; 5-Vertical rib.

[0022] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0023] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0024] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms indicating direction used in this application description are used only to indicate relative direction or positional relationship; when the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "comprising" as used in this application description indicates that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, but does not exclude other elements or objects.

[0025] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0026] A type of aircraft power distribution unit suspension mounting bracket, such as Figure 1 As shown, it includes the body structure connection side 1, the power distribution unit body connection side 2, and the inclined support side 3.

[0027] The connecting edge 1 of the fuselage structure is vertically connected to the fuselage structure by bolts. It is designed with interference avoidance grooves to avoid interference structures such as beams, girder runners, and stiffeners present on the fuselage structure. The shape and location of the interference avoidance grooves can be determined based on the shape and distribution of the interference structures. The number and distribution of bolt holes on the connecting edge 1 of the fuselage structure can be determined according to the connection strength requirements.

[0028] The power distribution unit connection edge 2 is horizontally connected to the upper end of the body structure connection edge 1, perpendicular to the body structure connection edge 1. The power distribution unit is then fixed by bolts. The dimensions of the power distribution unit connection edge 2 are designed according to the dimensions of the power distribution unit, and the number and distribution of bolt holes on it can be determined according to the connection strength requirements.

[0029] The two ends of the diagonal support edge 3 are connected to the lower end of the body structure connection edge 1 and the top end of the power distribution unit connection edge 2. The diagonal support is located between the body structure connection edge 1 and the power distribution unit connection edge 2, forming a stable triangular support structure to meet the rigidity requirements of the power distribution unit support and the vibration resistance.

[0030] An electrical wiring interface 4 is provided on the inclined support edge 3, which allows the power distribution unit to run its wiring. This allows the wiring of the power distribution unit to be constrained and organized, without the need for additional wiring structures such as wire harness clips.

[0031] To further enhance the rigidity, stability, and vibration resistance of the structure, the body structure connecting edge 1, the power distribution unit connecting edge 2, and the diagonal support edge 3 can be designed as an integral molded structure. The body structure connecting edge 1 and the power distribution unit connecting edge 2 can be designed as an angular structure, and multiple vertical ribs 5 can be set inside the angular shape of the body structure connecting edge 1 and the power distribution unit connecting edge 2. The number and distribution of the vertical ribs 5 on the body structure connecting edge 1 and the power distribution unit connecting edge 2 can be designed according to the rigidity requirements of the mounting bracket.

[0032] The aircraft power distribution unit suspension mounting bracket disclosed in the above embodiments is designed with a stable support structure consisting of fuselage structure connecting edge 1, power distribution unit connecting edge 2, and oblique support edge 3 to suspend and fix the power distribution unit. This can meet the requirements of the rigidity and vibration resistance of the power distribution unit support. Furthermore, the design uses bolts to connect the power distribution unit and the fuselage structure for easy assembly and disassembly, which can meet the needs of frequent inspection and maintenance of the power distribution unit. The fuselage structure connecting edge 1, which connects to the fuselage structure, is designed with interference avoidance grooves to avoid interference structures such as beams, stringers, and ribs on the fuselage structure during connection.

[0033] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. Similar or identical parts between embodiments can be referred to mutually. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined to obtain new embodiments.

[0034] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A suspension mounting bracket for an aircraft power distribution unit, characterized in that, Includes the body structure connection edge (1), the power distribution unit body connection edge (2), and the oblique support edge (3); The connecting edge (1) of the body structure is vertically connected to the body structure by bolts, and an interference avoidance groove is designed on it to avoid interference structures existing on the body structure; The root of the power distribution unit body connection edge (2) is horizontally connected to the upper end of the body structure connection edge (1), perpendicular to the body structure connection edge (1), and the power distribution unit body is fixed by bolts above it; The two ends of the oblique support side (3) are connected to the lower end of the body structure connection side (1) and the top end of the power distribution unit body connection side (2), and the oblique support is between the body structure connection side (1) and the power distribution unit body connection side (2) to form a stable triangular support structure. An electrical wiring interface (4) is provided on the inclined support edge (3) for the power distribution unit to run the wiring.

2. The aircraft power distribution unit suspension mounting bracket according to claim 1, characterized in that, The body structure includes the frame and wall panels.

3. The aircraft power distribution unit suspension mounting bracket according to claim 1, characterized in that, Interference structures present in the body structure include beams, girder, and stiffeners.

4. The aircraft power distribution unit suspension mounting bracket according to claim 1, characterized in that, The body structure connecting edge (1), the power distribution unit connecting edge (2), and the oblique support edge (3) are integrally formed structures.

5. The aircraft power distribution unit suspension mounting bracket according to claim 1, characterized in that, The connecting edge (1) of the main body structure and the connecting edge (2) of the power distribution unit are angular structures.

6. The aircraft power distribution unit suspension mounting bracket according to claim 5, characterized in that, Multiple vertical ribs (5) are set inside the corner of the body structure connection edge (1) and the power distribution unit body connection edge (2).

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