CN114172093A

CN114172093A - Aircraft cable laying structure, aircraft and cable laying method

Info

Publication number: CN114172093A
Application number: CN202111298422.8A
Authority: CN
Inventors: 刘小洁; 张明; 张东华; 顾井峰; 刘倩
Original assignee: Beijing Electromechanical Engineering Research Institute
Current assignee: Beijing Electromechanical Engineering Research Institute
Priority date: 2021-11-04
Filing date: 2021-11-04
Publication date: 2022-03-11

Abstract

The invention provides an aircraft cable laying structure, an aircraft and a cable laying method, wherein the structure comprises a cable guide component and a fastening component, wherein the cable guide component has a shape consistent with the preset trend of a cable and is used for laying the cable in the cable guide component so as to maintain the preset trend of the cable; the fastening assembly is respectively connected with the cable guide assembly and the aircraft and used for fixing the cable guide assembly in the aircraft, and the cable is laid in the aircraft in a preset direction through the cooperation of the cable guide assembly and the fastening assembly. By applying the technical scheme of the invention, the technical problems of low cable laying efficiency, easy cloth misplacement or cloth leakage and easy bending and failure of cables in the prior art are solved.

Description

Aircraft cable laying structure, aircraft and cable laying method

Technical Field

The invention relates to the technical field of aircraft cable laying, in particular to an aircraft cable laying structure, an aircraft and a cable laying method.

Background

At present, need install the equipment of different grade type usually in the aircraft, wherein, aircraft measurement and control system's component equipment is many kinds, and is in large quantity, and the cloth station dispersion, and the operational reliability requires highly. The cable plays a crucial role in transmitting control signals, interconnecting components, and transmitting power as a nerve for numerous devices in the aircraft. With the development of aircraft, the increase of electrical equipment makes the cable scale larger and larger, and a more efficient cable laying method is urgently needed.

At present, the cable manufacturing and laying process in the aircraft is still completed according to the traditional process by relying on the experience of workers. When cabling is to be carried out in the cabin of an aircraft, workers are required to confirm the arrangement position of each cable and each connector on each aircraft and in each cabin. Firstly, if improper cable arrangement causes the anterior segment cable before cable junction to relax during installation, will lead to the back end cable to connect the grafting difficulty even connect and insert not go up, just need do over again this moment, hard waste time, production efficiency is low. Moreover, in each process of wiring, workers need to search a large number of technical files for arrangement, and therefore labor intensity is high and efficiency is low. In addition, workers face thousands of wire harnesses and joints, and cloth misplacement or cloth leakage is easily caused by fatigue. In addition, after the cable arrangement is finished, manual checking is still needed, and particularly when the aircraft is in mass production, the cable laying work is repeated and complicated, errors are easy to occur, and a large amount of manpower and material resources are wasted. On the other hand, if the installation space is limited due to the numerous devices in the aircraft, the cable may be laid in an abnormally crowded manner, causing the cable to be bent to different degrees, and causing the cable to fail in a serious case.

Disclosure of Invention

The invention provides an aircraft cable laying structure, an aircraft and a cable laying method, and can solve the technical problems that in the prior art, the cable laying efficiency is low, cloth is prone to being misplaced or leaked, and the cable is prone to being bent and losing efficacy.

According to an aspect of the present invention, there is provided an aircraft cabling arrangement, the arrangement comprising:

the cable guide assembly is in a shape consistent with the preset direction of the cable and is used for laying the cable in the cable guide assembly so as to maintain the preset direction of the cable;

and the fastening assembly is respectively connected with the cable guide assembly and the aircraft and is used for fixing the cable guide assembly in the aircraft, and the cable is laid in the aircraft in a preset direction through the matching of the cable guide assembly and the fastening assembly.

Further, the cable guide assembly comprises a hollow guide frame and a buckle, wherein the side wall of the hollow guide frame is provided with an opening, the buckle is arranged on the opening, and the buckle is used for opening to lay the cable in the hollow guide frame and closing to limit the cable in the hollow guide frame.

Further, fastening components include the slider and with slider complex slide rail of suit mode, the slider setting is on hollow guide frame, the slide rail setting is in the aircraft.

Further, the fastening assembly further comprises a fixing pin, a first connecting hole is formed in the sliding block, a second connecting hole is formed in the sliding rail, and the fixing pin penetrates through the first connecting hole and the second connecting hole to fix the sliding rail and the sliding block in the aircraft.

Further, the hollow guide frame is a 3D printing forming part.

According to another aspect of the present invention, there is provided an aircraft comprising a cabling arrangement as set out above.

According to a further aspect of the present invention, there is provided a cable laying method comprising:

determining the shape of the cable guide component according to the preset trend of the cable, and manufacturing the cable guide component according to the shape;

laying the cable within the cable guide assembly;

the cable guide assembly is secured within the aircraft by a fastener assembly.

Further, the cable direction subassembly includes cavity guide frame and buckle, lays the cable and includes in the cable direction subassembly:

opening the buckle to lay the cable in the hollow guide frame;

the clasp is closed to retain the cable within the hollow guide frame.

Further, fastening components includes slider and slide rail, and the slider setting is in cavity guide frame, fixes cable guide components including in the aircraft through fastening components:

installing a slide rail in an aircraft;

the slider is inserted into the slide rail to slide into place.

Further, the hollow guide frame is manufactured by means of 3D printing.

The technical scheme of the invention provides an aircraft cable laying structure, an aircraft and a cable laying method. Because the cable direction subassembly has the shape unanimous with the cable trend of planning, lay the cable along the cable direction subassembly can, can avoid wrong cloth or hourglass cloth, can avoid the whole of the waste that the cable overlength caused and the short whole of causing to scrap simultaneously, and can form the protection to the cable, avoid the cable to buckle inefficacy, show improvement and lay efficiency and quality, the material resources of using manpower sparingly. Compared with the prior art, the technical scheme of the invention can solve the technical problems of low cable laying efficiency, easy cloth misplacement or cloth leakage and easy bending and failure of cables in the prior art.

Drawings

The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.

Fig. 1 shows a schematic structural view of a hollow guide frame provided according to a specific embodiment of the present invention;

FIG. 2 illustrates a schematic structural view of a cable guide assembly provided in accordance with a specific embodiment of the present invention;

FIG. 3 is a schematic diagram illustrating a position relationship between a slide rail and an aircraft according to an embodiment of the invention;

fig. 4 shows a partially enlarged view of a slide rail provided according to an embodiment of the present invention.

Detailed Description

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.

The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

As shown in fig. 2 and 3, according to a particular embodiment of the invention, there is provided an aircraft cabling arrangement comprising:

the cable guide assembly 10, the cable guide assembly 10 has a shape consistent with the preset direction of the cable, and is used for laying the cable in the cable guide assembly 10 so as to maintain the preset direction of the cable;

a fastening assembly 20, the fastening assembly 20 being connected to the cable guide assembly 10 and the aircraft 30, respectively, for fixing the cable guide assembly 10 in the aircraft 30, the cable being laid in a predetermined orientation in the aircraft 30 by cooperation of the cable guide assembly 10 and the fastening assembly 20.

The preset trend refers to the actual trend of the cable planned according to the layout of the electrical equipment in the aircraft 30, and when the structure provided by the invention is applied practically, a three-dimensional model of cable laying in the aircraft 30 can be drawn according to the layout of the electrical equipment, and then the cable guide assembly 10 is manufactured according to the three-dimensional model according to the actual proportion.

By applying the configuration mode, the cable laying structure of the aircraft is provided, the cable is laid in the cable guide assembly 10 in advance to maintain the preset trend of the cable, and then the cable guide assembly 10 is fixed in the aircraft through the fastening assembly 20, so that the cable is matched with the planned actual trend, and the cable can be laid in the aircraft 30 quickly and accurately. Because cable guide subassembly 10 has the shape unanimous with the cable trend of planning, lay the cable along cable guide subassembly 10 can, can avoid wrong cloth or hourglass cloth, can avoid the whole of the waste that the cable overlength caused and the short whole of causing to scrap simultaneously, and can form the protection to the cable, avoid the cable to buckle inefficacy, show improvement and lay efficiency and quality, the material resources of using manpower sparingly. Compared with the prior art, the technical scheme of the invention can solve the technical problems of low cable laying efficiency, easy cloth misplacement or cloth leakage and easy bending and failure of cables in the prior art.

In one embodiment of the present invention, as shown in fig. 2, the cable guide assembly 10 includes a hollow guide frame 11 and a buckle 12, a side wall of the hollow guide frame 11 has an opening, the buckle 12 is disposed on the opening, and the buckle 12 is used for opening to lay a cable in the hollow guide frame 11 and closing to limit the cable in the hollow guide frame 11. With this arrangement, the cable can be laid quickly and accurately while preventing the cable from being accidentally pulled out of the hollow guide frame 11 by the hook 12. The shape of the branch of the hollow guide frame 11 is determined as required, for example, as shown in fig. 2, the branch of the hollow guide frame 11 is a C-shaped rigid hollow structure, the buckles 12 are distributed along the radial direction, the C-shaped structure is convenient for cabling, and the exterior is smooth and is not easy to affect the equipment in the aircraft 30. Furthermore, the hollow guide frame 11 can be manufactured in real scale according to a three-dimensional model of cable laying, and preferably, the hollow guide frame 11 is manufactured by using a 3D printing forming technology, that is, the hollow guide frame 11 is a 3D printing forming part, and the overall appearance thereof is shown in the schematic diagram of fig. 1.

When the cables are integrally arranged on the hollow guide frame 11 according to the design requirement of electrical connection, the length of the integral cables can be increased by a small amount of plugging allowance according to the length of the frame, so that waste caused by overlong cables and scrapping of the integral cables caused by overlong cables are avoided. Connectors corresponding to equipment requirements are arranged at each end of the hollow guide frame 11, namely, an integral cable installation module is formed.

Further, as an embodiment of the present invention, the fastening assembly 20 includes a slider 21 and a slide rail 22 engaged with the slider 21 in a nested manner, the slider 21 is disposed on the hollow guide frame 11, and the slide rail 22 is disposed in the aircraft 30. After the cable laying and the connector installation are completed, the sliding block 21 is pushed into the sliding rail 22, the sliding block 21 is pushed to move to a proper position, the distribution position of the cable in the aircraft can be guaranteed to be completely consistent with the planned cable distribution position, the connector at the corresponding position and corresponding electrical equipment are plugged in place and can be put into use conveniently and quickly. The matching mode of the sliding block 21 and the sliding rail 22 is similar to a tenon structure, and in order to further improve the reliability of the matching of the sliding block 21 and the sliding rail 22, as shown in fig. 2 and 4, the cross section of the sliding block 21 is wedge-shaped, the sliding rail 22 has an inner surface matched with the sliding rail, and the sliding block 21 and the sliding rail 22 are clamped together, so that the sliding block 21 is prevented from being separated from the sliding rail 22.

In the present invention, the connection manner of the slide rail 22 and the aircraft 30 is determined according to actual needs, such as welding, riveting, and adhering. As an embodiment of the present invention, referring to fig. 2 and 4, the fastening assembly 20 further includes a fixing pin, the sliding block 21 has a first connecting hole 21a, the sliding rail 22 has a second connecting hole 22a, and the fixing pin passes through the first connecting hole 21a and the second connecting hole 22a to fix the sliding rail 22 and the sliding block 21 in the aircraft 30. Through the configuration mode, the slide rail 22 and the slide block 21 can be firmly fixed on the cabin body of the aircraft 30, the cable is prevented from being pulled due to shaking during working, and the reliability of the cable laying structure is improved.

Further, second connecting hole 22a on the slide rail 22 sets up in pairs on the length direction of slide rail 22, and in the second connecting hole 22a that sets up in pairs, one is located the left side wall of slide rail 22, and another is located the right side wall of slide rail 22, and just one side of being connected with the aircraft cabin body is the screw hole, and the opposite side is the through-hole, and the fixed pin chooses for use the screw thread cylindric lock to reduce the assembly degree of difficulty, improve the installation effectiveness.

According to another aspect of the invention, an aircraft is provided, characterized in that it comprises a cabling arrangement according to the invention as set forth above.

By applying the configuration mode, the aircraft comprises the aircraft cable laying structure, and the aircraft cable laying structure can avoid wrong or missed laying, realize quick and accurate laying of cables in the aircraft, simultaneously avoid waste caused by overlong cables and integral scrapping caused by overlong cables, protect the cables and avoid bending failure of the cables. Therefore, the aircraft cable laying structure is applied to the aircraft, the mass production capacity of the aircraft can be obviously improved, the production period is shortened, manpower and material resources are saved, and the reliability of the overall performance of the aircraft is improved.

According to a further aspect of the present invention, there is provided a cable laying method comprising: determining the shape of the cable guide component according to the preset trend of the cable, and manufacturing the cable guide component according to the shape; laying the cable within the cable guide assembly; the cable guide assembly is secured within the aircraft by a fastener assembly.

Through the mode, the cable can be matched with the planned actual trend, and the cable in the aircraft can be laid quickly and accurately. Because the cable direction subassembly has the shape unanimous with the cable trend of planning, lay the cable along the cable direction subassembly can, can avoid wrong cloth or hourglass cloth, can avoid the whole of the waste that the cable overlength caused and the short whole of causing to scrap simultaneously, and can form the protection to the cable, avoid the cable to buckle inefficacy, show improvement and lay efficiency and quality, the material resources of using manpower sparingly.

In one embodiment of the invention, the cable guide assembly comprises a hollow guide frame and a buckle, and laying the cable in the cable guide assembly comprises: opening the buckle to lay the cable in the hollow guide frame; the clasp is closed to retain the cable within the hollow guide frame. Preferably, the hollow guide frame is manufactured in a 3D printing mode, and the frame is accurate and convenient to realize.

Further, as an embodiment of the present invention, the fastening assembly includes a slider and a slide rail, the slider is disposed in the hollow guide frame, and the fixing of the cable guide assembly in the aircraft by the fastening assembly includes: installing a slide rail in an aircraft; the slider is inserted into the slide rail to slide into place.

Furthermore, the description of the examples of the method may refer to the description relating to the cabling structure of an aircraft and will not be repeated here.

In summary, the invention provides an aircraft cable laying structure, an aircraft and a cable laying method, the structure maintains a preset trend of a cable by laying the cable in a cable guide assembly in advance, and then fixes the cable guide assembly in the aircraft through a fastening assembly, so that the cable is consistent with a planned actual trend, and the cable in the aircraft can be laid quickly and accurately. Because the cable direction subassembly has the shape unanimous with the cable trend of planning, lay the cable along the cable direction subassembly can, can avoid wrong cloth or hourglass cloth, can avoid the whole of the waste that the cable overlength caused and the short whole of causing to scrap simultaneously, and can form the protection to the cable, avoid the cable to buckle inefficacy, show improvement and lay efficiency and quality, the material resources of using manpower sparingly. Compared with the prior art, the technical scheme of the invention can solve the technical problems of low cable laying efficiency, easy cloth misplacement or cloth leakage and easy bending and failure of cables in the prior art.

Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft cabling arrangement, said arrangement comprising:

a cable guide assembly (10), the cable guide assembly (10) having a shape conforming to a preset orientation of a cable for laying the cable within the cable guide assembly (10) to maintain the cable in the preset orientation;

a fastening assembly (20), the fastening assembly (20) being connected to the cable guide assembly (10) and the aircraft (30) respectively for fixing the cable guide assembly (10) within the aircraft (30), the cable being laid within the aircraft (30) in the predetermined course by cooperation of the cable guide assembly (10) and the fastening assembly (20).

2. A structure as claimed in claim 1, characterized in that the cable guide assembly (10) comprises a hollow guide frame (11) and a catch (12), the side wall of the hollow guide frame (11) having an opening, the catch (12) being provided on the opening, the catch (12) being adapted to open for laying the cable within the hollow guide frame (11) and to close for retaining the cable within the hollow guide frame (11).

3. The structure according to claim 2, characterized in that the fastening assembly (20) comprises a slider (21) and a sliding rail (22) cooperating in a nested manner with the slider (21), the slider (21) being arranged on the hollow guide frame (11), the sliding rail (22) being arranged inside the aircraft (30).

4. The structure according to claim 3, characterized in that the fastening assembly (20) further comprises a fixing pin, the slider (21) having a first connection hole (21a) thereon and the slide rail (22) having a second connection hole (22a) thereon, the fixing pin passing through the first connection hole (21a) and the second connection hole (22a) to fix the slide rail (22) and the slider (21) within the aircraft (30).

5. A structure as claimed in claim 4, characterized in that said hollow guide frame (11) is a 3D printed profiled part.

6. An aircraft, characterized in that it comprises a cabling arrangement according to any of claims 1 to 5.

7. A method of cabling, the method comprising:

determining the shape of a cable guide component according to the preset trend of the cable, and manufacturing the cable guide component according to the shape;

laying the cable within the cable guide assembly;

the cable guide assembly is secured within the aircraft by a fastener assembly.

8. The method of claim 7, wherein the cable guide assembly includes a hollow guide frame and a snap, and wherein laying the cable within the cable guide assembly includes:

opening the buckle to lay the cable within the hollow guide frame;

closing the clasp to restrain the cable within the hollow guide frame.

9. The method of claim 8, wherein the fastener assembly comprises a slider and a slide rail, the slider disposed within the hollow guide frame, and securing the cable guide assembly within the aircraft via the fastener assembly comprises:

installing the sled within the aircraft;

inserting the sliding block into the sliding rail to slide in place.

10. The method according to claim 9, characterized in that the hollow guide frame is manufactured by means of 3D printing.