Wing folding wire harness with retracting and releasing functions

Abstract

The invention belongs to the technical field of fixed wing and folding wing trailing edge wiring harnesses of folding wing aircrafts, and particularly relates to a wing folding wiring harness with a retracting and releasing function, one side of a motion support is fixedly connected with a folding wing of a folding wing aircraft, and the other side of the motion support is fixedly connected with a row clamp A; one side of the upper part of the fixed bracket is fixedly connected with a fixed wing of the folding wing aircraft, the isolator is fixedly connected to the other side of the upper part of the fixed bracket, and the lower part of the fixed bracket is fixedly connected with a row clamp B; each spiral wire harness assembly is wound on the isolator, fixed to the moving support through the corresponding row clamp A and fixed to the fixed support through the corresponding row clamp B. The moving support rotates along with the folding wings, and then the spiral wire harness assemblies are driven to achieve folding-flattening movement. The multi-core large-wire-diameter folding and moving wire harness is suitable for multi-core large-wire-diameter folding and moving wire harnesses with a telescopic function, grouping can be carried out according to laying space, the core number and isolation requirements, a folding device does not need to be additionally arranged, the structure is simple, the integration degree is high, and the weight is light.

Description

Technical Field

[0001] The invention belongs to the technical field of fixed wing and folding wing trailing edge harnesses of folding-wing aircraft, in particular to a wing folding harness with a retractable and retractable function. Background Art

[0002] The trailing edge wiring harnesses for fixed and folding wings of folding wing aircraft must have the following functions:

[0003] (1) Able to effectively transmit a large number of signals (85 cores);

[0004] (2) It has a folding-flattening function (a process of folding-flattening-folding). During the folding-flattening process, the length of the harness changes in real time. The process is: the longest shrinks to the shortest - the shortest and then stretches to the longest;

[0005] (3) The wiring harness will not get stuck during the folding and unfolding process, and the signal can still be transmitted reliably.

[0006] Traditional folding harnesses with telescopic function usually have two methods:

[0007] (1) Lay the wiring harness on the folding bracket; Figure 1 As shown, the folding bracket 26 is composed of a plurality of single brackets 27, each of which is connected end to end. The movement of the folding bracket 26 drives the movement of the wiring harness to achieve extension and contraction, and the connecting axis between two adjacent single brackets 27 is used to achieve folding. Please refer to the "A Folding Wiring Harness Bracket and Vehicle for On-Board Electrical Devices" disclosed in the announcement on July 15, 2022, with the announcement number CN216969432U;

[0008] (2) The harness is directly fixed to the fixed wing and folding wing of the folding wing aircraft; a bend 29 of sufficient length is reserved between the two fixing points 28 on the harness to ensure the maximum length required when folding. The flexible characteristics of the harness itself are used to adjust the effective length by bending and stacking the harness itself during the folding-flattening process, such as Figure 2A 、 Figure 2B shown.

[0009] The above-mentioned traditional folding harness with telescopic function has the following defects:

[0010] (1) The wire harness is laid on the folding bracket 26, which can control the movement trajectory of the wire harness and prevent the wire harness from getting stuck or wearing out. However, it is only applicable to the case where the number of wire cores is small and the overall outer diameter is relatively small. Because during the movement, the individual brackets 27 often form a relatively small angle, and the minimum bending radius should be guaranteed during the bending of the wire harness (the copper wire should ensure a bending radius of 6 times the diameter of the wire harness or 10 times the diameter of the largest wire in the wire harness, whichever is larger). A smaller angle cannot meet the bending requirements of the wire harness. In actual production, a larger outer diameter wire harness can be split into multiple smaller outer diameter wire harnesses and laid separately. This requires increasing the number or width of the brackets, which is not applicable to aircraft with very limited weight and space.

[0011] (2) The method of direct wiring harness installation is suitable for situations where the movement stroke during the folding-flattening process is small. When the movement stroke is large, a long wire harness will be bent and stacked during the folding-flattening process, which will increase the risk of wire harness jamming and wear (the wire harness itself or the surrounding structure will jam and wear). The shape of the wire harness after stacking is unpredictable, or a sharp angle is formed (not meeting the bending radius requirements), causing damage to the wire harness. The stress situation after the wire harness is stacked is unpredictable, or torsion or shear force is generated, causing fatigue damage after multiple folding-flattening, affecting the service life. Summary of the Invention

[0012] In order to overcome the above-mentioned defects of the traditional folding harness, the object of the present invention is to provide a wing folding harness with a retractable and retractable function.

[0013] The object of the present invention is achieved through the following technical solutions:

[0014] The present invention includes a moving bracket assembly, a fixed bracket assembly and multiple spiral wire harness assemblies, wherein the moving bracket assembly includes a moving bracket and a row of clamps A, one side of the moving bracket is fixedly connected to the folding wing of the folding-wing aircraft, and the other side of the moving bracket is fixedly connected to the row of clamps A; the fixed bracket assembly includes an insulator, a fixed bracket and a row of clamps B, one side of the upper part of the fixed bracket is fixedly connected to the fixed wing of the folding-wing aircraft, the insulator is fixedly connected to the other side of the upper part of the fixed bracket, and the lower part of the fixed bracket is fixedly connected to the row of clamps B; each of the spiral wire harness assemblies is respectively wound on the insulator, and is fixed to the moving bracket by the row of clamps A and to the fixed bracket by the row of clamps B, the moving bracket rotates with the folding wing, thereby driving each of the spiral wire harness assemblies to realize folding-flattening movement.

[0015] The isolator has the same number of recessed parts as the spiral wire harness components, both sides of each recessed part are protrusions with an outer diameter larger than the recessed part, and each spiral wire harness component is wound around the recessed part between two adjacent protrusions.

[0016] A through hole is provided inside the recessed portion, and a long bolt for fixing to the fixing bracket is passed through the through hole. The long bolt passes through the fixing bracket and is fixed to the fixing bracket through a hexagonal nut and a cotter pin.

[0017] The axial center line of the insulator is located at the rotation center of the folding-flattening movement, the outer diameter of the protrusion is larger than the maximum outer diameter of the spiral coil in the spiral wire harness assembly, and the outer diameter of the recess is smaller than the minimum outer diameter of the spiral coil in the spiral wire harness assembly.

[0018] At least one row of clamps A is fixed to the other side of the movable bracket, and each row of clamps A consists of two rows arranged upper and lower; at least one row of clamps B is fixed to the lower part of the fixed bracket, and each row of clamps B consists of two rows arranged upper and lower; the row of clamps A and the row of clamps B have the same structure, both including a clamp body, and the clamp body is provided with grooves along the length direction with the same number as the spiral wire harness components, and each of the spiral wire harness components is clamped between the corresponding two grooves on the upper and lower clamp bodies; a bolt hole for fixing to the movable bracket or the fixed bracket is provided between two adjacent grooves on the clamp body.

[0019] The surface of the groove is provided with a protrusion that contacts the spiral wire harness component.

[0020] The spiral harness assembly comprises a connector, a tail attachment and a spiral wire. The spiral wire is wound on an insulator, and each end of the spiral wire is provided with a tail attachment and a connector.

[0021] The advantages and positive effects of the present invention are:

[0022] 1. The present invention is suitable for folding and moving wire harnesses with multi-core and large-diameter wires and telescopic functions. They can be grouped according to the laying space, number of cores, and isolation requirements. The width of the clamps, spacers, and brackets can be set according to the grouping situation. There is no need to add a folding device. The structure is simple, the integration is high, and the weight is light.

[0023] 2. The motion bracket of the present invention is a follower mechanism that moves synchronously with the wing, and no additional power is required for the wiring harness.

[0024] 3. The present invention controls the effective length of the wire harness through the outer diameter of the preformed spiral coil, so that the trajectory of the moving wire harness is controllable and the effective length of the wire harness is controlled in real time, solving the protection problem between the foldable moving wire harness with the retractable and unfolding function and other structures.

[0025] 4. During the folding-flattening process, the force direction of the spiral part of the present invention is always along the tangent direction of the spiral line, which will not cause damage to the wire harness.

[0026] 5. The clamps of the present invention are grouped into two and can fix multiple wire harnesses at the same time. They can be flexibly designed according to the grouping of wire harnesses. Compared with ordinary clamps, the number of assembly parts can be reduced and space utilization can be improved.

[0027] 6. The spiral wire of the present invention is a preformed finished wire, and the finished state of the wire harness is the state of the maximum outer diameter of the spiral coil. During the production process, there is no need to bundle and solidify the wire harness, which simplifies the difficulty of wire harness processing.

[0028] 7. The wing folding harness of the present invention is fixed to the fuselage only by bolts. The harness space is controllable during the movement process and no additional protection is required, which simplifies the difficulty of harness laying. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 A schematic diagram of the structure of a folding bracket for laying a traditional folding wire harness;

[0030] Figure 2A This is one of the structural diagrams of a conventional folding harness that is directly fixed between the fixed wing and the folding wing of a folding-wing aircraft;

[0031] Figure 2B This is the second structural diagram of a conventional folding harness directly fixed between the fixed wing and the folding wing of a folding-wing aircraft;

[0032] Figure 3 It is a schematic diagram of the overall structure of the present invention;

[0033] Figure 4A for Figure 3 Schematic diagram of the structure of the moving bracket assembly and the fixed bracket assembly;

[0034] Figure 4B for Figure 4A A-A sectional view in FIG;

[0035] Figure 5 for Figure 3 Schematic diagram of the structure of the spiral harness assembly;

[0036] Figure 6 for Figure 3 Schematic diagram of the structure of the insulator;

[0037] Figure 7 for Figure 3 Schematic diagram of the structure of the middle row of clamps;

[0038] Figure 8A This is a schematic diagram of the structure of the present invention installed on the folding wing and fixed wing of a folding-wing aircraft in a flattened state;

[0039] Figure 8B This is a schematic diagram of the structure of the present invention installed on the folding wing and fixed wing of a folding-wing aircraft in a folded state;

[0040] Among them: 1 is the moving bracket assembly, 2 is the fixed bracket assembly, 3 is the spiral harness assembly A, 4 is the spiral harness assembly B, 5 is the spiral harness assembly C, 6 is the cotter pin, 7 is the hexagonal nut, 8 is the gasket A, 9 is the insulator, 901 is the protrusion, 902 is the recessed portion, 903 is the through hole, 10 is the long bolt, 11 is the support plate nut, 12 is the bolt A, 13 is the row clamp A, 1301 is the groove, 1302 is the protrusion, 1303 is the bolt hole, 1304 is the clamp body, 14 is the gasket B, 15 is the moving bracket, 16 is the fixed bracket, 17 is the connector, 18 is the tail accessory, 19 is the spiral wire, 20 is the folding wing, 21 is the fixed wing, 22 is the support plate nut B, 23 is the bolt B, 24 is the row clamp B, 25 is the gasket C, 26 is the folding bracket, 27 is the single bracket, 28 is the fixing point, and 29 is the bending portion. DETAILED DESCRIPTION

[0041] The present invention will be further described below in conjunction with the accompanying drawings.

[0042] like Figure 3 、 Figure 4A 、 Figure 4B 、 Figure 8A and Figure 8B As shown, the present invention includes a moving bracket assembly 1, a fixed bracket assembly 2 and a plurality of spiral harness assemblies, wherein the moving bracket assembly 1 includes a moving bracket 15 and a row of clamps A13, one side of the moving bracket 15 is fixedly connected to the folding wing 20 of the folding-wing aircraft by a fastening bolt, and the other side of the moving bracket 15 is fixedly connected to the row of clamps A13; the fixed bracket assembly 2 includes an insulator 9, a fixed bracket 16 and a row of clamps B24, one side of the upper part of the fixed bracket 16 is fixedly connected to the fixed wing 21 of the folding-wing aircraft by a fastening bolt, the insulator 9 is fixed to the other side of the upper part of the fixed bracket 16, and the lower part of the fixed bracket 16 is fixedly connected to the row of clamps B24; each spiral harness assembly is respectively wound on the insulator 9, and is fixed to the moving bracket 15 by the row of clamps A13 and to the fixed bracket 16 by the row of clamps B24, the moving bracket 15 rotates with the folding wing, and then drives each spiral harness assembly to realize the folding-flattening movement.

[0043] In this embodiment, the connecting plate fixed to the folding wing 20 on one side of the movable bracket 15 is perpendicular to the mounting plate of the mounting row clamp A13 on the other side, and the connecting plate fixed to the fixed wing 21 on the upper side of the fixed bracket 16 is perpendicular to the mounting plate of the lower mounting row clamp B24. Multiple mounting holes are provided on the connecting plates and mounting plates of the movable bracket 15 and the fixed bracket 16.

[0044] At least one set of clamps A13 (in this embodiment, the clamps A13 are one set) is fixed to the mounting plate on the other side of the moving bracket 15, and each set of clamps A13 consists of two clamps arranged in an upper and lower position. At least one set of clamps B24 (in this embodiment, the clamps B24 are one set) is fixed to the lower part of the fixed bracket 16, and each set of clamps B24 consists of two clamps arranged in an upper and lower position. Figure 4A 、 Figure 4B and Figure 7 As shown, the row of clamps A13 and the row of clamps B24 of this embodiment have the same structure, both including a long strip of clamp body 1304, the length direction of the clamp body 1304 is the width direction of the moving bracket 15 and the fixed bracket 16; the clamp body 1304 is provided with grooves 1301 along the length direction, the number of which is the same as the number of spiral harness components, and each spiral harness component is clamped between the corresponding two grooves 1301 on the upper and lower clamp bodies 1304. A bolt hole 1303 is provided between two adjacent grooves 1301; a bolt A12 is passed through the bolt hole 1303 on the row clamp A13, the upper end of the bolt A12 is located on the upper part of the upper row clamp A13, and a gasket B14 is provided between the bolt A12 and the upper row clamp A13, and the lower end of the bolt A12 passes through the mounting plate located on the other side of the lower row clamp A13 and the moving bracket 15, and is tightened and fixed with a support plate nut A11 to fix the row clamp A13 to the moving bracket 15. A bolt B23 is passed through the bolt hole 1303 on the row clamp B24. The upper end of the bolt B23 is located on the upper part of the upper row clamp B24, and a gasket C25 is provided between the upper row clamp B24. The lower end of the bolt B23 passes through the mounting plate located at the lower row clamp B24 and the lower part of the fixed bracket 16, and is tightened and fixed with a support plate nut B22 to fix the row clamp B24 to the fixed bracket 16.

[0045] The groove 1301 of this embodiment is semicircular, and the upper and lower grooves 1301 form a wiring harness channel. The diameter of the groove 1301 matches the wiring harness; the surface of the groove 1301 is provided with a protrusion 1302 that contacts the spiral wiring harness assembly to increase friction and prevent the wiring harness from moving.

[0046] like Figure 4A 、 Figure 4B and Figure 6As shown, the spacer 9 of this embodiment has a number of recesses 902 equal to the number of helical wire harness components. Each recess 902 is flanked by a protrusion 901 with a larger outer diameter. Each helical wire harness component is wound around the recess 902 between two adjacent protrusions 901. A through-hole 903 is formed within each recess 902. A long bolt 10 is inserted through the through-hole 903 for securing the spacer to the fixed bracket 16. The long bolt 10 passes through the fixed bracket 16 and is tightened with a hexagonal nut 7. A cotter pin 6 is inserted at the end to secure the spacer to the fixed bracket 16. A gasket A8 is provided between the hexagonal nut 7 and the fixed bracket 16. The axial centerline of the spacer 9 is located at the rotational center of the folding-flattening motion. The outer diameter of the protrusion 901 (the maximum outer diameter of the spacer 9) is larger than the maximum outer diameter of the helical coil in the helical wire harness component, while the outer diameter of the recess 902 (the minimum outer diameter of the spacer 9) is smaller than the minimum outer diameter of the helical coil in the helical wire harness component.

[0047] like Figure 4A 、 Figure 4B and Figure 5 As shown, the spiral harness assemblies of this embodiment are divided into three groups, namely spiral harness assembly A3, spiral harness assembly B4 and spiral harness assembly C5. The spiral harness assemblies of each group have the same structure, including a connector 17, a tail attachment 18 and a spiral 19. The spiral 19 is wound around the recessed portion 902 of the insulator 9, and each end of the spiral 19 is provided with a tail attachment 18 and a connector 17. The tail attachment 18 and connector 17 of this embodiment are prior art and will not be described in detail here. This embodiment divides the 85 cores into three groups, namely 30 cores, 26 cores and 29 cores, and the outer diameter of a single harness is 20 mm.

[0048] The working principle of the present invention is:

[0049] The motion bracket 15 in the motion bracket assembly 1 rotates around the rotation axis as the folding wing 20 rotates, thereby driving the folding-flattening movement of the wire harness, providing power for the folding movement of the wire harness, and the wire harness does not need to provide additional power; during the movement, the motion bracket assembly 1 does not interfere with itself or other structures of the aircraft.

[0050] The fixed bracket assembly 2 fixes the threaded wire harness assembly. The wire harness is fixed to the moving bracket 15 and the fixed bracket 16 respectively through the row of clamps A13 and the row of clamps B24. During the folding-flattening movement, the fixed bracket assembly 2 is used to ensure that the three groups of spiral wire harness assemblies and the insulator 9 are in a fixed position. While the moving bracket assembly 1 provides movement power for the wire harness, it limits the movement range of the wire harness and prevents the wire harness from interfering with other structures during the movement process.

[0051] Movable bracket 15 and fixed bracket 16 secure and support the wing folding wiring harness. They are made of aluminum alloy. Ensure the bracket width at the mounting holes (for aircraft mounting, mounting with mounting clamps, and mounting with spacers) meets the required width, and the wall thickness meets the required strength (4mm for aircraft mounting holes and 2.5mm for other locations). Avoid overdesign to minimize weight.

[0052] Three sets of spiral harness assemblies are used to transmit signals. The outer diameter of the spiral part is the smallest when folded, and the outer diameter of the spiral part is the largest when flattened. This enables the effective length of the harness to automatically change during the folding and flattening process, without interfering with other mechanisms of the aircraft and without being worn by the structure itself.

[0053] Spacer 9 is secured to bracket 16 via long bolt 10, hexagonal nut 7, and cotter pin 6. The centerline of long bolt 10 lies along the axis of rotation during the folding-flattening motion. This constrains the position of the wiring harness during the folding-flattening motion, preventing friction between the wiring harnesses and between the wiring harnesses and the aircraft structure, and ensuring a safe separation distance. Spacer 9 is made of PEEK (polyetheretherketone), which provides sufficient strength and light weight.

[0054] The function of the row clamp is to fix the spiral harness assembly on the moving bracket 15 and the fixed bracket 16 to prevent the harness from moving during the folding-flattening movement; the row clamp is made of PEEK (polyetheretherketone) material, which meets the strength requirements of use and is light in weight.

[0055] The spiral 19 is a preformed finished product. When the spiral is folded, the radius of the spiral portion is the minimum bending radius of the bundle (6 times the bundle diameter). When the spiral is flattened, the outer diameter of the spiral portion is calculated according to formula (1). The flattened state is the finished state of the spiral.

[0056]

[0057] Where d is the diameter of the helix, L1 is the effective length of the bundle in the folded state, L2 is the effective length of the bundle in the flattened state, and D is the diameter of the helix in the flattened state.

[0058] The centerline of the spiral coil lies on the axis of rotation during the folding and unfolding motion. During the folding and unfolding process, the force applied to the harness is always tangential to the coil, eliminating the lifespan and reliability issues associated with harnesses subject to torsion and shear forces. The folded state of the spiral represents the minimum radius, while the flattened state represents the maximum radius. The difference between the maximum and minimum circumferences of the coil represents the effective length of the harness, enabling real-time harness retraction and extension.

Claims

1. A wing folding harness with retractable function, characterized by: The invention comprises a moving support assembly (1), a fixed support assembly (2) and a plurality of spiral harness assemblies, wherein the moving support assembly (1) comprises a moving support (15) and a row of clamps A (13), one side of the moving support (15) is fixedly connected to a folding wing (20) of a folding-wing aircraft, and the other side of the moving support (15) is fixedly connected to a row of clamps A (13); the fixed support assembly (2) comprises an insulator (9), a fixed support (16) and a row of clamps B (24), one side of the upper part of the fixed support (16) is fixedly connected to the folding wing (20) of the folding-wing aircraft The fixed wing (21) is fixed to the fixed bracket (16), the spacer (9) is fixed to the other side of the upper part of the fixed bracket (16), and the lower part of the fixed bracket (16) is fixed with a row of clamps B (24); each of the spiral harness components is respectively wound on the spacer (9), and is fixed to the moving bracket (15) through the row of clamps A (13) and fixed to the fixed bracket (16) through the row of clamps B (24); the moving bracket (15) rotates with the folding wing, thereby driving each of the spiral harness components to achieve folding-flattening movement.

2. The wing folding harness with retractable function according to claim 1, characterized in that: The insulator (9) has recessed portions (902) equal in number to the number of the helical wire harness components. Both sides of each recessed portion (902) are protrusions (901) with an outer diameter larger than that of the recessed portion (902). Each helical wire harness component is wound around the recessed portion (902) between two adjacent protrusions (901).

3. The wing folding harness with retractable function according to claim 2, characterized in that: A through hole (903) is provided inside the recessed portion (902), and a long bolt (10) for fixing to the fixing bracket (16) is passed through the through hole (903). The long bolt (10) passes through the fixing bracket (16) and is fixed to the fixing bracket (16) through a hexagonal nut (7) and a cotter pin (6).

4. The wing folding harness with retractable function according to claim 2, characterized in that: The axial centerline of the insulator (9) is located at the rotation center of the folding-flattening movement, the outer diameter of the protrusion (901) is larger than the maximum outer diameter of the spiral coil in the spiral wire harness assembly, and the outer diameter of the recessed portion (902) is smaller than the minimum outer diameter of the spiral coil in the spiral wire harness assembly.

5. The wing folding harness with retractable function according to claim 1, characterized in that: At least one row of clamps A (13) is fixedly connected to the other side of the moving bracket (15), and each row of clamps A (13) is composed of two clamps arranged in an upper and lower position; at least one row of clamps B (24) is fixedly connected to the lower part of the fixed bracket (16), and each row of clamps B (24) is composed of two clamps arranged in an upper and lower position; the row of clamps A (13) and the row of clamps B (24) have the same structure, and both include a clamp body (1304), and the clamp body (1304) is provided with grooves (1301) with the same number as the spiral harness components along the length direction, and each spiral harness component is clamped between two corresponding grooves (1301) on the upper and lower clamp bodies (1304); a bolt hole (1303) for fixing to the moving bracket (15) or the fixed bracket (16) is provided between two adjacent grooves (1301) on the clamp body (1304).

6. The wing folding harness with retractable function according to claim 5, characterized in that: The surface of the groove (1301) is provided with a protrusion (1302) that contacts the spiral wire harness component.

7. The wing folding harness with retractable function according to claim 1, characterized in that: The spiral harness assembly comprises a connector (17), a tail attachment (18) and a spiral wire (19). The spiral wire (19) is wound on an insulator (9). Each end of the spiral wire (19) is provided with a tail attachment (18) and a connector (17).

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