Residual wire harness anti-shaking device

Abstract

The utility model belongs to the technical field of aviation electrical interconnection (EWIS), and particularly relates to a margin wire harness anti-shaking device, which comprises a rotating support, a hoop and two connecting rods, one end of each connecting rod is hinged with the rotating support, the other end of each connecting rod is hinged with the other end of each connecting rod, and the other end of each connecting rod is hinged with the hoop. The rotating support hinged to one connecting rod is fixed to equipment, and the rotating support hinged to the other connecting rod is fixed to an aircraft structure. And each connecting rod is fixedly connected with a clamping hoop. The fixing device is used for fixing the wire harness allowance required by the disassembly and assembly of the maintenance-port-free equipment on the airplane, can move along with the equipment, and guarantees the disassembly and assembly requirements of the equipment.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the aviation electrical interconnection (EWIS) technical field, specifically a surplus wire harness anti-shaking device. BACKGROUND

[0002] Due to the limited space of the aircraft and some specific technical requirements, the layout position of many devices is limited, there is no maintenance port to remove the interface wire harness of the device in advance, so these devices need to be installed and disassembled while maintaining the wire harness connection, which requires a certain amount of surplus wire harness to meet the disassembly and assembly requirements of the device.

[0003] As shown in Figure 1 The prior art is to arrange the surplus wire harness 8 required for disassembly and assembly of the device between the connector 9 connected with the device 10 and the first fixed clamp 4 of the wire harness on the aircraft. This section of surplus wire harness is generally long and directly suspended, and will shake with the movement of the aircraft, which can easily cause damage to the wire harness due to long-term stress; or collide with other devices or structures during the shaking process, which can easily cause damage to the wire harness itself and pose a certain risk to the aircraft and other devices. UTILITY MODEL CONTENTS

[0004] In view of the problem that the surplus wire harness required for disassembly of the device without a maintenance port on the aircraft is not fixed and prone to shaking with the movement of the aircraft, the utility model aims to provide a surplus wire harness anti-shaking device.

[0005] The utility model aims to achieve the following technical solutions:

[0006] The utility model discloses a rotating support, a clamp and a connecting rod, wherein the connecting rod is two, one end of two connecting rods is hingedly connected with a rotating support, the other end of two connecting rods is hingedly connected, the rotating support hingedly connected with one connecting rod is fixed on the device, and the rotating support hingedly connected with another connecting rod is fixed on the aircraft structure; a clamp is fixedly connected on each connecting rod.

[0007] Among them: the rotating support is provided with a groove, one end of the connecting rod is inserted into the groove and hingedly connected with the rotating support, and the groove is used to limit the activity space of the connecting rod.

[0008] The groove width near one end of the device or the aircraft structure is greater than the groove width near the other end of the connecting rod, and one end of the connecting rod is inserted from the end with smaller groove width.

[0009] Both ends of the rotating support are provided with connecting holes A, the rotating support is connected with the equipment or the aircraft structure through the bolt A passing through the connecting hole A at one end; the other end of the rotating support is provided with connecting holes A symmetrically on both sides of the groove, and the connecting rod is hingedly connected with the rotating support through the bolt B passing through the connecting hole A at the other end and the nut screwed with the bolt B.

[0010] One side of the connecting rod extends outward to form an extension, and a clamp mounting hole is formed in the extension, and the clamp is fixed with the connecting rod through the bolt C passing through the clamp mounting hole and the nut screwed with the bolt C.

[0011] Both ends of the connecting rod are provided with connecting holes B, one end of the connecting rod is hingedly connected with the rotating support through the bolt B passing through the connecting hole B at one end and the nut screwed with the bolt B, and the other end of the connecting rod is hingedly connected with the other connecting rod through the counter-lock bolt passing through the connecting hole B at the other end and the counter-lock nut screwed with the counter-lock bolt.

[0012] The utility model discloses the advantages and positive effects are:

[0013] 1. The utility model discloses a wire harness surplus for fixing the equipment on the aircraft without maintenance opening, which can move with the equipment and ensure the disassembly and assembly of the equipment.

[0014] 2. The utility model discloses a simple structure, and the non-standard parts in the main components are only two rotating supports and connecting rods, which are repeatedly used in the device. The device is simple and reliable, and the implementation cost is low. DRAWINGS

[0015] Figure 1 It is an assembly diagram of the surplus wire harness in the prior art;

[0016] Figure 2 It is a structure front view of the utility model;

[0017] Figure 3 It is a structure top view of the utility model;

[0018] Figure 4 It is a structure diagram of the rotating support of the utility model;

[0019] Figure 5 It is a structure diagram of the connecting rod of the utility model;

[0020] Figure 6 It is an assembly diagram of the equipment and the aircraft structure during disassembly or installation of the utility model;

[0021] Figure 7 It is an assembly diagram of the equipment and the aircraft structure after installation of the utility model;

[0022] Wherein: 1 is bolt A, 2 is rotating support, 3 is nut, 4 is clamp, 5 is connecting rod, 6 is locking bolt, 7 is locking nut, 8 is spare wire harness, 9 is connector, 10 is equipment, 11 is aircraft structure, 12 is bolt B, 13 is bolt C, 14 is connecting hole A, 15 is groove, 16 is extension, 17 is clamp mounting hole, and 18 is connecting hole B. Detailed Implementation

[0023] The present invention will now be described in further detail with reference to the accompanying drawings.

[0024] like Figure 2 , Figure 3 As shown, this utility model includes a rotating support 2, a clamp 4, and a connecting rod 5. There are two connecting rods 5, one end of each connecting rod 5 is hinged to the rotating support 2, and the other ends of the two connecting rods 5 are hinged together. The rotating support 2 hinged to one connecting rod 5 is fixed on the equipment 10, and the rotating support 2 hinged to the other connecting rod 5 is fixed on the aircraft structure 11. A clamp 4 is fixedly connected to each connecting rod 5.

[0025] The rotating support 2 primarily serves to fix the entire device to the equipment 10 or aircraft structure 11, and provides a rotation axis for the connecting rod 5 via bolts B12 and nuts 3, while limiting the rotation range of the connecting rod 5 via grooves 15. Figures 2 to 5 As shown, the rotating support 2 in this embodiment has a groove 15. The groove width of the end of the groove 15 near the device 10 or aircraft structure 11 is greater than the groove width of the other end near the connecting rod 5. One end of the connecting rod 5 is inserted from the end with the smaller groove width. The rotating support 2 has four connecting holes A14, with two connecting holes A14 at each end. The two connecting holes A14 at one end are located at the bottom of the groove 15, and the two connecting holes A14 at the other end are symmetrically located on both sides of the groove 15. The rotating support 2 is connected to the device 10 or aircraft structure 11 via a bolt A1 passing through a connecting hole A14 at one end. The device 10 or aircraft structure 11 can use a nut 3 or directly drill internal threads; no limitation is made here. In this embodiment, both ends of the connecting rod 5 have connecting holes B18. One end of the connecting rod 5 is inserted into the groove 15. The connecting rod 5 and the rotating support 2 are hinged together by a bolt B12 passing through the connecting hole A14 at the other end of the rotating support 2 and the connecting hole B18 at one end of the connecting rod 5, and a nut 3 threadedly connected to the bolt B12. The groove 15 is used to restrict the movement space of the connecting rod 5. The other end of the connecting rod 5 is hinged together by a locking bolt 6 passing through the connecting hole B18 at the other end and a locking nut 7 threadedly connected to the locking bolt 6, and another connecting rod 5.

[0026] The one side of the connecting rod 5 of the embodiment extends outwardly to form an extension 16, and a clamp mounting hole 17 is formed in the extension 16; the clamp 4 used for wiring harness laying is fixed to the connecting rod 5 through the bolt C13 passing through the clamp mounting hole 17 and the nut 3 and the bolt C13 threadedly connected.

[0027] The working principle of the utility model is as follows:

[0028] As shown in Figure 6 the utility model fixes the excess wiring harness 8 through two rotating supports 2 fixing the whole device and the equipment 10 and the aircraft structure 11 respectively and forming a two-connecting-rod mechanism with the connecting rod 5, drives the rotating support 2 at one end of the device to move along with the equipment dismounting or mounting, then drives the connecting rod 5 and the excess wiring harness 8 fixed thereon through the clamp 4 to move together.

[0029] As shown in Figure 7 when the equipment 10 is installed in place, the positions of the rotating supports 2 at both ends of the device are fixed, the connecting rod 5 is also locked by the rotating shaft composed of the groove 15 of the rotating support 2 and the bolt B12, the nut 3 and the counter-lock bolt 6 and the counter-lock nut 7, so that the excess wiring harness 8 is fixed, and shaking is avoided.

Claims

1. A slack line bundle anti-wobble device characterized by: The utility model provides a kind of rotating support (2), clamp (4) and connecting rod (5), wherein connecting rod (5) is two, one end of two connecting rod (5) is hinged with rotating support (2), the other end of two connecting rod (5) is hinged, and rotating support (2) being hinged with one connecting rod (5) is fixed on equipment (10), and rotating support (2) being hinged with another connecting rod (5) is fixed on aircraft structure (11);Clamp (4) is fixed on each connecting rod (5).

2. The sway control device of claim 1, wherein: Groove (15) is formed in rotating support (2), one end of connecting rod (5) is inserted into groove (15), and is hinged with rotating support (2), and groove (15) is used to limit the activity space of connecting rod (5).

3. The sway control device of claim 2, wherein: The width of groove (15) near one end of equipment (10) or aircraft structure (11) is greater than the width of groove (15) near the other end of connecting rod (5), and one end of connecting rod (5) is inserted from the end with smaller width.

4. The sway control device of claim 2, wherein: Connecting hole A (14) is formed in both ends of rotating support (2), and rotating support (2) is connected with equipment (10) or aircraft structure (11) by bolt A (1) passing through connecting hole A (14) in one end; connecting hole A (14) is symmetrically formed on both sides of groove (15) in the other end of rotating support (2), and connecting rod (5) and rotating support (2) are hinged by bolt B (12) passing through connecting hole A (14) in the other end and nut (3) threaded with bolt B (12).

5. The sway control device of claim 1, wherein: Extension (16) is formed on one side of connecting rod (5), clamp mounting hole (17) is formed in extension (16), and clamp (4) is fixed with connecting rod (5) by bolt C (13) passing through clamp mounting hole (17) and nut (3) threaded with bolt C (13).

6. The sway control device of claim 1, wherein: Connecting hole B (18) is formed in both ends of connecting rod (5), one end of connecting rod (5) is hinged with rotating support (2) by bolt B (12) passing through connecting hole B (18) in one end and nut (3) threaded with bolt B (12), and the other end of connecting rod (5) is hinged with another connecting rod (5) by opposite lock bolt (6) passing through connecting hole B (18) in the other end and opposite lock nut (7) threaded with opposite lock bolt (6).

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