Aviation engine cable connector fixing device and aviation engine

Abstract

The present invention relates to a fixing device for an aero-engine cable connector and an aero-engine. The fixing device for the aero-engine cable connector comprises: a support plate (1) provided with a plurality of mounting holes (11); cable connectors (2) arranged in one-to-one correspondence with the mounting holes (11), the cable connectors (2) comprising connector bodies inserted into the mounting holes (11) and protruding portions protruding radially from the connector bodies along the mounting holes (11); and a pressing plate (4) connected to the support plate (1) and abutting against the protruding portions of the plurality of cable connectors (2) to clamp the protruding portions between the support plate (1) and the pressing plate (3). By applying the technical solution of the present invention, the pressing plate (4) can simultaneously fix a plurality of cable connectors on the support plate (1), solving the problem of the complex structure of the cable connector fixing device in the prior art.

Description

Technical Field

[0001] The present invention relates to the field of aviation equipment, and more particularly, to a fixing device for an aviation engine cable connector and an aviation engine. Background Art

[0002] The airborne cable harness of an aviation engine provides an electrical transmission channel for control system equipment to achieve the transmission of electrical signals or control parameters between equipment. Connections are made through cable connectors between various equipment and harnesses, between the engine and the aircraft, and between the engine and the test bench. There are a large number of connectors on the engine with different sizes. Currently, the fixing method for connectors is mostly to fix a group of cable connectors 2 on a support plate 1, and the cable connector 2 and the support plate 1 are fixed by bolts 3. Each plug-in head requires at least 4 bolts for fixing. See Figures 1 to 3 .

[0003] Currently, the fixing method of aviation engine cable connectors is mainly as Figure 1 shown, and there are the following drawbacks:

[0004] 1. Complicated structure. When installing multiple cable connectors 2 on the same support panel 1, each cable connector 2 needs to have connection holes and fixing holes, and the number is at least 5. The support structure has many holes and is complicated in structure;

[0005] 2. Complicated operation. Each cable connector 2 requires at least 4 bolts 3 for fixing, with high requirements for the relative position accuracy of the hole positions. Each bolt needs to measure the torque value and install a fuse, and the assembly operation is complicated;

[0006] 3. Many parts and prone to generate foreign objects. Each cable connector 2 requires at least 4 bolts for fixing. The bolts are numerous and small in size, and are extremely likely to fall off during the assembly on the engine, generating foreign objects;

[0007] 4. Small size and low strength of the fixing parts. The bolts for fixing the cable connectors are small in size and weak in load-bearing capacity. Summary of the Invention

[0008] The present invention aims to provide a fixing device for an aviation engine cable connector and an aviation engine to improve the problem of the complicated structure of the cable connector fixing device in the related art.

[0009] According to one aspect of an embodiment of the present invention, a fixing device for an aviation engine cable connector is provided. The fixing device includes:

[0010] A support plate provided with a plurality of mounting holes;

[0011] The cable connectors are provided in one-to-one correspondence with the mounting holes. The cable connector includes a connector body inserted into the mounting hole and a protruding portion protruding radially from the connector body along the mounting hole.

[0012] The pressing plate is connected to the support plate and abuts against the protruding portions of a plurality of cable connectors to clamp the protruding portions between the support plate and the pressing plate.

[0013] In some embodiments, the pressing plate is provided with an avoidance hole for avoiding the cable connector.

[0014] In some embodiments, the avoidance hole has an open side. The aero-engine cable connector fixing device further includes a pressing strip, which is connected to the support plate and is located on the open side of the mounting hole to limit the cable connector in the mounting hole.

[0015] In some embodiments, the pressing strip includes:

[0016] The first pressing strip abuts against the cable connector, and one side of the first pressing strip away from the cable connector has an inclined surface.

[0017] The second pressing strip is connected to the support plate and abuts against the inclined surface of the first pressing strip to press the first pressing strip against the cable connector when the second pressing strip approaches the support plate.

[0018] In some embodiments, the second pressing strip is connected to the support plate through a fastener. The fastener includes:

[0019] A nut;

[0020] A bolt passes through the first bolt hole on the support plate and the second bolt hole on the second pressing strip and is connected to the nut.

[0021] In some embodiments, the nut is fixed on the second pressing strip.

[0022] In some embodiments, the pressing plate is connected to the support plate through a fastener. The fastener includes:

[0023] A nut;

[0024] A bolt passes through the first bolt hole on the support plate and the third bolt hole on the pressing plate and is connected to the nut.

[0025] In some embodiments, the nut is fixed on the pressing plate.

[0026] According to another aspect of the present invention, an aero-engine is further provided. The aero-engine includes the above-mentioned aero-engine cable connector fixing device.

[0027] By applying the technical solution of the present invention, the pressing plate can fix a plurality of cable connectors on the support plate at the same time, solving the problem of the complex structure of the cable connector fixing device in the prior art.

[0028] Other features and advantages of the present invention will become apparent from the following detailed description of exemplary embodiments of the invention with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or in the related art, the following will briefly introduce the drawings required for use in the description of the embodiments or the related art. Obviously, the drawings in the following description are only some embodiments of the present invention, and for those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0030] Figure 1 FIG. shows a schematic structural diagram of a fixing device for an aeroengine cable connector in the related art;

[0031] Figure 2 FIG. shows a three-dimensional structural diagram of a support plate of a fixing device for an aeroengine cable connector in the related art;

[0032] Figure 3 FIG. shows a three-dimensional structural diagram of the support plate of the fixing device for an aeroengine cable connector in the related art from another angle;

[0033] Figure 4 FIG. shows a three-dimensional structural diagram of a fixing device for an aeroengine cable connector according to an embodiment of the present invention;

[0034] Figure 5 FIG. shows a three-dimensional structural diagram of the fixing device for an aeroengine cable connector according to an embodiment of the present invention from another angle;

[0035] Figure 6 FIG. shows an exploded view of the fixing device for an aeroengine cable connector according to an embodiment of the present invention;

[0036] Figure 7 FIG. shows Figure 6 a partial enlarged view at A in

[0037] Figure 8 FIG. shows a structural diagram of a support plate of a fixing device for an aeroengine cable connector according to an embodiment of the present invention;

[0038] Figure 9 FIG. shows a structural diagram of a pressing plate of a fixing device for an aeroengine cable connector according to an embodiment of the present invention;

[0039] Figure 10 FIG. shows a structural diagram of a pressing strip of a fixing device for an aeroengine cable connector according to an embodiment of the present invention; and

[0040] Figure 11 The side view structural schematic diagram of the pressing strip of the aero-engine cable connector fixing device according to an embodiment of the present invention is shown. Specific embodiments

[0041] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. The following description of at least one exemplary embodiment is actually illustrative only and in no way limits the present invention and its application or use. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts belong to the scope of protection of the present invention.

[0042] Combined with Figures 4 to 11 As shown, the aero-engine cable connector fixing device of this embodiment includes a support plate 1, a cable connector 2, and a pressing plate 4. The support plate 1 is provided with a plurality of mounting holes 11. The cable connectors 2 are arranged in one-to-one correspondence with the mounting holes 11. The cable connector 2 includes a connector body inserted into the mounting hole 11 and a protruding portion protruding radially from the connector body along the mounting hole.

[0043] The pressing plate 4 is connected to the support plate 1 and abuts against the protruding portions of the plurality of cable connectors 2 to clamp the protruding portions between the support plate 1 and the pressing plate 3.

[0044] As Figure 7 And 9 As shown, in some embodiments, the pressing plate 4 is provided with an avoidance hole for avoiding the cable connector 2.

[0045] The avoidance hole 41 has an open side. The aero-engine cable connector fixing device further includes a pressing strip 5. The pressing strip 5 is connected to the support plate 1 and is located on the open side of the avoidance hole 41 to limit the cable connector 2 within the mounting hole 41.

[0046] The pressing strip 5 includes a first pressing strip 51 and a second pressing strip 52. The first pressing strip 51 abuts against the cable connector 2, and the side of the first pressing strip 51 away from the cable connector 2 has an inclined surface. The second pressing strip 52 is connected to the support plate 1 and abuts against the inclined surface of the first pressing strip 51 to press the first pressing strip 51 against the cable connector 2 when the second pressing strip 52 approaches the support plate 1.

[0047] The second pressing strip 52 is connected to the support plate 1 through a fastener 3. The fastener 3 includes a nut 32 and a bolt 31; the bolt 31 passes through the first bolt hole 11 on the support plate 1 and the second bolt hole on the second pressing strip 52 and is connected to the nut.

[0048] In some embodiments, the nut 32 is fixed on the second pressing strip 52.

[0049] The pressing plate 4 is connected to the supporting plate 1 via a fastener 3 . The fastener 3 comprises a nut 32 and a bolt 31 . The bolt 31 passes through a first bolt hole 11 on the supporting plate 1 and a third bolt hole on the pressing plate 4 and is connected to the nut 32 .

[0050] In some embodiments, the nut 32 is fixed on the pressure plate 4 .

[0051] The present invention proposes a fixing structure and operating method of an aircraft engine cable connector, which is composed of a support plate, a pressure plate, a pressure strip, a fastener and other structures. The connector is fixed by the pressure plate and the pressure strip, achieving the beneficial effects of simple structure, convenient operation and a small number of parts. The following technical solutions are mainly adopted:

[0052] (1) Support plate 1, pressure plate 4, pressure strip 5, fastener 3. The support plate 1 has a mounting hole for placing the cable connector 2. The pressure plate 4 has an avoidance hole 41, the size of which corresponds to the size of the cable plug connector, which is used to press the cable connector 2 and the base, and to constrain the movement of the cable connector perpendicular to the support plate. The pressure strip has a trapezoidal cross section with a bevel. The pressure strip 5 includes a first pressure strip 51 without a nut and a second pressure strip 52 with a support plate nut. The straight edge of the first pressure strip 51 directly contacts the connector 2, and the bevel of the first pressure strip 51 contacts the bevel of the second pressure strip 52. When the bolts for fixing the second pressure strip 52 are tightened, the second pressure strip 52 moves toward the support plate, and at the same time presses the first pressure strip 51 to move toward the connector, which is used to press the cable connector 2 and constrain the movement of the cable connector 2 parallel to the support plate. The fastener is used to fasten the pressure plate and the support plate, and the pressure strip and the support plate.

[0053] (2) In the first step, all connectors are inserted into the support plate 1 through the holes. In the second step, the support plate 1 and the pressure plate 4 are connected by fasteners 3. The fasteners 3 do not need to be tightened, and the two should be allowed to swing. In the third step, the fasteners 3 are tightened after adjusting the position of the connectors. In the fourth step, the first pressure strip 51 is placed in the avoidance hole 41 of the pressure plate. In the fifth step, the pressure strip is tightened by the fasteners. The assembly process is now completed.

[0054] In view of the shortcomings of the existing cable connector fixing method, the present invention proposes a new cable connector fixing structure and operation method, which can better solve the problems of complex structure, cumbersome operation, large number of parts, weak bolt bearing capacity, etc. during installation of the cable connector, and achieves the beneficial effects of simple structure, convenient operation and small number of parts.

[0055] According to another aspect of this embodiment, an aircraft engine is also provided. The aircraft engine includes the above-mentioned aircraft engine cable connector fixing device.

[0056] The above are only exemplary embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. An aviation engine cable connector fixing device, characterized in that Comprising: A support plate (1) provided with a plurality of mounting holes (11); Cable connectors (2) arranged in one-to-one correspondence with the mounting holes (11), the cable connectors (2) comprising connector bodies inserted into the mounting holes (11) and protruding portions protruding radially from the connector bodies along the mounting holes (11); A pressure plate (4) connected to the support plate (1) and abutting against the protruding portions of the plurality of cable connectors (2) to clamp the protruding portions between the support plate (1) and the pressure plate (3), The pressure plate (4) is provided with avoidance holes for avoiding the cable connectors (2), The avoidance holes (41) have an open side, and the aero-engine cable connector fixing device further comprises a pressing strip (5), the pressing strip (5) being connected to the support plate (1) and located at the open side of the avoidance holes (41) to limit the cable connectors (2) within the mounting holes (41), The pressing strip (5) comprises: A first pressing strip (51) abutting against the cable connector (2), and a slope is provided on a side of the first pressing strip (51) away from the cable connector (2); A second pressing strip (52) connected to the support plate (1) and abutting against the slope of the first pressing strip (51) to abut the first pressing strip (51) against the cable connector (2) when the second pressing strip (52) approaches the support plate (1).

2. The fixing device for an aero-engine cable connector according to claim 1, wherein The second pressing strip (52) is connected to the support plate (1) by a fastener (3), and the fastener (3) comprises: A nut (32); A bolt (31) passing through a first bolt hole (11) in the support plate (1) and a second bolt hole in the second pressing strip (52) and connected to the nut.

3. The fixing device for an aero-engine cable connector according to claim 2, characterized in that, The nut (32) is fixed on the second pressing strip (52).

4. The fixing device for an aero-engine cable connector according to claim 1, characterized in that, The pressure plate (4) is connected to the support plate (1) by a fastener (3), and the fastener (3) comprises: A nut (32); A bolt (31) passing through a first bolt hole (11) in the support plate (1) and a third bolt hole in the pressure plate (4) and connected to the nut (32).

5. The fixing device for an aero-engine cable connector according to claim 4, characterized in that, The nut (32) is fixed on the pressure plate (4).

6. An aeroengine, characterized in that, Comprising the aero-engine cable connector fixing device according to any one of claims 1 to 5.

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