Equipment insertion piece mounting structure

Abstract

The utility model relates to an equipment insertion piece installation structure, in particular to an equipment insertion piece installation structure with multi-axial constraint performance and pre-tightening capacity. An equipment insertion piece installation structure comprises an equipment box body, a pressing piece, an insertion piece, a bolt lug piece and an installation bolt, the equipment box body is installed on an airplane structure installation plane, the matching face of the pressing piece and the insertion piece is provided with a convex structure and a concave structure, and the convex structure and the concave structure jointly form a meshing structure; the bottom of the inserting piece is arranged to be slope-shaped, the height of the inserting piece can be reduced by inclining the equipment box body during installation so that the inserting piece can enter the position below the pressing piece, and after the equipment box body recovers to be horizontal, the inserting piece is meshed with the pressing piece. The utility model has the advantages that: 1, unidirectional constraint is changed into multi-axial composite constraint; 2, multi-axial composite constraint installation is realized by using special installation steps; 3, the elastic pressing sheet is used for generating pre-tightening force, so that the pressing sheet is tightly and reliably combined with the insertion sheet on the equipment box body; and 4, the equipment box body is stable and reliable to install and is reasonably loaded.

Description

Technical Field

[0001] The utility model relates to an equipment plug-in installation structure, in particular to an equipment plug-in installation structure with multi-axial constraint performance and pre-tightening capability. Background Art

[0002] Insert installation is a common equipment installation method on aircraft. The conventional insert installation structure and principle are as follows Figure 1 As shown, a pressure plate 2 is arranged on the aircraft structure mounting surface 6 for securing the structure. Insertion plates 3 and bolt tabs 4 are designed at each end of the device box 1 to be installed. During installation, the device box 1 is first placed on the aircraft structure mounting surface 6. The device box 1 is then pushed along the mounting surface to insert the insertion plates 3 under the pressure plate 2. Once in place, the bolt tabs 4 are secured to the aircraft structure mounting surface 6 using mounting bolts 5, completing the device installation.

[0003] This conventional insert installation method has the following problems: First, since the constraint of the pressure plate 2 on the insert plate 3 only exists in the direction perpendicular to the installation plane, the loads in other directions on the box body must be borne by the bolt ear piece 4, resulting in uneven force on the equipment box body and unstable installation; second, since the pressure plate 2 and the insert plate 3 are both rigid structures, the tolerance gap is difficult to control. If the design fit is too tight, it is easy to cause installation difficulties. If the design fit is too loose, the pressure plate 2 will not have a restraining effect on the insert plate 3, and all the loads on the box body will be borne by the bolt ear piece 4, causing the box body to be in an unstable state. In addition, the large bending moment will sharply deteriorate the load on the bolt ear piece 4, which is prone to damage. Utility Model Content

[0004] The purpose of the utility model is to solve the problems existing in the prior art and provide a device inserting piece installation structure, which changes the unidirectional constraint of the pressing piece on the inserting piece on the device box body into a multi-axial composite constraint.

[0005] In order to achieve the above-mentioned purpose, the present invention adopts the following technical solutions: a device plug-in installation structure, including a device box body, a pressing piece, an insert, a bolt ear piece, and a mounting bolt. The device box body is installed on the aircraft structure mounting plane. The mating surfaces of the pressing piece and the insert are provided with protrusions and recessed structures, and the two together form an engaging structure; the bottom of the insert is set to a slope shape, and during installation, the height of the insert can be lowered by tilting the device box body to enter under the pressing piece. After the device box body returns to a horizontal state, the insert and the pressing piece engage.

[0006] Preferably, the pressing tablet is an elastic pressing tablet.

[0007] Preferably, the elastic pressing piece includes an elastic section and an engaging section; both ends of the elastic section are mounted on the aircraft structure mounting plane by fixing bolts; a gap is reserved between the middle part of the elastic section and the aircraft structure mounting plane for allowing the insert to enter; the engaging section is arranged on the lower surface of the middle part of the elastic section, and its side facing the aircraft structure mounting plane is a concave structure.

[0008] Preferably, there are two engaging sections, which are distributed on the left and right sides of the pressing sheet in the insertion direction of the insert sheet.

[0009] Preferably, the fitting relationship between the engaging section and the insert is an interference fit.

[0010] Another technical solution adopted by the present invention is: an equipment plug-in installation structure, including an equipment box body, a pressing piece, an insert, a bolt ear piece, and a mounting bolt. The equipment box body is installed on the aircraft structure mounting plane, and a protrusion and a recessed structure are provided on the mounting surface of the equipment box body and the aircraft structure mounting plane, and the two together form an engaging structure; the bottom of the insert is set to a slope shape, and during installation, the height of the insert can be lowered by tilting the equipment box body to enter under the pressing piece.

[0011] Compared with the prior art, the utility model has the following advantages:

[0012] 1. The single-direction constraint of the pressing sheet on the insert on the device box is changed to a multi-axial composite constraint;

[0013] 2. Special installation steps are used to achieve the installation of multi-axial composite constraints;

[0014] 3. Use elastic pressing piece to generate pre-tightening force to ensure the combination of pressing piece and inserting piece on equipment box body is tight and reliable;

[0015] 4. Make the equipment box installed firmly and reliably, and bear the load reasonably, which can ensure the stability of equipment installation and reduce the overall weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of a conventional insert installation structure in the background technology of the present utility model;

[0017] Figure 2 This is a schematic structural diagram of Example 1 of the present utility model;

[0018] Figure 3 This is a schematic diagram of the installation of Example 1 of the utility model;

[0019] Figure 4 This is a schematic diagram of the tablet pressing structure in Example 1 of the present utility model (along the direction of insertion of the device box);

[0020] Figure 5 This is a schematic structural diagram of Example 2 of the present utility model;

[0021] Figure 1 1. Equipment box; 2. Pressing piece; 3. Inserting piece; 4. Bolt lug; 5. Mounting bolt; 6. Aircraft structure mounting surface;

[0022] Figure 2-4 Among them, 7, equipment box body; 8, pressing piece; 9, inserting piece; 10, meshing structure; 11, bolt ear piece; 12, mounting bolt; 13, aircraft structure mounting plane; 14, elastic section; 15, fixing bolt; 16, meshing section;

[0023] Figure 5 Among them, 7, equipment box body; 8, pressing piece; 9, inserting piece; 10, engaging structure; 11, bolt ear piece; 12, mounting bolt; 13, aircraft structure mounting plane. DETAILED DESCRIPTION

[0024] It should be noted that the terms "upper", "lower", "left", "right", etc. are described according to the drawings and do not constitute limitations of the present invention. Those skilled in the art should understand them in accordance with the technical solutions of the present invention. Example

[0025] The following is combined with Figure 2-4 The utility model is further described in detail: a device insert installation structure, such as Figure 2-3 As shown, it includes a device box body 7, a pressing piece 8, an inserting piece 9, a bolt ear piece 11, and a mounting bolt 12. The inserting piece 9 and the bolt ear piece 11 are respectively arranged at both ends of the device box body 7, and the device box body 7 is installed on the aircraft structure mounting plane 13; the pressing piece 8 and the inserting piece 9 are respectively designed with mutually matching protrusions and recessed structures, and the two together form an engaging structure 10. When the device box body 7 is installed in place, the engaging structure 10 can provide three axial constraints, solving the under-constraint problem of the conventional inserting piece installation method.

[0026] As a preferred implementation of this embodiment, in order to compensate for the fitting tolerance and generate a pre-tightening force between the pressing piece 8 and the inserting piece 9, the pressing piece 8 is designed as an elastic pressing piece in this embodiment. Figure 4As shown, the elastic pressing piece is designed with an elastic section 14 and an engaging section 16. The two ends of the elastic section 14 are mounted on the aircraft structure mounting plane 13 by fixing bolts 15. A gap is reserved between the middle part of the elastic section 14 and the aircraft structure mounting plane 13 to allow the insert 9 to enter. The engaging section 16 is arranged on the lower surface of the middle part of the elastic section 14, and its side facing the aircraft structure mounting plane 13 is a concave structure. In addition, the thickness of the elastic section 14 is calculated through stiffness analysis. The fitting relationship between the engaging section 16 and the insert 9 on the device box body 1 is designed to be an interference fit. During installation, the deformation of the elastic section 14 allows the engaging section 16 to produce a certain displacement in a direction perpendicular to the aircraft structure mounting plane 13, compensating for the interference and fitting tolerance, and ensuring that the pressing piece generates a continuous pre-tightening force on the insert after the device is installed, so that the device is installed firmly and reliably.

[0027] As a preferred embodiment of this embodiment, the bottom of the insert 9 is set to a slope, leaving a certain gap with the aircraft structure installation plane 13. When installing, the height of the insert 9 can be lowered by tilting the device box body 7 to enter under the pressing piece 8; the body installation method is as follows Figure 3 As shown, first tilt the device box body 7 so that the insert 9 is pushed under the pressing piece 8, then restore the device box body 7 to a horizontal level so that the insert 9 and the pressing piece 8 are engaged, and finally screw the mounting bolts 12 into the bolt ears 11 to connect them to the aircraft structure mounting plane 13 to complete the installation of the device box body 7. Example

[0028] The following is combined with Figure 5 The utility model is further described in detail: a device insert installation structure, such as Figure 5 As shown, it includes a device box body 7, a pressing piece 8, an inserting piece 9, a bolt ear piece 11, and a mounting bolt 12. The inserting piece 9 and the bolt ear piece 11 are respectively arranged at both ends of the device box body 1, and the device box body 7 is installed on the aircraft structure mounting plane 13; a protrusion and a recessed structure are provided on the mounting surface of the device box body 7 and the aircraft structure mounting plane 13, and the two together form a meshing structure 10; the bottom of the inserting piece 9 is set to a slope shape, and when installing, the height of the inserting piece 9 can be lowered by tilting the device box body 7 to enter under the pressing piece 8.

[0029] When the space on the aircraft structure mounting plane allows, the engaging structure 10 is arranged between the device box body 7 and the aircraft structure mounting plane 13, which can isolate the influence of the elastic pressing sheet stiffness on the overall mounting stiffness of the device and allow the elastic pressing sheet stiffness to be further reduced, thereby further improving the overall mounting stability and reducing the overall weight.

[0030] The above embodiments are merely preferred embodiments of the present invention and do not constitute limitations on the present invention. The structures of Examples 1 and 2 may be cross-adjusted as needed. Any extensions, modifications, equivalent substitutions, etc. made by persons of ordinary skill in the art without departing from the principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A device insert mounting structure, comprising a device box, a pressing piece, an insert, a bolt lug, and mounting bolts, wherein the device box is mounted on an aircraft structure mounting plane, and is characterized in that: The mating surfaces of the pressing piece and the inserting piece are provided with raised and recessed structures, which together form an engaging structure; the bottom of the inserting piece is set to be sloped, and during installation, the height of the inserting piece can be lowered by tilting the device box body to enter under the pressing piece. After the device box body returns to a horizontal state, the inserting piece and the pressing piece engage.

2. The device insert installation structure according to claim 1, characterized in that: The pressed tablet is an elastic pressed tablet.

3. The device insert installation structure according to claim 2, characterized in that: The elastic pressing piece includes an elastic section and an engaging section; the two ends of the elastic section are mounted on the aircraft structure mounting plane by fixing bolts; a gap is reserved between the middle part of the elastic section and the aircraft structure mounting plane to allow the insert to enter; the engaging section is arranged on the lower surface of the middle part of the elastic section, and its side facing the aircraft structure mounting plane is a concave structure.

4. The device insert installation structure according to claim 3, characterized in that: There are two engaging sections, which are distributed on the left and right sides of the pressing sheet in the inserting direction of the insert sheet.

5. The device insert installation structure according to claim 3, characterized in that: The fitting relationship between the meshing section and the insert is an interference fit.

6. A device insert mounting structure, comprising a device box, a pressing piece, an insert, a bolt lug, and mounting bolts, wherein the device box is mounted on an aircraft structure mounting plane, and is characterized in that: The mounting surface between the equipment box and the aircraft structure is provided with raised and recessed structures, which together form an engaging structure; the bottom of the insert is provided with a slope, and during installation, the height of the insert can be lowered by tilting the equipment box to enter under the pressing sheet.

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