Airplane inertial navigation locking quick-assembly and quick-disassembly device

Abstract

The utility model discloses an aircraft inertial navigation locking quick-assembly quick-disassembly device, which relates to the technical field of inertial navigation and comprises a shell and a bottom plate. According to the technical scheme, the limiting structure is installed on the base, the locking part installed on the side face of the shell is inserted into the limiting structure and matched with the three side face plates, positioning installation of the shell is achieved, and due to the fact that the locking part is inserted into the limiting structure, locking between the bottom plate and the shell is achieved by inserting and pulling out the locking part. Meanwhile, the bottom plate and the shell can be quickly disassembled and assembled, and the installation efficiency of the inertial navigation equipment is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of inertial navigation, and particularly relates to an aircraft inertial navigation locking quick installation and disassembly device. Background Technique

[0002] In order to enable the navigation system to exert the maximum accuracy during use, strict requirements are imposed on the installation of inertial navigation equipment.

[0003] In related technologies, the connection between the inertial navigation equipment and the installation bracket is mostly directly fastened and installed by screws, and during the installation process, multiple positions and operations are required to achieve it, resulting in difficult disassembly and assembly and reducing the installation efficiency. Content of the Utility Model

[0004] The main object of the utility model is to propose an aircraft inertial navigation locking quick installation and disassembly device, aiming to improve the installation efficiency of inertial navigation equipment.

[0005] To achieve the above object, the aircraft inertial navigation locking quick installation and disassembly device proposed by the utility model includes:

[0006] A bottom plate, on which a positioning space is provided, and a limiting structure is installed on the side of the bottom plate;

[0007] A housing, which is embedded in the positioning space, and a locking portion is provided on the side of the housing;

[0008] Wherein, the locking portion is inserted into the limiting structure and limits the housing on the bottom plate.

[0009] In an embodiment, the limiting structure includes a limiting portion, the limiting portion is provided on the side of the bottom plate, and a limiting groove with an opening facing the bottom plate is provided in the limiting portion, and the locking portion is inserted into the limiting groove.

[0010] In an embodiment, the limiting structure further includes a support rod, the support rod is rotatably arranged on the side of the bottom plate, the limiting portion passes through the support rod and is in threaded cooperation with the support rod, and the support rod passes through the limiting groove.

[0011] In an embodiment, a fixed seat is fixedly arranged on the bottom plate, one end of the fixed seat extends to one side of the bottom plate, and the support rod is rotatably arranged on the fixed seat.

[0012] In an embodiment, the locking portion and the limiting portion are arranged on the same plane.

[0013] In an embodiment, the aircraft inertial navigation locking quick installation and disassembly device further includes a positioning portion, the positioning portion passes through the side of the bottom plate and extends into the positioning space, and the positioning portion is inserted into the housing.

[0014] In one embodiment, the positioning portion includes a plug-in body and a limiting plate, the plug-in body is connected to the limiting plate, the plug-in body passes through the side of the base plate and is plugged into the shell, and the limiting plate abuts against the side of the base plate away from the positioning space.

[0015] In one embodiment, the plug-in body includes a first plug-in portion, a cone portion and a second plug-in portion, the first plug-in portion is connected to the cone portion, and the side of the cone portion facing away from the first plug-in portion is connected to the second plug-in portion, and the first plug-in portion and the cone portion are plugged into the shell.

[0016] In one embodiment, the diameter of the first plug-in portion is smaller than the diameter of the second plug-in portion.

[0017] In one embodiment, a limiting groove is provided in the shell, and a conical surface is provided on the side wall of the limiting groove opening.

[0018] The technical solution of the utility model is installed on the base through a limiting structure, and the locking part installed on the side of the shell is plugged into the limiting structure, and cooperates with the three side panels to realize the positioning and installation of the shell. Moreover, since the locking part is plugged into the limiting structure, the locking between the bottom plate and the shell is realized by plugging and pulling the locking part, and the rapid disassembly and assembly between the bottom plate and the shell is realized, thereby improving the installation efficiency of the inertial navigation device. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0020] Figure 1 A structural schematic diagram of an embodiment of an aircraft inertial navigation locking quick-install and quick-release device provided by the utility model;

[0021] Figure 2 A structural schematic diagram of another embodiment of the aircraft inertial navigation locking quick assembly and disassembly device provided by the utility model;

[0022] Figure 3 A structural schematic diagram of another embodiment of the aircraft inertial navigation locking quick assembly and disassembly device provided by the utility model;

[0023] Figure 4 A schematic structural diagram of a bottom plate in an embodiment of an aircraft inertial navigation locking quick-install and quick-release device provided by the utility model;

[0024] Figure 5 Schematic diagram of the structure of the positioning part in an embodiment of the aircraft inertial navigation locking quick-installation and quick-removal device provided by the present utility model;

[0025] Figure 6 Schematic diagram of the structure of the housing in an embodiment of the aircraft inertial navigation locking quick-installation and quick-removal device provided by the present utility model;

[0026] Figure 7 Schematic diagram of the structure of the locking part in an embodiment of the aircraft inertial navigation locking quick-installation and quick-removal device provided by the present utility model;

[0027] Figure 8 Schematic diagram of the structure of the limiting mechanism in an embodiment of the aircraft inertial navigation locking quick-installation and quick-removal device provided by the present utility model.

[0028] Explanation of the reference numerals in the drawings:

[0029] 100, aircraft inertial navigation locking quick-installation and quick-removal device; 10, housing; 20, bottom plate; 21, plate body; 22, positioning space; 23, through hole; 24, installation groove; 30, limiting structure; 31, support rod; 32, limiting part; 33, fixed seat; 34, limiting groove; 40, limiting structure; 41, first insertion part; 42, second insertion part; 43, limiting plate; 44, tapered part; 50, limiting groove; 60, locking part; 61, mounting seat; 62, connecting seat; 63, locking piece.

[0030] The realization, functional features and advantages of the purpose of the present utility model will be further described with reference to the embodiments and the accompanying drawings. Specific embodiments

[0031] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described with reference to the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without making creative efforts shall fall within the protection scope of the present utility model.

[0032] It should be noted that if there are directional indications (such as up, down, left, right, front, back...) involved in the embodiments of the present utility model, the directional indications are only used to explain the relative position relationship and movement conditions between components in a specific posture. If the specific posture changes, the directional indications will also change accordingly.

[0033] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present utility model, the descriptions of "first", "second", etc. are only for descriptive purposes and should not be construed as indicating or implying their relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In addition, if "and / or" or "and / or" appears throughout the text, its meaning includes three parallel scenarios. Taking "A and / or B" as an example, it includes Scenario A, or Scenario B, or the scenario where both A and B are satisfied simultaneously. In addition, the technical solutions between various embodiments can be combined with each other, but it must be based on the ability of those of ordinary skill in the art to implement. When the combination of technical solutions results in contradictions or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by the present utility model.

[0034] The present utility model provides an aircraft inertial navigation locking quick-installation and quick-disassembly device.

[0035] Please refer to Figure 1 , in an embodiment of the present utility model, the aircraft inertial navigation locking quick-installation and quick-disassembly device includes:

[0036] A bottom plate 20, on which a positioning space 22 is provided, and a limiting structure 30 is installed on the side of the bottom plate 20;

[0037] A housing 10, which is embedded in the positioning space 22, and a locking portion 60 is provided on the side of the housing 10;

[0038] Wherein, the locking portion 60 is inserted into the limiting structure 30 and restricts the housing 10 to the bottom plate 20.

[0039] As Figure 4 shown, the bottom plate 20 includes a plate body 21, the plate body includes a base and three side panels installed on the base, the three side panels are connected, and the three side panels and the base enclose to form the positioning space 22.

[0040] It can be understood that the housing 10 is arranged in the positioning space 22, and the side of the housing 10 contacts the three side panels to realize the installation and positioning of the housing 10.

[0041] As Figure 2 shown in Figure 7 connection seat 62, and the locking piece 63 is installed on the side of the connection seat 62 away from the mounting seat 61.

[0042] It should be noted that the mounting base 61 and the connecting base 62 are connected by screws.

[0043] It can be understood that the locking piece 63 is inserted into the limiting structure 34, and in cooperation with the limiting effect of the bottom plate 20 on the housing 10, the locking and limiting of the housing 10 are realized.

[0044] The technical solution of the present utility model is installed on the base through the limiting structure 30. The locking portion 60 installed on the side of the housing 10 is inserted into the limiting structure 30, and in cooperation with the three side panels, the positioning and installation of the housing 10 are realized. Moreover, since the locking portion 60 is inserted into the limiting structure 30, by inserting and pulling out the locking portion 60, the locking between the bottom plate 20 and the housing is realized, and at the same time, the rapid disassembly and assembly between the bottom plate 20 and the housing 10 are realized, improving the installation efficiency of the inertial navigation device.

[0045] In an embodiment, the limiting structure 30 includes a limiting portion 32. The limiting portion 32 is provided on the side of the bottom plate 20. A limiting groove 34 with an opening facing the bottom plate 20 is provided in the limiting portion 32, and the locking portion 60 is inserted into the limiting groove 34.

[0046] Such as Figure 2 And Figure 8 As shown, the limiting portion 32 is provided on the side of the bottom plate 20, so that the locking piece 63 can be inserted into the limiting groove 34 to realize the limitation of the housing 10.

[0047] It should be noted that in order to facilitate the insertion of the locking piece 63 into the limiting groove 34, a slope is provided on the outer side surface of the limiting portion 32, and the slope is provided on the outer side surface of the limiting portion 32 close to the housing 10.

[0048] It can be understood that when the locking piece 63 needs to be inserted into the limiting groove 34, the locking piece 63 is in contact with the slope on the outer side surface of the limiting portion 32, and the locking piece 63 can accurately extend into the limiting groove 34 along the slope, so as to ensure the assembly efficiency and quality of the locking piece 63 and the limiting groove 34.

[0049] In an embodiment, the limiting structure 30 further includes a support rod 31. The support rod 31 is rotatably provided on the side of the bottom plate 20. The limiting portion 32 passes through the support rod 31 and is in threaded cooperation with the support rod 31. The support rod 31 passes through the limiting groove 34.

[0050] It can be understood that the support rod 31 and the limiting portion 32 are in threaded cooperation. When the limiting portion 32 is driven to rotate, the limiting portion 32 moves along the support rod 31.

[0051] It is understandable that the support rod 31 passes through the limiting groove 34, so that the insertion space of the locking piece 63 is annular, thereby avoiding interference with the locking piece 63 during the rotation of the limiting portion 32 and affecting the limiting and fixing effect between the limiting portion 32 and the locking piece 63.

[0052] As Figure 1 shown in Figure 2 the figure, the support rod 31 is rotatably arranged on the side surface of the bottom plate 20. When it is necessary to cooperate with the locking piece 63 to limit the housing 10, by rotating the support rod 31 and rotating it in the direction close to the housing 10, the limiting portion 32 is brought closer to the locking piece 63, and then the limiting portion 32 is rotated to make the limiting groove 34 close to the locking piece 63. After the locking piece 63 is inserted into the limiting groove 34, continue to rotate the limiting portion 32 until the limiting portion 32 abuts against the locking piece 63, thereby realizing the limitation of the housing 10.

[0053] In an embodiment, a fixed seat 33 is fixedly arranged on the bottom plate 20. One end of the fixed seat 33 extends to one side of the bottom plate 20, and the support rod 31 is rotatably arranged on the fixed seat 33.

[0054] As Figure 4 shown in the figure, in order to facilitate the rotational fixation of the support rod 31 on the base and not affect the rotation of the support rod 31 and the installation of the housing 10, an installation groove 24 with an opening facing away from the positioning space is arranged on the base. The fixed seat 33 is arranged in the installation groove 24 and is connected to the base.

[0055] It should be noted that the fixed seat 33 and the base are connected by bolts.

[0056] It is understandable that a part of the fixed seat 33 extends out of the installation groove 24 and is rotatably connected to the support rod 31, avoiding interference between the rotation of the support rod 31 and the base and the housing 10, ensuring the rotation of the support rod 31, and cooperating with the limiting portion 32 and the locking piece 63 to improve the limiting effect on the housing 10.

[0057] In an embodiment, the locking portion 60 and the limiting portion 32 are arranged in the same plane.

[0058] It is understandable that the locking portion 60 and the limiting portion 32 are arranged in the same plane, which is convenient for the alignment and insertion cooperation between the limiting portion 32 and the locking piece 63, and ensures the limiting effect on the housing 10.

[0059] It should be noted that there are multiple limiting structures 30 , and the number of the locking portions 60 is the same as the number of the limiting structures 30 . The locking portions 60 and the limiting structures 30 are installed in alignment.

[0060] It is understandable that the limiting structure 30 and the locking portion 60 are both provided in plural numbers, so as to realize the limitation of the shell 10 on the bottom plate 20 at multiple points, strengthen the shell 10, and improve the limiting and positioning effect of the shell 10.

[0061] In one embodiment, the aircraft inertial navigation locking quick-install and quick-release device 100 further includes a positioning portion 40 , which is disposed through a side surface of the bottom plate 20 and extends into the positioning space 22 , and the positioning portion 40 is plugged into the housing 10 .

[0062] like Figure 2 and Figure 3 As shown, the positioning portion 40 is installed on the side panel and abuts against the outer side surface of the housing 10 .

[0063] It can be understood that the positioning portion 40 abuts against the shell 10, so that the shell 10 is positioned and restricted along the extension direction of the positioning portion 40, and the positioning portion 40 is inserted into the shell 10, so that the shell 10 is positioned and restricted in a direction perpendicular to the extension direction of the positioning portion 40, and then by arranging the positioning portion 40 on the base plate 20, the shell 10 is accurately positioned on the base plate 20, thereby improving the assembly accuracy of the shell 10 on the base plate 20.

[0064] It should be noted that, in order to improve the positioning effect, a plurality of positioning portions 40 are provided, and the plurality of positioning portions 40 are arranged at intervals on the side panel.

[0065] In one embodiment, the positioning portion 40 includes a plug-in body and a limit plate 43, the plug-in body is connected to the limit plate 43, the plug-in body passes through the side of the base plate 20, and is plugged into the shell 10, and the limit plate 43 abuts against the side of the base plate 20 away from the positioning space 22.

[0066] like Figure 5 As shown, in order to avoid the positioning part 40 completely penetrating the side panel during the installation of the positioning part 40 and causing a reduction in the positioning effect, the positioning part 40 includes the plug-in body and the limit plate 43. When the plug-in body penetrates the side panel and extends into the shell 10, the limit plate 43 abuts against the side surface of the side panel to achieve the positioning installation of the positioning part 40.

[0067] It should be noted that the limiting plate 43 is bolted to the side panel.

[0068] It can be understood that by the abutment of the limiting plate 43 against the side panel, the stability of the installation of the positioning portion 40 on the side panel is ensured, thereby improving the positioning stability effect of the positioning portion.

[0069] In an embodiment, the plugging main body includes a first plugging portion 41, a tapered portion 44 and a second plugging portion 42. The first plugging portion 41 is connected to the tapered portion 44, and the side of the tapered portion 44 facing away from the first plugging portion 41 is connected to the second plugging portion 42. The first plugging portion 41 and the tapered portion 44 are plugged into the housing 10.

[0070] As Figure 2 , Figure 3 and Figure 5 shown, when the positioning portion 40 penetrates the side panel, the second plugging portion 42 is in a state of penetrating the side panel, while the tapered portion 44 and the first plugging portion 41 are in a state of extending into the housing 10.

[0071] It can be understood that the positioning of the housing 10 is achieved by inserting the tapered portion 44 and the first plugging portion 41 into the housing 10.

[0072] It can be understood that in order to facilitate the penetration of the second plugging portion 42, a through hole 23 is provided on the side panel.

[0073] It should be noted that when the number of the positioning portions is multiple, the number of the through holes 23 is greater than or equal to the number of the positioning portions, and the multiple through holes 23 are spaced apart.

[0074] In an embodiment, the diameter of the first plugging portion 41 is smaller than the diameter of the second plugging portion 42.

[0075] As Figure 5 shown, the diameters of the first plugging portion 41 and the second plugging portion 42 are different, and the first plugging portion 41 and the second plugging portion 42 are transitionally connected through the tapered portion 44.

[0076] It can be understood that, since the diameters of the first insertion part 41 and the second insertion part 42 are different, when the first insertion part 41 is inserted into the housing 10, the housing 10 directly abuts against the second insertion part 42. Then, when the locking piece 63 is inserted into the limiting groove 34 and the locking piece 63 abuts against the insertion part 32, in cooperation, the housing 10 abuts against the second insertion part 42, effectively achieving the locking effect of the housing 10. And in cooperation with the positioning part 40, the positioning effect of the housing 10 on the bottom plate 20 is realized. In this way, the quick disassembly and quick assembly of the housing 10 on the bottom plate 20 are realized, the assembly efficiency of the housing 10 is improved, the positioning quality is improved, and the positioning difficulty is reduced.

[0077] In an embodiment, a limiting groove 50 is provided in the housing 10, and a conical surface is provided on the side wall at the opening of the limiting groove 50.

[0078] It can be understood that, as Figure 6 shown, the setting of the limiting groove 50 is to facilitate the accommodation of the first insertion part 41 and the conical part 44.

[0079] It should be noted that the side wall at the opening of the limiting groove 50 is set as a conical surface to facilitate the expansion of the opening of the limiting groove 50. When the first insertion part 41 needs to be inserted into the limiting groove 50, after the first insertion part 41 comes into contact with the conical surface, the first insertion part 41 can move along the inclined surface and finally be accurately positioned in cooperation with the limiting groove 50, improving the positioning quality and efficiency.

[0080] It can be understood that the conical part 44 is in close contact with the conical surface.

[0081] It can be understood that the conical part 44 is the connecting part between the first insertion part 41 and the second insertion part 42. When the conical part 44 is in close contact with the conical surface, the acting force on the housing 10 after the close cooperation between the locking piece 63 and the limiting part 32 can be transmitted to the second insertion part 42 through the conical part 44 to ensure the stability of the restriction of the housing 10.

[0082] The above are only exemplary embodiments of the present invention, and do not limit the patent scope of the present invention. Any equivalent structural transformation made under the technical concept of the present invention by using the content of the specification and drawings of the present invention, or directly / indirectly applied in other related technical fields, is included in the patent protection scope of the present invention.

Claims

1. An aircraft inertial navigation locking quick-installation and quick-disassembly device, characterized in that, include: A bottom plate, wherein a positioning space is provided on the bottom plate, and a limiting structure is installed on a side of the bottom plate; A shell, the shell is embedded in the positioning space, and a locking portion is provided on a side of the shell; Wherein, the locking portion is inserted into the limiting structure and limits the shell to the bottom plate.

2. The aircraft inertial navigation locking quick-installation and quick-disassembly device according to claim 1, characterized in that The limiting structure comprises a limiting portion, the limiting portion is arranged on the side of the bottom plate, a limiting groove with an opening toward the bottom plate is arranged in the limiting portion, and the locking portion is inserted into the limiting groove.

3. The aircraft inertial navigation locking quick-installation and quick-disassembly device according to claim 2, characterized in that, The limiting structure also includes a support rod, which is rotatably arranged on the side of the bottom plate, the limiting portion is penetrated by the support rod and threadably matched with the support rod, and the support rod is penetrated by the limiting groove.

4. The aircraft inertial navigation locking quick-installation and quick-disassembly device according to claim 3, characterized in that, A fixing seat is fixedly arranged on the bottom plate, one end of the fixing seat extends to one side of the bottom plate, and the support rod is rotatably arranged on the fixing seat.

5. The aircraft inertial navigation locking quick-installation and quick-disassembly device according to claim 4, characterized in that The locking portion and the limiting portion are arranged on the same plane.

6. The aircraft inertial navigation locking quick-installation and quick-disassembly device according to claim 2, characterized in that, The aircraft inertial navigation locking quick-install and quick-release device also includes a positioning portion, which is penetrated through the side surface of the bottom plate and extends into the positioning space, and the positioning portion is plugged into the shell.

7. The aircraft inertial navigation locking quick-installation and quick-disassembly device according to claim 6, characterized in that, The positioning part includes a plug-in body and a limiting plate, the plug-in body is connected to the limiting plate, the plug-in body passes through the side of the bottom plate and is plugged into the shell, and the limiting plate abuts against the side of the bottom plate away from the positioning space.

8. The aircraft inertial navigation locking quick installation and quick disassembly device according to claim 7, characterized in that, The plug-in body includes a first plug-in portion, a cone portion and a second plug-in portion, the first plug-in portion is connected to the cone portion, and the side of the cone portion facing away from the first plug-in portion is connected to the second plug-in portion, and the first plug-in portion and the cone portion are plugged into the shell.

9. The aircraft inertial navigation locking quick-installation and quick-disassembly device according to claim 8, characterized in that, The diameter of the first plug-in portion is smaller than the diameter of the second plug-in portion.

10. The aircraft inertial navigation locking quick installation and disassembly device according to claim 8, characterized in that, A limiting groove is arranged in the shell, and a conical surface is arranged on the side wall at the opening of the limiting groove.

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