CN216576793U - Vacuum tool for machining airplane parts - Google Patents

Abstract

The utility model provides a vacuum tool for processing airplane parts, which can reduce the deformation of parts in the processing process, simplify the process scheme, ensure the thickness of a web plate and the position degree of holes, and ensure the product quality.

Description

Vacuum tool for machining airplane parts

Technical Field

The utility model relates to the field of airplane part machining, in particular to a vacuum tool for airplane part machining.

Background

In prior art, there is the part that web thickness is 0.5mm, and the part side is opened there is the smart hole that position accuracy requires highly, and the web very easily produces and warp, needs a lot of processing to ensure web thickness and plane degree, guarantees that hole site degree is qualified, adopts original processing mode, can cause the processing cycle long, consumes a large amount of manpowers, material resources and financial resources, and has the risk that web thickness and hole site degree are out of tolerance.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a vacuum tool for machining airplane parts, which can reduce the deformation of parts in the machining process, simplify the technical scheme, ensure the thickness of a web plate and the position degree of a hole and ensure the product quality.

The embodiment of the utility model is realized by the following steps:

the utility model provides a vacuum frock for aircraft parts machining, this vacuum frock includes the frock body, the frock body is the plate body form, the surface of frock body is the holding surface, the center of holding surface is provided with the locating surface of class trefoil form, the locating surface is provided with annular seal groove and vertical seal groove, annular seal groove sets up along class trefoil form locating surface a week, the vertical setting of vertical seal groove, the both ends and the annular seal groove of vertical seal groove link up, at least one bottom in annular seal groove and the vertical seal groove is provided with the air vent, the suction nozzle has been seted up to the side of frock body, the suction nozzle link up with the air vent.

In a preferred embodiment of the present invention, the supporting surface is further provided with positioning pin holes, the plurality of positioning pin holes are located on a ring side of the positioning surface, and the positioning pin holes are distributed at four corners of the supporting surface.

In a preferred embodiment of the present invention, there are 4 positioning pin holes.

In a preferred embodiment of the present invention, the supporting surface is further provided with a threaded hole, and the plurality of threaded holes are disposed on the ring side of the positioning surface.

In a preferred embodiment of the present invention, the number of the threaded holes is 8, each two threaded holes are in a group, and a group of threaded holes is respectively disposed on four corners of the supporting surface.

In a preferred embodiment of the present invention, the positioning pin hole is located between two threaded holes.

The embodiment of the utility model has the beneficial effects that: according to the vacuum tool, the leaf-like positioning surface is arranged on the supporting surface, the annular sealing groove and the vertical sealing groove are formed in the positioning surface, the shapes of the annular sealing groove and the parts are matched, part of the structures of the parts enter the vertical sealing groove, the airplane parts are machined in a vacuum adsorption mode, deformation of the parts in the machining process is reduced, the process scheme is simplified, the thickness of a web plate and the position degree of holes are guaranteed, and the product quality is guaranteed.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is a schematic view of a surface structure of a tool body according to an embodiment of the present invention;

FIG. 2 is a schematic sectional view of a tooling of an embodiment of the present invention;

icon: 100-a tool body; 110-a support surface; 120-a positioning surface; 130-a vent; 140-a suction nozzle; 150-dowel holes; 160-threaded hole.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships based on orientations or positional relationships shown in the drawings or orientations or positional relationships that are conventionally placed when the products of the present invention are used, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

First embodiment

Referring to fig. 1-2, the present embodiment provides a vacuum tool for aircraft part processing, the vacuum tool includes a tool body 100, the tool body 100 is plate-shaped, the surface of the tool body 100 is a supporting surface 110, a leaf-like positioning surface 120 is disposed at the center of the supporting surface 110, the positioning surface 120 is provided with an annular sealing groove and a vertical sealing groove, the annular sealing groove is disposed along a circumference of the leaf-like positioning surface 120, the vertical sealing groove is vertically disposed, two ends of the vertical sealing groove are communicated with the annular sealing groove, an air vent 130 is disposed at the bottom of at least one of the annular sealing groove and the vertical sealing groove, an air suction nozzle 140 is disposed on a side surface of the tool body 100, and the air suction nozzle 140 is communicated with the air vent 130.

When the part needs vacuum adsorption, put the part in locating surface 120 department, make part lower surface and the laminating of frock locating surface 120, open the vacuum pump and make the sealed tank formation vacuum environment of frock body 100, adsorb the part to can guarantee parts machining, this frock location is accurate, the product percent of pass is high, processing convenient and fast.

In this embodiment, the supporting surface 110 is further provided with positioning pin holes 150, the plurality of positioning pin holes 150 are located on the ring side of the positioning surface 120, the positioning pin holes 150 are distributed at four corners of the supporting surface 110, and the number of the positioning pin holes 150 is 4. The support surface 110 is further provided with a plurality of threaded holes 160, and the plurality of threaded holes 160 are disposed on the ring side of the positioning surface 120. The number of the threaded holes 160 is 8, each two of the threaded holes are a group, and a group of the threaded holes 160 is respectively arranged on four corners of the supporting surface 110. The positioning pin hole 150 is located between the two threaded holes 160, the aircraft part in this embodiment is clamped on the positioning surface 120, a positioning pin is inserted through the positioning pin hole 150 to position the aircraft part, then the aircraft part is fixed on the supporting surface 110 by a screw, and finally the vacuum equipment is started to adsorb the web of the workpiece on the supporting surface 110.

In conclusion, the vacuum tool in this embodiment is provided with the locating surface 120, closely laminate the aircraft part, be provided with the seal groove on the locating surface 120, the seal groove is inwards sunken, and set up air vent 130 on locating surface 120, air vent 130 link up with inside air vent and extend to the suction nozzle 140 outside the holding surface 110, suction nozzle 140 is connected to the vacuum pump through the trachea, when needs adsorb the aircraft part, place the part in seal groove department, make the part lower surface laminate with the frock locating surface 120, open the vacuum pump and make the seal groove formation vacuum environment of tool body 100, adsorb the part, thereby can guarantee thin web parts machining.

This description describes examples of embodiments of the utility model, and is not intended to illustrate and describe all possible forms of the utility model. It should be understood that the embodiments described in this specification can be implemented in many alternative forms. The figures are not necessarily to scale; some features may be exaggerated or minimized to show details of particular components. Specific structural and functional details disclosed are not to be interpreted as limiting, but merely as a representative basis for teaching one skilled in the art to variously employ the present invention. It will be appreciated by persons skilled in the art that a plurality of features illustrated and described with reference to any one of the figures may be combined with features illustrated in one or more other figures to form embodiments which are not explicitly illustrated or described. The described combination of features provides a representative embodiment for a typical application. However, various combinations and modifications of the features consistent with the teachings of the present invention may be used as desired for particular applications or implementations.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (6)

1. The utility model provides a vacuum frock for aircraft parts machining, a serial communication port, vacuum frock includes the frock body, the frock body is the plate form, the surface of frock body is the holding surface, the center of holding surface is provided with the locating surface of class trefoil form, the locating surface is provided with annular seal groove and vertical seal groove, the annular seal groove is followed class trefoil form locating surface a week sets up, the vertical setting of vertical seal groove, the both ends of vertical seal groove with the annular seal groove link up, at least one bottom in annular seal groove and the vertical seal groove is provided with the air vent, the suction nozzle has been seted up to the side of frock body, the suction nozzle with the air vent link up.

2. The vacuum tool for machining aircraft parts according to claim 1, wherein the supporting surface is further provided with positioning pin holes, the positioning pin holes are located on the ring side of the positioning surface, and the positioning pin holes are distributed at four corners of the supporting surface.

3. The vacuum tool for aircraft part machining according to claim 2, wherein the number of the positioning pin holes is 4.

4. The vacuum tool for aircraft part machining according to claim 3, wherein the supporting surface is further provided with threaded holes, and the threaded holes are formed in the ring side of the positioning surface.

5. The vacuum tool for the aircraft part machining according to claim 4, wherein the number of the threaded holes is 8, every two threaded holes form a group, and four corners of the supporting surface are respectively provided with a group of the threaded holes.

6. The vacuum tooling for aircraft part machining according to claim 5, wherein the dowel hole is located between two of the threaded holes.

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