CN215035669U - Cambered surface tool for machining airplane parts - Google Patents
Cambered surface tool for machining airplane parts Download PDFInfo
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- CN215035669U CN215035669U CN202120779373.9U CN202120779373U CN215035669U CN 215035669 U CN215035669 U CN 215035669U CN 202120779373 U CN202120779373 U CN 202120779373U CN 215035669 U CN215035669 U CN 215035669U
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- positioning
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- cambered surface
- cambered
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Abstract
The utility model provides a cambered surface frock for processing aircraft part, it can reduce the part in the course of working and warp, simplifies the process scheme, guarantees the precision of part, guarantees product quality, including the frock body, its frock body includes holding surface and the locating surface of setting in the middle part of the holding surface, and the holding surface is the plane, and the locating surface is the cambered surface, and the locating surface is laminated with the cambered surface of aircraft part; the positioning surface is provided with a plurality of sealing grooves which are formed by inwards sinking from the surface of the positioning surface, the positioning surface is provided with vent holes, the vent holes are communicated with the vent grooves in the tool body, the side surface of the supporting surface is provided with a suction nozzle, and the suction nozzle is communicated with the vent grooves.
Description
Technical Field
The utility model relates to an aircraft parts machining field particularly, relates to a cambered surface frock for processing aircraft part.
Background
In the prior art, a cambered surface part is an important component of the overall appearance structure of an airplane, and due to the special structure and the use requirement of the part, the airplane part is very thin, so that a large amount of deformation is easily generated in the machining process, and the precision cannot be guaranteed in the machining process.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a cambered surface frock for processing aircraft part, it can reduce the part in the deformation of course of working, simplifies technical scheme, guarantees the precision of part, guarantees product quality.
The embodiment of the utility model is realized like this:
a cambered surface tool for processing an airplane part comprises a tool body, wherein the tool body comprises a supporting surface and a positioning surface arranged in the middle of the supporting surface, the supporting surface is a plane, the positioning surface is a cambered surface, and the positioning surface is attached to the cambered surface of the airplane part; the positioning surface is provided with a plurality of sealing grooves which are formed by inwards sinking from the surface of the positioning surface, the positioning surface is provided with vent holes, the vent holes are communicated with the vent grooves in the tool body, the side surface of the supporting surface is provided with a suction nozzle, and the suction nozzle is communicated with the vent grooves.
In a preferred embodiment of the present invention, the sealing groove is a square sealing groove.
In the preferred embodiment of the present invention, the surface of the supporting surface is further provided with a threaded hole and a positioning pin hole, and the aircraft part is fixed on the tool body by a screw and a fixing pin.
In a preferred embodiment of the present invention, the threaded holes and the positioning pin holes are spaced apart from each other.
In a preferred embodiment of the present invention, the surface of the supporting surface is further provided with positioning holes.
In a preferred embodiment of the present invention, a verification edge is further disposed on one corner of the supporting surface.
The embodiment of the utility model provides a beneficial effect is: the utility model provides a cambered surface frock is provided with curved locating surface, closely laminate aircraft part, be provided with the seal groove on the locating surface, the seal groove is inside sunken, and set up the air vent on the locating surface, the air vent link up with inside air channel and extend to the outer air exhaust mouth of holding surface, air exhaust mouth passes through the trachea and is connected to the vacuum pump, when needs adsorb aircraft part, place the part in seal groove department, make part lower surface and the laminating of frock cambered surface, open the vacuum pump and make the seal groove of frock body form vacuum environment, adsorb the part, thereby can guarantee thinner arc aircraft parts machining.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required 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 perspective view of an embodiment of the present invention;
FIG. 2 is a schematic view of a cross-sectional structure of a cambered surface tool according to an embodiment of the present invention;
icon: 100-arc surface tooling; 110-a support surface; 120-a positioning surface; 121-seal groove; 122-a vent; 123-a vent groove; 111-suction nozzle; 112-a threaded hole; 113-positioning pin holes; 114-a locating hole; 115-verify edge.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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, 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, as 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 accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to 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", and the like indicate the position or positional relationship based on the position or positional relationship shown in the drawings, or the position or positional relationship which is usually placed when the product of the present invention is used, and are only for convenience of description and simplification of the description, but do not indicate or imply that the device or element referred to must have a specific position, 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, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; 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 meaning 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 and fig. 2, the present embodiment provides an arc surface tool 100 for processing an aircraft part, including a tool body, where the tool body includes a supporting surface 110 and a positioning surface 120 disposed in the middle of the supporting surface 110, the supporting surface 110 is a plane, the positioning surface 120 is an arc surface, and the positioning surface 120 is attached to the arc surface of the aircraft part.
The positioning surface 120 is provided with a plurality of sealing grooves 121, the sealing grooves 121 are formed by inwards sinking from the surface of the positioning surface 120, the positioning surface 120 is provided with vent holes 122, the vent holes 122 are communicated with vent grooves 123 inside the tool body, the side surface of the supporting surface 110 is provided with an air suction nozzle 111, the air suction nozzle 111 is communicated with the vent grooves 123, and the bottom of the sealing grooves 121 is in a grid shape.
In this embodiment, a plurality of square sealing grooves are formed in the arc surface, and the sealing groove 121 is formed by inwards recessing the surface of the arc surface of the tool; open on the cambered surface has air vent 122, link up each other with the inside air channel 123 of frock body, it has exhaust nozzle 111 to open in the frock body side, link up each other with inside air channel 123, air channel 123 passes through exhaust nozzle 111, trachea and vacuum pump connection form the circulation, when needs adsorb this type of part, place the part in seal groove 121 department, make part lower surface and frock cambered surface laminating, open the vacuum pump and make the seal groove 121 of frock body form vacuum environment, adsorb the part, thereby can guarantee parts machining.
More specifically, the surface of the support surface 110 in this embodiment is further provided with a threaded hole 112 and a positioning pin hole 113, and the aircraft component is fixed on the tool body by a screw and a fixing pin. The threaded hole 112 and the positioning pin hole 113 are arranged at intervals, and for better matching with airplane parts, a lug is arranged at the position of the threaded hole 112. The surface of the supporting surface 110 is further provided with a positioning hole 114 for positioning the tool. A verification edge 115 is also provided on one corner of the support surface 110 as a precaution against errors during the machining process.
In conclusion, the utility model provides a cambered surface frock 100 is provided with curved locating surface 120, closely laminate the aircraft part, be provided with seal groove 121 on the locating surface 120, seal groove 121 is inside sunken, and set up air vent 122 on locating surface 120, air vent 122 link up and extend to the outer suction nozzle 111 of holding surface 110 with inside air channel 123, suction nozzle 111 passes through the trachea and is connected to the vacuum pump, when needs adsorb the aircraft part, place the part in seal groove 121 department, make part lower surface and the laminating of frock cambered surface, it makes the seal groove 121 of frock body form vacuum environment to open the vacuum pump, adsorb the part, thereby can guarantee thinner arc aircraft parts machining, this frock location is accurate, the product percent of pass is high, processing convenient and fast.
This description describes examples of embodiments of the invention, and is not intended to illustrate and describe all possible forms of the invention. 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 is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to 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 cambered surface tool for machining the airplane part comprises a tool body and is characterized in that the tool body comprises a supporting surface and a positioning surface arranged in the middle of the supporting surface, the supporting surface is a plane, the positioning surface is a cambered surface, and the positioning surface is attached to the cambered surface of the airplane part; the tool comprises a tool body and is characterized in that a plurality of sealing grooves are formed in the positioning surface, the sealing grooves are formed by inwards recessing the surface of the positioning surface, vent holes are formed in the positioning surface, the vent holes are communicated with vent grooves in the tool body, the side face of the supporting surface is provided with an air suction nozzle, and the air suction nozzle is communicated with the vent grooves.
2. The cambered surface tool for machining aircraft parts according to claim 1, wherein the sealing groove is a square sealing groove.
3. The cambered surface tool for machining aircraft parts according to claim 1, wherein the surface of the supporting surface is further provided with a threaded hole and a positioning pin hole, and the aircraft parts are fixed on the tool body through screws and fixing pins.
4. The cambered surface tool for machining aircraft parts according to claim 3, wherein the threaded hole and the locating pin hole are arranged at intervals.
5. The cambered surface tool for machining aircraft parts according to claim 1, wherein the surface of the supporting surface is further provided with positioning holes.
6. The cambered surface tool for machining aircraft parts according to claim 1, wherein a verifying edge is further arranged on one corner of the supporting surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120779373.9U CN215035669U (en) | 2021-04-16 | 2021-04-16 | Cambered surface tool for machining airplane parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120779373.9U CN215035669U (en) | 2021-04-16 | 2021-04-16 | Cambered surface tool for machining airplane parts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215035669U true CN215035669U (en) | 2021-12-07 |
Family
ID=79105908
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120779373.9U Active CN215035669U (en) | 2021-04-16 | 2021-04-16 | Cambered surface tool for machining airplane parts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215035669U (en) |
-
2021
- 2021-04-16 CN CN202120779373.9U patent/CN215035669U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 611330 No. 18, Ganxi Road, Industrial Development Zone, Jinyuan Town, Dayi County, Chengdu, Sichuan Patentee after: Chengdu chaohepur Aviation Technology Co.,Ltd. Address before: 611330 No. 18, Ganxi Road, Industrial Development Zone, Jinyuan Town, Dayi County, Chengdu, Sichuan Patentee before: CHENGDU JIAODA PUER INDUSTRIAL Co.,Ltd. |
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| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 611330 No. 18, Ganxi Road, Industrial Development Zone, Jinyuan Town, Dayi County, Chengdu, Sichuan Patentee after: Chengdu Chaohepu Aviation Technology Co.,Ltd. Address before: 611330 No. 18, Ganxi Road, Industrial Development Zone, Jinyuan Town, Dayi County, Chengdu, Sichuan Patentee before: Chengdu chaohepur Aviation Technology Co.,Ltd. |