CN217412574U - Detection block assembly for milling tool of aircraft panel - Google Patents
Detection block assembly for milling tool of aircraft panel Download PDFInfo
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- CN217412574U CN217412574U CN202220983346.8U CN202220983346U CN217412574U CN 217412574 U CN217412574 U CN 217412574U CN 202220983346 U CN202220983346 U CN 202220983346U CN 217412574 U CN217412574 U CN 217412574U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02W—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO WASTEWATER TREATMENT OR WASTE MANAGEMENT
- Y02W30/00—Technologies for solid waste management
- Y02W30/50—Reuse, recycling or recovery technologies
- Y02W30/62—Plastics recycling; Rubber recycling
Abstract
The utility model discloses a detection block component for an aircraft panel milling tool, which comprises a detection frame and at least one independent detection block; the shape of the inner edge of the detection frame is matched with the shape of the outer edge of a tire molding assembly of the milling tool for the aircraft wall plate, and the outer edge of the detection frame is of a regular linear structure; the independent detection block is matched with the through groove of the tire molding assembly in shape, and detection gaps are respectively arranged between the inner edge of the detection frame and the outer edge of the tire molding assembly and between the independent detection block and the through groove of the tire molding assembly; the detection frame and the independent detection block are connected with the milling tool of the aircraft wallboard. The utility model discloses a detect the frame and independently detect and form between piece and the type subassembly and detect the clearance, the error detection of completion part that the cooperation standard ruler can be quick, accurate, and the testing result is accurate, reliable.
Description
Technical Field
The utility model relates to an aircraft spare part processingequipment technical field, in particular to aircraft wallboard mills detection block subassembly for frock.
Background
The aircraft wallboard part is generally a thin-walled part with an irregular curved surface, and the part needs to be firmly clamped by a tool during numerical control machining, so that the phenomenon that the part is out of tolerance or scrapped due to the fact that a broach, a cutter spring and the like are formed in the machining process of the part is prevented.
The milling tool for the aircraft panel is mainly used for fixing the aircraft panel, the aircraft panel is directly fixed with a molding die assembly (also called a molding surface die matrix) when the milling tool is used, and errors are easily generated at the processing part of the aircraft panel (part). The machining error is usually determined by manual observation, and the method has large error, and the direct result is that the machining error of the part cannot be found in time and the unqualified part cannot be picked out in time.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome prior art not enough, provide an aircraft wallboard mills detection block subassembly for frock, through detecting the frame and independently detect and form between piece and the type child subassembly and detect the clearance, the error detection of completion part that the cooperation standard ruler can be quick, accurate, and the testing result is accurate, reliable.
The purpose of the utility model is realized through the following technical scheme:
a detection block assembly for an aircraft panel milling tool comprises a detection frame and at least one independent detection block;
the shape of the inner edge of the detection frame is matched with the shape of the outer edge of a tire molding assembly of the milling tool of the aircraft wall plate, and the outer edge of the detection frame is of a regular linear structure;
the independent detection block is matched with the through groove of the tire molding assembly in shape, and detection gaps are respectively arranged between the inner edge of the detection frame and the outer edge of the tire molding assembly and between the independent detection block and the through groove of the tire molding assembly;
the detection frame and the independent detection block are connected with the milling tool of the aircraft wallboard.
Further, the detection frame is of a split structure.
Furthermore, the detection frame comprises two connection detection blocks which are symmetrically arranged and half frames which are symmetrically arranged at two sides of the two connection detection blocks, each half frame comprises a side edge and two transverse edges, one end of each transverse edge is connected with the connection detection block, and two ends of each side edge are connected with the other end of each transverse edge;
the outer edge of one transverse edge is of an inverted-.
Further, the detection frame and the independent detection block are connected with the milling tool of the aircraft wall plate through bolts.
Furthermore, the bottoms of the detection frame and the independent detection block are provided with cushion blocks for adjusting the inclination of the detection frame and the inclination of the independent detection block.
Furthermore, a reference block is arranged on the connection detection block.
The utility model has the advantages that:
the utility model discloses a detect frame and independently detect and form between piece and the type child subassembly and detect the clearance, the error detection of completion part that the cooperation standard ruler can be quick, accurate, and the testing result is accurate, reliable.
Drawings
Fig. 1 is a perspective view of a detection block assembly for an aircraft panel milling tool in an embodiment of the present invention;
fig. 2 is a top view of the detection block assembly for the aircraft panel milling tool in the embodiment of the present invention;
fig. 3 is a front view of the detection block assembly for the aircraft panel milling tool in the embodiment of the present invention;
fig. 4 is a schematic structural diagram of a tire assembly of an aircraft panel milling tool according to an embodiment of the present invention;
fig. 5 is a use state diagram of the detection block assembly for the aircraft panel milling tool in the embodiment of the present invention;
in the figure, 1, detecting a frame; 2. an independent detection block; 3. a tire assembly; 4. connecting a detection block; 5. half frame; 6. a side edge; 7. transverse edges; 8. a cushion block; 9. a reference block.
Detailed Description
The technical solution of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by those skilled in the art without creative efforts belong to the protection scope of the present invention.
Referring to fig. 1-5, the present invention provides a technical solution:
example (b):
as shown in fig. 1 to 5, a detection block assembly for an aircraft panel milling tool comprises a detection frame 1 and four independent detection blocks 2;
the shape of the inner edge of the detection frame 1 is matched with the shape of the outer edge of a tire molding assembly 3 of the milling tool of the aircraft wall plate, and the outer edge of the detection frame 1 is of a regular linear structure;
the shape of the independent detection block 2 is matched with that of the through groove of the tire molding assembly 3, detection gaps are respectively arranged between the inner edge of the detection frame 1 and the outer edge of the tire molding assembly 3 and between the independent detection block 2 and the through groove of the tire molding assembly 3, wherein the detection gaps are X in a figure 5;
the detection frame 1 and the independent detection block 2 are connected with an aircraft wallboard milling tool.
The detection frame 1 and the independent detection block 2 are connected with an aircraft panel milling tool through bolts.
The working principle is as follows: the inner edge of the detection frame 1 surrounds the outer edge of the tire building component 3, a detection gap of 2-3mm is formed between the inner edge and the outer edge of the tire building component 3, and a detection gap of 2-3mm is formed between the outer edge of the independent detection block 2 and the inner edge of the through groove of the tire building component 3.
The aircraft wall plate (hereinafter referred to as a part) is fixed on the mould assembly 3 for processing, and the processed part is matched with the shape of the mould assembly 3. And after the machining is finished, the error detection of the part can be started.
The error detection process of the part is as follows: and detecting whether the clearance between the part and the detection block assembly is consistent with the detection clearance size within an error range by a standard ruler (which can be but is not limited to a feeler gauge), if so, determining that the clearance is qualified, and if not, determining that the clearance is unqualified.
The shape of the inner edge of the detection frame 1 is matched with the shape of the outer edge of a tire molding assembly 3 of the milling tool of the aircraft wall plate, and the detection gaps are guaranteed to be uniform. The outer fringe that detects frame 1 is the linear structure of rule, can guarantee to detect the wholeness of frame 1, and whether the regularity of accessible outer fringe judges that detection frame 1 installs in place when the installation simultaneously, and then guarantees the precision that detects.
The utility model discloses a detect frame 1 and independently detect and form between piece 2 and the type child subassembly 3 and detect the clearance, the error detection of completion part that the cooperation standard ruler can be quick, accurate, and the testing result is accurate, reliable.
Further, as shown in fig. 1 and fig. 2, the detection frame 1 is a split structure.
The detection frame 1 comprises two symmetrically arranged connection detection blocks 4 and half frames 5 symmetrically arranged at two sides of the two connection detection blocks 4, each half frame 5 comprises a side edge 6 and two transverse edges 7, one end of each transverse edge 7 is connected with the connection detection block 4, and two ends of each side edge 6 are connected with the other end of each transverse edge 7;
the outer edge of one transverse edge 7 is of an inverted-.
The side edge 6 comprises three detection blocks, the horizontal side edge 7 in a zigzag shape comprises seven detection blocks, and the horizontal side edge 7 in a circular arc shape comprises three detection blocks, and the specific structure is shown in the figure.
The detection frame 1 is of a split structure, so that the detection frame is conveniently connected with a milling tool, and the independent detection block is connected with the milling tool through two bolts and is stable in connection. And the connecting block is convenient to replace when damaged.
Further, as shown in fig. 1 and fig. 2, the bottoms of the detection frame 1 and the independent detection block 2 are provided with a cushion block 8 for adjusting the inclination of the detection frame 1 and the independent detection block 2. The cushion block 8 is used for guaranteeing that the radian and the gradient of the detection frame 1 and the independent detection block 2 are the same as those of the milling tool.
Further, as shown in fig. 1 and 2, the connection detection block 4 is provided with a reference block 9. The arranged reference block is convenient for connecting the installation, the positioning and the,
The foregoing is illustrative of the preferred embodiments of the present invention, and it is to be understood that the invention is not limited to the precise forms disclosed herein and that the invention is not to be considered as limited to the disclosed embodiments, but is capable of use in various other combinations, modifications, and environments and is capable of changes within the scope of the inventive concept as expressed herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. But that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the invention, which is to be limited only by the claims appended hereto.
Claims (6)
1. The utility model provides an aircraft wallboard mills detection block subassembly for frock which characterized in that: the device comprises a detection frame and at least one independent detection block;
the shape of the inner edge of the detection frame is matched with the shape of the outer edge of a tire molding assembly of the milling tool of the aircraft wall plate, and the outer edge of the detection frame is of a linear structure;
the independent detection block is matched with the through groove of the tire molding assembly in shape, and detection gaps are respectively arranged between the inner edge of the detection frame and the outer edge of the tire molding assembly and between the independent detection block and the through groove of the tire molding assembly;
the detection frame and the independent detection block are connected with the milling tool of the aircraft panel.
2. The inspection block assembly for an aircraft panel milling fixture of claim 1, wherein: the detection frame is of a split structure.
3. The inspection block assembly for an aircraft panel milling fixture of claim 1, wherein: the detection frame comprises two connection detection blocks which are symmetrically arranged and half frames which are symmetrically arranged at two sides of the two connection detection blocks, each half frame comprises a side edge and two transverse edges, one end of each transverse edge is connected with the connection detection block, and two ends of each side edge are connected with the other end of each transverse edge;
the outer edge of one transverse edge is of an inverted-.
4. The inspection block assembly for an aircraft panel milling fixture of claim 1, wherein: the detection frame and the independent detection block are connected with the milling tool of the aircraft wallboard through bolts.
5. The inspection block assembly for an aircraft panel milling fixture of claim 1, wherein: and the bottoms of the detection frame and the independent detection block are provided with cushion blocks for adjusting the inclination of the detection frame and the inclination of the independent detection block.
6. The inspection block assembly for an aircraft panel milling fixture of claim 3, wherein: and the connection detection block is provided with a reference block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220983346.8U CN217412574U (en) | 2022-04-26 | 2022-04-26 | Detection block assembly for milling tool of aircraft panel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220983346.8U CN217412574U (en) | 2022-04-26 | 2022-04-26 | Detection block assembly for milling tool of aircraft panel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217412574U true CN217412574U (en) | 2022-09-13 |
Family
ID=83184232
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220983346.8U Active CN217412574U (en) | 2022-04-26 | 2022-04-26 | Detection block assembly for milling tool of aircraft panel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217412574U (en) |
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2022
- 2022-04-26 CN CN202220983346.8U patent/CN217412574U/en active Active
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