CN217617945U - Drilling and reaming fixture for titanium alloy framework-shaped part of airplane - Google Patents
Drilling and reaming fixture for titanium alloy framework-shaped part of airplane Download PDFInfo
- Publication number
- CN217617945U CN217617945U CN202221194914.2U CN202221194914U CN217617945U CN 217617945 U CN217617945 U CN 217617945U CN 202221194914 U CN202221194914 U CN 202221194914U CN 217617945 U CN217617945 U CN 217617945U
- Authority
- CN
- China
- Prior art keywords
- drilling
- titanium alloy
- bottom plate
- plate
- top end
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Drilling And Boring (AREA)
Abstract
The utility model discloses a fixture which solves the problem that the position precision of a hole can not be basically ensured when a sample plate or a common drill jig is used for processing, the operation is convenient, and the precision of the hole manufactured by the fixture is high; the technical scheme is as follows: a drilling and reaming hole clamp for an aircraft titanium alloy skeleton-shaped part comprises: drilling a template; a bottom plate: the drill jig is characterized in that two quick-change drill bushings are arranged on the top end face of the drill jig plate, a bolt is inserted into the quick-change drill bushings, long rod bolts are arranged at the positions, close to the left end and the right end, of the top end face of the bottom plate, the top ends of the long rod bolts penetrate through the drill jig plate and then are fixed through double-lug spanner nuts, and a tire body is fixed in the middle of the top end face of the bottom plate. The utility model discloses a drilling and reaming hole anchor clamps structural design of titanium alloy skeleton shape part is reasonable, can target in place the part clamping through the cooperation of bushing plate and matrix, and this anchor clamps convenient operation adopts the hole precision height that this anchor clamps were made, satisfies the assembly operation requirement.
Description
Technical Field
The utility model relates to an aircraft titanium alloy skeleton shape part bore reaming anchor clamps.
Background
At present, the structural application of the framework-shaped titanium alloy sheet metal part of the airplane in the structure of the airplane is very wide, the framework-shaped titanium alloy sheet metal part is made of a titanium alloy material (Ti-6 AL-4V), two holes need to be machined in the framework-shaped titanium alloy sheet metal part, the position precision requirement of the holes is high, the position precision of the holes in the general sheet metal part is phi 1, but the hole position precision of the framework-shaped titanium alloy sheet metal part is phi 0.2. The position precision of the hole can not be basically guaranteed when a sample plate or a common drilling jig is used for machining, the assembly requirement can not be met, the part is scrapped, and the production cost is increased.
SUMMERY OF THE UTILITY MODEL
The utility model overcomes prior art exists not enough, provides a drilling and reaming anchor clamps of aircraft titanium alloy skeleton shape part, has solved and has added the problem that the position accuracy in hole can't guarantee basically with template or general jig, and convenient operation adopts the hole precision height that this anchor clamps were made.
In order to solve the technical problem, the utility model discloses a technical scheme be: the utility model provides an aircraft titanium alloy skeleton shape part bore reaming anchor clamps, includes:
drilling a template;
the bottom plate is arranged below the drilling template:
the method is characterized in that: the drill jig comprises a drill jig plate, a base plate, a drill jig plate, a double-lug spanner nut, a drill jig plate and a bolt, wherein two quick-change drill sleeves are arranged on the top end face of the drill jig plate, the bolt is inserted into the quick-change drill sleeves, long rod bolts are arranged at the positions, close to the left end and the right end, of the top end face of the base plate, the top ends of the long rod bolts penetrate through the drill jig plate and then are fixed through the double-lug spanner nut, and a tire body is fixed in the middle of the top end face of the base plate.
In the structure, one side of the quick-change drill bushing is provided with a drill bushing fixing screw for fixing the quick-change drill bushing.
In the structure, the tire body and the bottom plate are fixed through a plurality of fastening screws.
In the structure, a plurality of cylindrical pins inserted in the bottom plate are arranged in the tire body.
In the structure, a material blocking pin is arranged at the position, close to the right end, of the top end face of the tire body.
Compared with the prior art, the beneficial effects of the utility model are that: the utility model discloses a drilling and reaming hole anchor clamps structural design of titanium alloy skeleton shape part is reasonable, can target in place the part clamping through the cooperation of bushing plate and matrix, and this anchor clamps convenient operation adopts the hole precision height that this anchor clamps were made, satisfies the assembly operation requirement.
Drawings
Fig. 1 is a schematic structural diagram of a hole drilling and reaming fixture for an aircraft titanium alloy skeleton-shaped part according to an embodiment of the present invention;
fig. 2 is a second schematic structural view of a hole drilling and reaming fixture for an aircraft titanium alloy skeleton-shaped part according to an embodiment of the present invention;
FIG. 3 is a schematic view of a connection structure between a bottom plate and a carcass in a hole drilling and reaming fixture for an aircraft titanium alloy skeleton-shaped part according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a bottom plate in the drilling and reaming hole fixture for the titanium alloy skeleton-shaped part of the aircraft according to the embodiment of the present invention.
In the figure:
1. drilling a template; 2. a base plate; 3. quickly replacing the drill bushing; 4. a bolt; 5. a long rod bolt; 6. a double lug spanner nut; 7. a carcass; 8. a drill bushing fixing screw; 9. a fastening screw; 10. a cylindrical pin; 11. a material blocking pin; 12. and (4) parts.
Detailed Description
The following detailed description of the embodiments of the present invention is provided with reference to the accompanying drawings and examples. The following examples are intended to illustrate the invention, but are not intended to limit the scope of the invention.
As shown in fig. 1, a drilling and reaming fixture for an airplane titanium alloy skeleton-shaped part comprises:
drilling a template 1;
the bottom plate 2 is arranged below the drilling template 1:
the method is characterized in that: the drill jig comprises a drill jig plate 1 and is characterized in that two quick-change drill bushings 3 are arranged on the top end face of the drill jig plate 1, bolts 4 are inserted into the quick-change drill bushings 3, long rod bolts 5 are arranged at the positions, close to the left end and the right end, of the top end face of a bottom plate 2, the top ends of the long rod bolts 5 penetrate through the drill jig plate 1 and then are fixed through double-lug spanner nuts 6, and a tire body 7 is fixed in the middle of the top end face of the bottom plate 2.
In the structure, one side of the quick-change drill bushing 3 is provided with a drill bushing fixing screw 8 for fixing the quick-change drill bushing 3.
In the above structure, the carcass 7 and the bottom plate 2 are fixed by a plurality of fastening screws 9.
In the structure, a plurality of cylindrical pins 10 inserted in the bottom plate 2 are arranged in the tire body 7.
In the structure, a material blocking pin 11 is arranged at the position, close to the right end, of the top end face of the tire body 7, and the material blocking pin 11 plays a role in positioning a part 12.
The utility model discloses a drilling and reaming anchor clamps of titanium alloy skeleton shape part when specifically using, will connect good matrix 7 and bottom plate 2 and put on work platform, will go the part 12 of surplus and put on matrix 7 through the fixed positioning action that keeps off material round pin 11, install bushing plate 1 on stock bolt 5 after to it is fixed through ears spanner nut 6, then assemble quick change bushing 3 on bushing plate 1 through the butt joint effect of bolt 4 and the fastening effect of bushing set screw 8. The part 12 is assembled on the reaming jig and the desired hole is made. The drilling and reaming fixture has the advantages that the fixture is made of 45# steel, the cost is low, the fixture is convenient to operate when used for drilling holes, the precision of the drilled holes is high, and the assembly and use requirements are met.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (5)
1. The utility model provides an aircraft titanium alloy skeleton shape part bore reaming anchor clamps, includes:
a drilling template (1);
the bottom plate (2) is arranged below the drilling template (1):
the method is characterized in that: the drill jig is characterized in that two quick-change drill bushings (3) are arranged on the top end face of the drill jig plate (1), a bolt (4) is inserted into the quick-change drill bushings (3), long rod bolts (5) are arranged at the positions, close to the left end and the right end, of the top end face of the bottom plate (2), the top ends of the long rod bolts (5) penetrate through the drill jig plate (1) and then are fixed through double-lug spanner nuts (6), and a tire body (7) is fixed in the middle of the top end face of the bottom plate (2).
2. The drilling and reaming fixture for the titanium alloy skeleton-shaped part of the aircraft as claimed in claim 1, characterized in that: and drill bushing fixing screws (8) used for fixing the quick-change drill bushing (3) are arranged on one side of the quick-change drill bushing (3).
3. The drilling and reaming fixture for the titanium alloy skeleton-shaped part of the aircraft as claimed in claim 1, characterized in that: the tyre body (7) and the bottom plate (2) are fixed through a plurality of fastening screws (9).
4. The drilling and reaming fixture for the titanium alloy skeleton-shaped part of the aircraft as claimed in claim 1, characterized in that: a plurality of cylindrical pins (10) inserted into the bottom plate (2) are arranged in the tire body (7).
5. The drilling and reaming fixture for the titanium alloy skeleton-shaped part of the aircraft as claimed in claim 1, characterized in that: and a material blocking pin (11) is arranged at the position, close to the right end, of the top end surface of the tire body (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221194914.2U CN217617945U (en) | 2022-05-19 | 2022-05-19 | Drilling and reaming fixture for titanium alloy framework-shaped part of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221194914.2U CN217617945U (en) | 2022-05-19 | 2022-05-19 | Drilling and reaming fixture for titanium alloy framework-shaped part of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217617945U true CN217617945U (en) | 2022-10-21 |
Family
ID=83653754
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221194914.2U Active CN217617945U (en) | 2022-05-19 | 2022-05-19 | Drilling and reaming fixture for titanium alloy framework-shaped part of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217617945U (en) |
-
2022
- 2022-05-19 CN CN202221194914.2U patent/CN217617945U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109926617B (en) | Clamp for simultaneously drilling upper holes and lower holes on spring lifting lug parts | |
| CN210909097U (en) | Special drilling clamp for L-shaped parts | |
| CN103612138B (en) | The fixture flexible positioning method of connecting rod cap, bearing cap class part processing and device | |
| CN206967089U (en) | A kind of drill jig | |
| CN205111380U (en) | Connecting rod bolt hole anchor clamps that drill and ream | |
| CN217617945U (en) | Drilling and reaming fixture for titanium alloy framework-shaped part of airplane | |
| CN112247618B (en) | Special fixture and method for machining end face of tenon root of blade of aero-engine | |
| CN206795344U (en) | A kind of turning attachment for being used to process square cross | |
| CN101176926A (en) | Magnetizer drilling jig gripper for electro-hydraulic servo valve | |
| CN215880765U (en) | Special frock of large-scale titanium alloy structure spare | |
| CN213195772U (en) | Fixing device for shaft end drilling | |
| CN201792013U (en) | Spring hole machining tool for automobile front axle plate | |
| CN220920951U (en) | Hydraulic chuck split claw for ring bearing turning | |
| CN210789364U (en) | Processing assembly suitable for crane beam structure and connecting plate mounting hole | |
| CN207915661U (en) | A kind of hydraulic support guide rod drilling universal fixture | |
| CN209319311U (en) | Frock clamp suitable for Four-axis milling | |
| CN209754641U (en) | special fixture for drilling high-precision spherical hole on swinging arm piece | |
| CN220330056U (en) | Clamp for drilling flat flange plate | |
| CN205200604U (en) | Guarantee a plurality of continuous union pieces in different apertures of hole concentricity | |
| CN112823984A (en) | Fixture for drilling L-shaped part and using method | |
| CN219074477U (en) | Clamp for milling screw holes and peripheral molded surfaces of supporting piece | |
| CN220259633U (en) | Valve core overturning type drill jig | |
| CN113752062B (en) | Automobile-used frock of complicated weldment | |
| CN213857220U (en) | Adjustable drill jig for drilling cabin body assembling holes | |
| CN220278359U (en) | Adjustable arm flange drilling frock |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |