CN217843074U - Auxiliary force fixing tool for airplane assembly - Google Patents
Auxiliary force fixing tool for airplane assembly Download PDFInfo
- Publication number
- CN217843074U CN217843074U CN202221738914.4U CN202221738914U CN217843074U CN 217843074 U CN217843074 U CN 217843074U CN 202221738914 U CN202221738914 U CN 202221738914U CN 217843074 U CN217843074 U CN 217843074U
- Authority
- CN
- China
- Prior art keywords
- connects
- wall
- joint
- connecting plate
- mounting hole
- 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
- Connection Of Plates (AREA)
Abstract
The utility model relates to a mechanical production makes technical field, and discloses an aircraft equipment is with supplementary power of deciding instrument, connect and connecting plate including anterior joint, rear portion, the connecting plate welding sets up on the lateral wall that connects at front portion, the one end welding of the anterior joint of connecting plate back of the body power sets up on the lateral wall that connects at the rear portion, anterior joint sets up the right side that connects at the rear portion, the dovetail has been seted up to the inside that connects at the front portion, the top welding of anterior joint is provided with expands and takes over, the inside that expands and takes over is provided with the mounting hole, the bottom and the anterior inner wall intercommunication that connects and be located the dovetail of mounting hole set up. The utility model discloses effectively increase the area of contact of joint and part, avoid pressure to concentrate on the condition of a certain point or a certain line, the protection part does not receive the damage at the level force in-process.
Description
Technical Field
The utility model relates to a mechanical production makes technical field, especially relates to an aircraft equipment is with supplementary power of deciding instrument.
Background
When the existing universal constant force tool joint is used for fixing the force of the oxygen pipeline joint, the oxygen pipeline is made of stainless steel and has lower hardness, but the moment value of the fastening oxygen pipeline is larger, so that a more obvious root pressing can be left on the oxygen pipeline, and parts are scrapped.
In the prior art, although the conventional joint has the advantages of convenience in use, size standardization and the like, the contact area between the joint and a part is small, and the situation of damaging the part cannot be avoided. Therefore, the application designs an auxiliary constant force tool for aircraft assembly.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the present joint among the prior art and though having advantages such as convenient, the size standardization of use, nevertheless the area of contact of joint and part is less, the problem that the condition emergence of the part can't be avoided damaging, and the aircraft equipment that provides is with supplementary constant force instrument.
In order to realize the purpose, the utility model adopts the following technical scheme:
the utility model provides an aircraft equipment is with supplementary power of deciding instrument, connects and the connecting plate including anterior joint, rear portion, the connecting plate welding sets up on the lateral wall that connects at front portion, the one end welding that the anterior joint of connecting plate back of the body power set up on the lateral wall that connects at rear portion, the front portion connects the right side that sets up at rear portion, the dovetail has been seted up to the inside that connects at the front portion, the top welding that connects at the front portion is provided with expands the takeover, the inside that expands the takeover is provided with the mounting hole, the bottom and the front portion of mounting hole connect the inner wall intercommunication setting that is located the dovetail.
Preferably, the outer side of the rear joint is in a shape of a round tube, the inner wall of the rear joint is in a shape of a prismatic groove, the prismatic groove is in a shape of a regular hexagon, and an opening is formed in the side wall of the rear joint.
Preferably, the front joint is provided with a rectangular groove on the inner wall of the dovetail groove, and the rectangular groove extends to the inside of the mounting hole.
Preferably, the right side inner wall that expands the takeover and be located the mounting hole is provided with the convex surface, just expand the right side inner wall that the takeover is located two convex surface clearances department and set up to the plane.
Preferably, the rear joint is provided with a chamfer angle at the outer side of the cylinder wall at the bottom end.
Preferably, fillets are respectively formed at the connection positions of the two ends of the connecting plate and the front joint and the connection positions of the two ends of the connecting plate and the rear joint.
Preferably, the inner wall of the barrel wall of the bottom end of the rear joint is provided with a conical surface, and the inclination angle of the conical surface is 14.4 degrees.
Compared with the prior art, the utility model provides an aircraft equipment is with supplementary power of deciding instrument possesses following beneficial effect:
1. this aircraft equipment is with supplementary power tool decides, through the anterior joint with decide the power spanner after correctly installing, with the inside that oxygen pipeline ran into the rear portion through the opening and connect, make rear portion connect and oxygen pipeline joint complete contact under the condition of not touching the pipeline, the power of being convenient for decides.
2. This aircraft equipment is with supplementary power tool that decides, the convex surface that sets up through the inner wall of mounting hole, the gag lever post that makes and mounting hole assorted play the fixed effect of installation to deciding power spanner that can be better, and the conical surface that rear portion joint bottom set up simultaneously can play good direction effect before rear portion connects and oxygen pipeline connects the complete contact.
The part that does not relate to in the device all is the same with prior art or can adopt prior art to realize, the utility model discloses effectively increase the area of contact who connects and the part, avoid pressure to concentrate on the condition of a certain point or a certain line, the protection part is not damaged at the level force in-process.
Drawings
Fig. 1 is a perspective view of an auxiliary force fixing tool for aircraft assembly according to the present invention;
fig. 2 is a structural sectional view of an auxiliary constant force tool for aircraft assembly according to the present invention;
fig. 3 is a top view of the auxiliary force fixing tool for aircraft assembly according to the present invention.
In the figure: the connecting structure comprises a front connector 1, a rear connector 2, a connecting plate 3, a prismatic groove 4, an opening 5, a dovetail groove 6, an expansion connecting pipe 7, a mounting hole 8, a rectangular groove 9, a chamfer angle 10, a fillet 11 and a conical surface 12.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
Example one
Referring to fig. 1-3, an auxiliary force fixing tool for aircraft assembly comprises a front connector 1, a rear connector 2 and a connecting plate 3, wherein the connecting plate 3 is welded on the side wall of the front connector 1, one end of the front connector 1 is welded on the side wall of the rear connector 2 after being stressed by the connecting plate 3, the front connector 1 is arranged on the right side of the rear connector 2, the outer side of the rear connector 2 is in a circular tube shape, the inner wall of the rear connector 2 is a prismatic groove 4, the prismatic groove 4 is in a regular hexagon shape, an opening 5 is arranged on the side wall of the rear connector 2, a dovetail groove 6 is formed in the front connector 1, an expansion pipe 7 is welded at the top end of the front connector 1, a mounting hole 8 is formed in the expansion pipe 7, the bottom of the mounting hole is communicated with the inner wall, located on the dovetail groove 6, of the front connector 1 is provided with a rectangular groove 9, and the rectangular groove 9 extends into the mounting hole 8.
Extend one side of deciding power spanner link to the inside of dovetail 6, plug-in the gag lever post is connected to the inside mounting hole 8 of expansion pipe 7 simultaneously, make the gag lever post extrude each other with the link of deciding power spanner and play certain spacing effect to deciding power spanner, make deciding power spanner install in the inside of anterior joint 1, with anterior joint 1 with decide power spanner after correctly installing, ensure that rear portion connects 2 according to the same direction with oxygen pipeline, with oxygen pipeline through opening 5 in the inside of rear portion joint 2, make rear portion joint 2 and oxygen pipeline connect the complete contact under the condition of not touching the pipeline. After securing the stabilization, the force setting is started. During the process of fixing the force, the joint is ensured to be kept in full contact with the oxygen pipeline joint in real time.
Example two
Referring to fig. 1-3, the right inner wall of the expansion joint pipe 7 located in the mounting hole 8 is provided with a convex surface, the right inner wall of the expansion joint pipe 7 located in the gap between the two convex surfaces is set to be a plane, the outer side of the rear joint 2 located in the bottom end cylinder wall is provided with a chamfer angle 10, the two ends of the connecting plate 3 are respectively provided with a fillet 11 at the connection position of the front joint 1 and the rear joint 2, the inner wall of the rear joint 2 located in the bottom end cylinder wall is provided with a conical surface 12, and the inclination angle of the conical surface 12 is set to be 14.4 °.
Convex surface that the inner wall of mounting hole 8 set up, what make can be better with 8 assorted gag lever posts of mounting hole plays the fixed effect of installation to deciding power spanner, the conical surface 12 that rear portion joint 2 bottoms set up simultaneously can play good guide effect before rear portion connects 2 and oxygen pipeline to connect the complete contact, fillet 11 can guarantee the both ends of connecting plate 3 and the degree of roundness of anterior joint 1 and rear portion joint 2's junction simultaneously, can improve service life, reducing wear.
The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (7)
1. The utility model provides an aircraft assembly is with supplementary dead force instrument, includes that front portion connects (1), rear portion connects (2) and connecting plate (3), its characterized in that: connecting plate (3) welding sets up on the lateral wall that connects at front (1), the one end welding that connecting plate (3) back force front portion connects (1) sets up on the lateral wall that connects (2) at the rear portion, front portion connects (1) and sets up the right side that connects (2) at the rear portion, dovetail (6) have been seted up to the inside that connects (1) at the front portion, the top welding that connects (1) at the front portion is provided with expands and takes over (7), the inside that expands and takes over (7) is provided with mounting hole (8), the bottom and the front portion of mounting hole connect (1) the inner wall intercommunication setting that is located dovetail (6).
2. An auxiliary force fixing tool for aircraft assembly according to claim 1, wherein: the outer side of the rear connector (2) is in a circular tube shape, the inner wall of the rear connector (2) is a prismatic groove (4), the prismatic groove (4) is in a regular hexagon shape, and an opening (5) is formed in the side wall of the rear connector (2).
3. An auxiliary force fixing tool for aircraft assembly according to claim 1, wherein: the inner wall of the front connector (1) positioned on the dovetail groove (6) is provided with a rectangular groove (9), and the rectangular groove (9) extends into the mounting hole (8).
4. An auxiliary force fixing tool for aircraft assembly according to claim 1, wherein: expand the right side inner wall that takes over (7) and be located mounting hole (8) and be provided with the convex surface, just expand the right side inner wall that takes over (7) and be located two convex surface clearances department and set up to the plane.
5. The auxiliary constant force tool for aircraft assembly according to claim 1, wherein the rear joint (2) is provided with a chamfer angle (10) at the outer side of the bottom end cylinder wall.
6. An auxiliary force fixing tool for aircraft assembly according to claim 1, wherein: fillets (11) are respectively formed at the connection positions of the two ends of the connecting plate (3) and the front connector (1) and the rear connector (2).
7. An auxiliary force fixing tool for aircraft assembly according to claim 1, wherein: the inner wall of the rear joint (2) on the cylinder wall at the bottom end is provided with a conical surface (12), and the inclination angle of the conical surface (12) is 14.4 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221738914.4U CN217843074U (en) | 2022-07-06 | 2022-07-06 | Auxiliary force fixing tool for airplane assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221738914.4U CN217843074U (en) | 2022-07-06 | 2022-07-06 | Auxiliary force fixing tool for airplane assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217843074U true CN217843074U (en) | 2022-11-18 |
Family
ID=84035897
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221738914.4U Active CN217843074U (en) | 2022-07-06 | 2022-07-06 | Auxiliary force fixing tool for airplane assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217843074U (en) |
-
2022
- 2022-07-06 CN CN202221738914.4U patent/CN217843074U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4103937A (en) | Self-aligning permanent fitting | |
| CN217843074U (en) | Auxiliary force fixing tool for airplane assembly | |
| CN206123489U (en) | Spheroid work piece negative pressure absorption clamping utensil | |
| CN215444666U (en) | Square pipe connecting structure | |
| CN213288231U (en) | Pipeline roundness adjusting device | |
| CN215658631U (en) | Assembled C type robot soldering turret quiet arm structure | |
| CN219565386U (en) | Bolt connection structure between ship bodies | |
| CN217046289U (en) | Spring seat pressing connector convenient for assembling engine valve spring | |
| CN221144590U (en) | Oil return pipe of turbocharger | |
| CN213598373U (en) | Connecting rod bolt | |
| CN220348451U (en) | Fixing device for wet spraying manipulator material tube seat | |
| CN212599457U (en) | Multipoint blanking cutter | |
| CN219599354U (en) | Novel jig for air duct | |
| CN214822461U (en) | Argon-free welding condenser bracket | |
| CN213236520U (en) | Elbow structure convenient to install fast | |
| CN212012060U (en) | Prevent insulator protection architecture that drops | |
| CN213108406U (en) | Improved pressing plate of sugar cube machine | |
| CN220866333U (en) | Middle groove connecting device | |
| CN209991002U (en) | Oblique connecting pressing plate | |
| CN216554735U (en) | Cylinder fixing plate | |
| CN215846240U (en) | Whole rifle connection structure of welder for air-cooled machine | |
| CN210232056U (en) | Curved plate alignment adjusting device | |
| CN216641040U (en) | External corner connecting structure of shear wall | |
| CN212478819U (en) | Lock body linking structure | |
| CN216742311U (en) | Furniture fastener |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |