CN212495543U - Helicopter alloy steel truss reference end face machining equipment - Google Patents
Helicopter alloy steel truss reference end face machining equipment Download PDFInfo
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- CN212495543U CN212495543U CN202021257708.2U CN202021257708U CN212495543U CN 212495543 U CN212495543 U CN 212495543U CN 202021257708 U CN202021257708 U CN 202021257708U CN 212495543 U CN212495543 U CN 212495543U
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- helicopter
- alloy steel
- steel truss
- telescopic
- face machining
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Abstract
The utility model discloses a helicopter alloy steel truss benchmark terminal surface processing equipment belongs to helicopter alloy steel truss processing technology field, and helicopter alloy steel truss benchmark terminal surface processing equipment includes: a base; the fixing mechanism is arranged on the base and is configured to fix the helicopter alloy steel truss; the supporting part is arranged on the base; a rotation adjusting part rotatably provided on the support part; the telescopic part is arranged on the rotation adjusting part and is provided with a telescopic execution end; the reference end face processing part is arranged on the telescopic execution end and is configured to trim the joint of the helicopter alloy steel truss; wherein, the rotation regulation part is configured to adjust the relative position between the telescopic execution end and the helicopter alloy steel truss. The utility model discloses a helicopter alloy steel truss benchmark terminal surface processing equipment, the distance between each joint of adjustable benchmark terminal surface processing portion and helicopter alloy steel truss.
Description
Technical Field
The utility model relates to a helicopter alloy steel truss processing technology field especially relates to a helicopter alloy steel truss benchmark terminal surface processing equipment.
Background
The helicopter alloy steel truss is usually processed by adopting a welding process, and a formed welding joint always has a machining allowance of 1.5-3mm at the welding position of the truss so as to avoid unqualified quality of the helicopter alloy steel truss caused by welding errors. And the formed welding joint needs to be trimmed after the welding of the steel truss is finished until the end face of the welding joint reaches the standard.
The helicopter alloy steel truss reference end face machining equipment is a machining device for trimming a welding joint, and generally comprises a clamping device for clamping a steel truss and a trimming device arranged on one side of the clamping device and used for trimming the joint of the steel truss, wherein a trimming cutter is arranged at an execution end of the trimming device.
However, in the existing helicopter alloy steel truss reference end face machining equipment, the execution end of the trimming device is usually relatively fixed, the relative position between the execution end and the steel truss cannot be adjusted, different joints on the steel truss are difficult to trim, the steel truss needs to be loosened ceaselessly and then clamped again after the position is adjusted, and the trimming error is large.
SUMMERY OF THE UTILITY MODEL
A primary object of the utility model is to provide a helicopter alloy steel truss benchmark terminal surface processing equipment to solve among the prior art repair cut the execution end of device can't adjust and steel truss between the relative position and can't connect the technical problem who repairs and cut to steel truss is last different.
In order to achieve the above object, an embodiment of the present application provides a helicopter alloy steel truss reference end face machining apparatus, including: a base; the fixing mechanism is arranged on the base and is configured to fix the helicopter alloy steel truss; a support part disposed on the base; a rotation adjusting part rotatably provided on the supporting part; the telescopic part is arranged on the rotation adjusting part and is provided with a telescopic execution end; the reference end face processing part is arranged on the telescopic execution end and is configured to trim a joint of the helicopter alloy steel truss; wherein, the rotation adjustment part is configured to adjust the relative position between the telescopic execution end and the helicopter alloy steel truss.
In one embodiment, the rotation adjusting portion includes: a support shaft fixed to the support portion; the inner ring of the rotary bearing is sleeved on the supporting shaft; the rotary platform is provided with an installation cavity, and the installation cavity is sleeved on an outer ring of the rotary bearing; wherein, the pars contractilis set up on rotary platform.
In one embodiment, the rotation adjusting portion further includes: the elastic bolt penetrates through the rotating platform and is in threaded fit with the rotating platform; the maximum outer diameter of the rotating platform is smaller than the width of the supporting part, so that the elastic bolt is tightly abutted to the supporting part to fix the rotating platform.
In one embodiment, the loose bolts are provided with at least two loose bolts, and the at least two loose bolts are uniformly distributed on the rotating platform.
In one embodiment, the bellows comprises: the fixed sleeve is arranged on the rotary adjusting part and is provided with an installation cavity; the telescopic rod penetrates through the mounting cavity and extends to one side close to the fixing mechanism; the telescopic execution end is arranged on the telescopic rod and extends to be close to the fixing mechanism.
In one embodiment, the telescopic rod comprises: the fixed main rod penetrates through the installation cavity and is provided with a telescopic cavity, and the telescopic cavity is arranged along the length direction of the fixed main rod; the telescopic auxiliary rod is in sliding fit in the telescopic cavity, and one end of the telescopic auxiliary rod extends to the outside of the telescopic cavity to form the telescopic execution end; the fixing screw penetrates through the fixing main rod and is in threaded fit with the fixing main rod, and one end of the fixing screw extends into the telescopic cavity; the fixing screw abuts against the telescopic auxiliary rod to fix the telescopic auxiliary rod on the fixing main rod.
In one embodiment, the fixing screws are provided with at least two fixing screws, and the at least two fixing screws are uniformly distributed along the circumferential direction of the fixing main rod.
In one embodiment, the reference end-face processing portion includes: the drill jig is arranged on the telescopic execution end; and the countersink is arranged on the drill jig and is configured to trim the joint of the helicopter alloy steel truss.
In one embodiment, the securing mechanism comprises: the fixed table is arranged on the base; and the clamping part is arranged on the fixed table and is configured to clamp the helicopter alloy steel truss.
In one embodiment, the rotation plane of the rotation regulating part is parallel to the extension line of the length direction of the supporting part.
Compared with the prior art, the beneficial effects of the utility model are that:
the utility model provides a helicopter alloy steel truss benchmark terminal surface processing equipment, through setting up the base, fixed establishment, the supporting part, rotation regulation portion, pars contractilis and benchmark terminal surface processing portion, helicopter alloy steel truss clamping is after on fixed establishment, rotation regulation portion can drive the pars contractilis rotatory, relative position between flexible execution end and the helicopter alloy steel truss of regulation pars contractilis, simultaneously through the flexible distance between each joint with accurate regulation benchmark terminal surface processing portion and helicopter alloy steel truss of pars contractilis, thereby realized that a clamping of helicopter alloy steel truss can repair and cut its a plurality of joints. Meanwhile, due to the matched arrangement of the rotary adjusting part and the telescopic part, the welding joint trimming device can be suitable for trimming the welding joints of helicopter alloy steel trusses with different specifications and sizes.
Drawings
The accompanying drawings, which form a part of the present application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
In the drawings:
fig. 1 is a schematic structural diagram of a helicopter alloy steel truss reference end surface processing device provided in an embodiment of the present invention;
fig. 2 is a second schematic structural diagram of a helicopter alloy steel truss reference end surface processing device provided in the specific embodiment of the present invention;
fig. 3 is a schematic side view of a rotation adjusting portion according to an embodiment of the present invention;
fig. 4 is a schematic structural view of a telescopic rod provided in the embodiment of the present invention;
fig. 5 is a schematic structural view of a countersink according to an embodiment of the present invention.
In the figure:
100. machining equipment for a reference end face of the alloy steel truss of the helicopter; 10. a base; 20. a fixing mechanism; 200. helicopter alloy steel trusses; 30. a support portion; 40. a rotation adjusting part; 50. a telescopic part; 60. a reference end face machining part; 41. a support shaft; 42. a rotating bearing; 43. rotating the platform; 44. tightening and loosening the bolts; 51. fixing a sleeve; 52. a telescopic rod; 521. fixing the main rod; 522. a telescopic auxiliary rod; 523. a set screw; 61. drilling a mold; 62. countersinking; 21. a fixed table; 22. and a clamping part.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
It is noted that, unless otherwise indicated, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.
In the present invention, unless otherwise specified, the use of directional words such as "upper and lower" is generally in reference to the orientation shown in the drawings, or to the vertical, perpendicular or gravitational orientation; likewise, for ease of understanding and description, "left and right" are generally to the left and right as shown in the drawings; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself, but the above directional terms are not intended to limit the present invention.
In addition, descriptions in the present application as to "first", "second", and the like are for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In order to solve the technical problem that the execution end of a trimming and cutting device in the prior art cannot adjust the relative position between the execution end and a steel truss and cannot trim and cut different connectors on the steel truss, the application provides a helicopter alloy steel truss reference end face machining device.
The present invention will be further explained with reference to the accompanying drawings.
As shown in fig. 1 to 5, the present embodiment provides a helicopter alloy steel truss reference end face machining apparatus, and the helicopter alloy steel truss reference end face machining apparatus 100 includes a base 10, a fixing mechanism 20, a support portion 30, a rotation adjusting portion 40, a telescopic portion 50, and a reference end face machining portion 60.
The base 10 functions to support the fixing mechanism 20 and the supporting portion 30.
A securing mechanism 20 is disposed on the base 10, the securing mechanism 20 being configured to secure the helicopter alloy steel truss 200.
The supporting portion 30 is disposed on the base 10 and located at one side of the fixing mechanism 20.
The rotation regulating portion 40 is rotatably provided on the support portion 30. The rotation plane of the rotation adjusting part 40 is parallel to the extension line of the support part 30 in the longitudinal direction.
The expansion part 50 is disposed on the rotation adjusting part 40, and the expansion part 50 has an expansion actuating end.
The reference end face machining portion 60 is provided on the telescopic execution end, and the reference end face machining portion 60 is configured to trim the joint of the helicopter alloy steel truss 200.
Wherein the rotation adjustment portion 40 is configured to adjust the relative position between the telescopic actuation end and the helicopter alloy steel truss 200.
After the helicopter alloy steel truss is clamped on the fixing mechanism 20, the rotation adjusting part 40 can drive the telescopic part 50 to rotate so as to adjust the relative position between the telescopic execution end of the telescopic part 50 and the helicopter alloy steel truss 200, and simultaneously, the distance between the reference end face processing part 60 and each joint of the helicopter alloy steel truss 200 can be accurately adjusted through the telescopic action of the telescopic part 50, so that the plurality of joints of the helicopter alloy steel truss can be trimmed by one-time clamping. Meanwhile, due to the matched arrangement of the rotary adjusting part 40 and the telescopic part 50, the welding joint trimming device can be suitable for trimming the welding joints of helicopter alloy steel trusses with different specifications and sizes.
In the present embodiment, the rotation adjusting portion 40 includes a support shaft 41, a rotation bearing 42, and a rotation platform 43.
The support shaft 41 is fixed to the support portion 30. The inner race of the rotary bearing 42 is fitted over the support shaft 41. The rotary platform 43 has a mounting cavity, and the rotary platform 43 is sleeved on the outer ring of the rotary bearing 42 through the mounting cavity. The telescopic portion 50 is provided on the rotary platform 43.
With the above arrangement, the rotary platform 43 can rotate relative to the support shaft 41, thereby rotating the telescopic part 50 located thereon.
In this embodiment, the rotation adjusting portion 40 further includes a tension bolt 44 penetrating the rotating platform 43 and threadedly engaged with the rotating platform 43. The maximum outer diameter of the rotary platform 43 is smaller than the width of the support 30, so that the turnbuckle 44 is tightly pressed against the support 30 to fix the rotary platform 43.
With the arrangement, after the elastic bolt 44 is loosened, the rotating platform 43 can rotate freely, and after the telescopic part 50 is adjusted to a required position by rotation, the elastic bolt 44 is screwed to fix the position, so that the adjustment is facilitated.
In this embodiment, at least two of the loose bolts 44 are arranged, and the at least two loose bolts 44 are uniformly distributed on the rotating platform 43. The stability of the rotary platform 43 after rotating to a given position can be improved.
In this embodiment, the telescopic portion 50 includes a fixing sleeve 51 and a telescopic rod 52.
The fixing sleeve 51 is disposed on the rotating platform 43 of the rotating adjustment part 40, and the fixing sleeve 51 has a mounting cavity. The telescoping rod 52 extends through the mounting cavity and toward a side adjacent to the securing mechanism 20. Wherein, the telescopic actuating end is disposed on the telescopic rod 52 and extends to be close to the fixing mechanism 20. The telescopic rod 52 is connected to the rotary platform 43 by means of a fixed sleeve 51. The telescoping rod 52 may be fixed in the harness 51 or may rotate relative to the harness 51.
In this embodiment, the telescopic rod 52 includes a fixed main rod 521, a telescopic auxiliary rod 522, and a fixing screw 523.
The fixed main rod 521 is arranged in the installation cavity in a penetrating manner, the fixed main rod 521 is provided with a telescopic cavity, and the telescopic cavity is arranged along the length direction of the fixed main rod 521.
The telescoping sub-rod 522 is slidably fitted in the telescoping cavity, with one end of the telescoping sub-rod 522 extending outside the telescoping cavity to form a telescoping actuation end.
The fixing screw 523 penetrates through the fixing main rod 521 and is in threaded fit with the fixing main rod 521, and one end of the fixing screw 523 extends into the telescopic cavity; the fixing screw 523 tightly presses the auxiliary telescopic rod 522 to fix the auxiliary telescopic rod 522 to the main fixed rod 521.
With the above arrangement, after the fixing screw 523 is unscrewed, the telescopic auxiliary rod 522 can slide in the telescopic cavity to lengthen or shorten the overall length of the telescopic rod 52, and after the length is adjusted to the required length, the fixing screw 523 is screwed to realize fixing.
In this embodiment, at least two fixing screws 523 are provided, and the at least two fixing screws 523 are uniformly distributed along the circumferential direction of the main fixing rod 521
In the present embodiment, the reference end surface processing portion 60 includes a jig 61 and a countersink 62.
The jig 61 is provided on the telescopic execution end. The countersink 62 is provided on the jig 61 and configured to trim the joint of the helicopter alloy steel truss 200. The joint of the helicopter alloy steel truss 200 is trimmed by the countersink blade of the countersink 62. A transmission mechanism for driving the countersink 62 to rotate may be provided on the telescopic auxiliary rod 522, and the joint of the helicopter alloy steel truss 200 may be trimmed by the rotation of the countersink 62. Or a transmission mechanism may be arranged at one end of the fixed main rod 521, which is far away from the fixing mechanism, and the transmission mechanism drives the fixed main rod 521 to rotate so as to trim the joint of the helicopter alloy steel truss 200. The countersink 62 may employ a flat bottom cutting edge. The countersink 62 and the transmission mechanism can be the countersink and the transmission mechanism in the prior art, and are not described in detail here.
In this embodiment, the fixing mechanism 20 includes a fixing table 21 and a chuck 22.
The fixed table 21 is provided on the base 10, and supports the clamping portion 22 and the helicopter alloy steel truss 200.
The clamping part 22 is arranged on the fixed table 21 and configured to clamp the helicopter alloy steel truss 200. The clamping portion 22 may include a fixing plate fixed to the top end of the fixing table 21 and a clamping plate detachably provided on the fixing plate, and the helicopter alloy steel truss 200 may be clamped between the fixing plate and the clamping plate.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that are not thought of through the creative work should be covered within the scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope defined by the claims.
Claims (10)
1. The utility model provides a helicopter alloy steel truss benchmark terminal surface processing equipment which characterized in that, helicopter alloy steel truss benchmark terminal surface processing equipment includes:
a base;
the fixing mechanism is arranged on the base and is configured to fix the helicopter alloy steel truss;
a support part disposed on the base;
a rotation adjusting part rotatably provided on the supporting part;
the telescopic part is arranged on the rotation adjusting part and is provided with a telescopic execution end; and
the reference end face machining part is arranged on the telescopic execution end and is configured to trim a joint of the helicopter alloy steel truss;
wherein, the rotation adjustment part is configured to adjust the relative position between the telescopic execution end and the helicopter alloy steel truss.
2. The helicopter alloy steel truss datum face machining apparatus of claim 1, wherein the rotation adjustment portion comprises:
a support shaft fixed to the support portion;
the inner ring of the rotary bearing is sleeved on the supporting shaft;
the rotary platform is provided with an installation cavity, and the installation cavity is sleeved on an outer ring of the rotary bearing;
wherein, the pars contractilis set up on rotary platform.
3. The helicopter alloy steel truss datum face machining apparatus of claim 2, wherein the rotation adjustment portion further comprises:
the elastic bolt penetrates through the rotating platform and is in threaded fit with the rotating platform;
the maximum outer diameter of the rotating platform is smaller than the width of the supporting part, so that the elastic bolt is tightly abutted to the supporting part to fix the rotating platform.
4. The helicopter alloy steel truss datum face machining device of claim 3, wherein:
the elastic bolts are arranged in at least two numbers, and the elastic bolts are uniformly distributed on the rotating platform.
5. The helicopter alloy steel truss datum face machining apparatus of claim 1, wherein the telescoping section comprises:
the fixed sleeve is arranged on the rotary adjusting part and is provided with an installation cavity;
the telescopic rod penetrates through the mounting cavity and extends to one side close to the fixing mechanism;
the telescopic execution end is arranged on the telescopic rod and extends to be close to the fixing mechanism.
6. The helicopter alloy steel truss datum face machining apparatus of claim 5, wherein the telescoping rod comprises:
the fixed main rod penetrates through the installation cavity and is provided with a telescopic cavity, and the telescopic cavity is arranged along the length direction of the fixed main rod;
the telescopic auxiliary rod is in sliding fit in the telescopic cavity, and one end of the telescopic auxiliary rod extends to the outside of the telescopic cavity to form the telescopic execution end;
the fixing screw penetrates through the fixing main rod and is in threaded fit with the fixing main rod, and one end of the fixing screw extends into the telescopic cavity;
the fixing screw abuts against the telescopic auxiliary rod to fix the telescopic auxiliary rod on the fixing main rod.
7. The helicopter alloy steel truss datum face machining device of claim 6, wherein:
the fixing screws are provided with at least two, and the at least two fixing screws are uniformly distributed along the circumferential direction of the fixing main rod.
8. The helicopter alloy steel truss datum face machining apparatus of claim 1, wherein the datum face machining section comprises:
the drill jig is arranged on the telescopic execution end;
and the countersink is arranged on the drill jig and is configured to trim the joint of the helicopter alloy steel truss.
9. The helicopter alloy steel truss datum face machining apparatus of claim 1, wherein the securing mechanism comprises:
the fixed table is arranged on the base;
and the clamping part is arranged on the fixed table and is configured to clamp the helicopter alloy steel truss.
10. The helicopter alloy steel truss datum face machining apparatus of any one of claims 1-9, wherein:
the rotating plane of the rotating adjusting part is parallel to the extension line of the supporting part in the length direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021257708.2U CN212495543U (en) | 2020-06-30 | 2020-06-30 | Helicopter alloy steel truss reference end face machining equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021257708.2U CN212495543U (en) | 2020-06-30 | 2020-06-30 | Helicopter alloy steel truss reference end face machining equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212495543U true CN212495543U (en) | 2021-02-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021257708.2U Active CN212495543U (en) | 2020-06-30 | 2020-06-30 | Helicopter alloy steel truss reference end face machining equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212495543U (en) |
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2020
- 2020-06-30 CN CN202021257708.2U patent/CN212495543U/en active Active
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