CN214920842U - Aircraft nose case stable structure based on numerically controlled fraise machine - Google Patents
Aircraft nose case stable structure based on numerically controlled fraise machine Download PDFInfo
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- CN214920842U CN214920842U CN202022964591.8U CN202022964591U CN214920842U CN 214920842 U CN214920842 U CN 214920842U CN 202022964591 U CN202022964591 U CN 202022964591U CN 214920842 U CN214920842 U CN 214920842U
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- China
- Prior art keywords
- head box
- machine head
- aircraft nose
- nose case
- casting
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- 238000003801 milling Methods 0.000 claims abstract description 21
- 238000005266 casting Methods 0.000 claims abstract description 19
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 10
- 230000000087 stabilizing effect Effects 0.000 claims description 5
- 230000002787 reinforcement Effects 0.000 claims description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 2
- 230000001174 ascending effect Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model discloses a stable structure of a machine head box based on a numerical control milling machine, which comprises a machine head box, wherein a casting tripod support and a reinforcing inclined block are arranged below the machine head box, a milling machine frame is arranged on one side of the machine head box, a slide block is arranged between the machine head box and the milling machine frame, the casting tripod support and the machine head box are connected in an integral casting mode, the top surface of the reinforcing inclined block and the top surface of the upper end of an upper tripod reinforcing support are positioned on the same horizontal line, the reinforcing inclined block and the machine head box are connected in an integral casting mode, the utility model improves the stability of the machine head box by arranging the reinforcing inclined block and the casting tripod support, increases the arrangement of the casting tripod support, increases the integral stress surface of the machine head box, increases the moment in the vertical direction of the machine head box, and improves the support capability of the machine head box in the vertical direction, the supporting capability of the machine head box in the inclined plane direction is improved due to the arrangement of the reinforcing inclined block, so that the stability of the machine head box is higher.
Description
Technical Field
The utility model relates to a milling machine aircraft nose case technical field specifically is a aircraft nose case stable structure based on numerically controlled fraise machine.
Background
The milling machine is a machine tool with wide application, and can process planes (horizontal planes and vertical planes), grooves (key grooves, T-shaped grooves, dovetail grooves and the like), tooth dividing parts (gears, spline shafts and chain wheels), spiral surfaces (threads and spiral grooves) and various curved surfaces on the milling machine. In addition, the method can be used for machining the surface and inner hole of the revolving body, cutting off the revolving body, and the like.
The stability of a traditional milling machine head box is not enough, so that the situation that the machine head box shakes in subsequent milling machine operation is caused.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a aircraft nose case stable structure based on numerically controlled fraise machine to solve the problem that proposes among the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
the utility model provides a aircraft nose case stable structure based on numerically controlled fraise machine, includes the aircraft nose case, the below of aircraft nose case is equipped with the tripod of foundry goods and supports and consolidate the sloping block, one side of aircraft nose case is equipped with the milling machine frame, be equipped with the slider between aircraft nose case and the milling machine frame.
Preferably, the tripod of foundry goods supports and is connected through the integral casting mode between the aircraft nose case, the top surface of consolidating the sloping block and the tripod of foundry goods supports upper end top surface and is in same horizontal line, consolidate and be connected through the integral casting mode between sloping block and the aircraft nose case.
Preferably, the outer surfaces of two sides of the tripod support of the casting are provided with a plurality of groups of fixing bolts for fixing the headstock.
Preferably, the reinforcing inclined block and the tripod support of the casting form an integral workpiece, and the integral workpiece is formed by pouring through a specific mould.
Compared with the prior art, the beneficial effects of the utility model are that: the utility model discloses a consolidate sloping block and whole cast setting, let aircraft nose case stability improve, the setting that the tripod of foundry goods supported has increased the stress surface of aircraft nose case, has increased the vertical ascending moment in side of aircraft nose case, has improved the vertical ascending support ability in side of aircraft nose case, consolidates the setting of sloping block simultaneously, has promoted the ascending support ability in inclined plane side of aircraft nose case for aircraft nose case stability is higher.
Drawings
Fig. 1 is a side view of the head box stabilizing structure based on the numerically controlled milling machine of the present invention;
fig. 2 is a front view of the head box stabilizing structure based on the numerically controlled milling machine of the present invention;
fig. 3 is the utility model relates to a three-legged bearing structure sketch map of sloping block and foundry goods is consolidated to aircraft nose case stable structure based on numerically controlled fraise machine.
In the figure: 1. a head box; 2. a milling machine frame; 3. reinforcing the inclined block; 4. tripod support of the casting; 5. a slide block.
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. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-3, the present invention provides a technical solution: the utility model provides a aircraft nose case stable structure based on numerically controlled fraise machine, includes aircraft nose case 1, its characterized in that: the three-leg support 4 and the reinforcement sloping block 3 of foundry goods are equipped with to the below of aircraft nose case 1, one side of aircraft nose case 1 is equipped with milling machine frame 2, be equipped with slider 5 between aircraft nose case 1 and the milling machine frame 2.
The three-leg support 4 of foundry goods is connected through the whole casting mode between the aircraft nose case 1, the top surface of consolidating the sloping block 3 and the three-leg support 4 upper end top surface of foundry goods are in same water flat line, consolidate and be connected through the whole casting mode between sloping block 3 and the aircraft nose case 1.
And a plurality of groups of fixing bolts are arranged on the outer surfaces of two sides of the tripod support 4 of the casting piece and used for fixing the headstock 1.
The reinforcing inclined block 3 and the tripod support 4 of the casting form an integral workpiece, and the integral workpiece is formed by pouring through a specific die.
What need explain, the utility model relates to a aircraft nose case stable structure based on numerically controlled fraise machine, the three-legged setting of supporting 4 through the foundry goods, aircraft nose case 1 and milling machine frame 2's lifting surface area has been increased, because it links together between the three-legged 4 of aircraft nose case 1 and foundry goods to support, the moment in the 1 vertical side of aircraft nose case has been increased simultaneously, the supporting capacity in the 1 vertical side of aircraft nose case has been improved, it links together to consolidate between the three-legged 4 that supports of sloping block 3 and aircraft nose case 1 and foundry goods, consolidate the setting of sloping block 3, the supporting capacity on the whole inclined plane of aircraft nose case has been increased, the three-legged 4 that supports through the foundry goods and the mutually supporting of consolidating sloping block 3, both increased the supporting capacity of the 1 vertical direction of whole aircraft nose case and inclined plane direction, the stability of aircraft nose case has been improved.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (4)
1. The utility model provides a aircraft nose case stable structure based on numerically controlled fraise machine, includes aircraft nose case (1), its characterized in that: the three-leg support (4) and the reinforcement sloping block (3) of foundry goods are arranged below the machine head box (1), a milling machine frame (2) is arranged on one side of the machine head box (1), and a sliding block (5) is arranged between the machine head box (1) and the milling machine frame (2).
2. The machine head box stabilizing structure based on the numerical control milling machine according to claim 1, characterized in that: the three-leg support (4) of foundry goods are connected through the whole casting mode with aircraft nose case (1) between, the top surface of consolidating sloping block (3) and the three-leg support (4) upper end top surface of foundry goods are in same water flat line, consolidate and be connected through the whole casting mode between sloping block (3) and aircraft nose case (1).
3. The machine head box stabilizing structure based on the numerical control milling machine according to claim 1, characterized in that: the outer surfaces of two sides of the tripod support (4) of the casting are provided with a plurality of groups of fixing bolts for fixing the headstock (1).
4. The machine head box stabilizing structure based on the numerical control milling machine according to claim 1, characterized in that: the reinforcing inclined block (3) and the tripod support (4) of the casting form an integral workpiece, and the integral workpiece is formed by pouring through a die.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022964591.8U CN214920842U (en) | 2020-12-11 | 2020-12-11 | Aircraft nose case stable structure based on numerically controlled fraise machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022964591.8U CN214920842U (en) | 2020-12-11 | 2020-12-11 | Aircraft nose case stable structure based on numerically controlled fraise machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214920842U true CN214920842U (en) | 2021-11-30 |
Family
ID=79113835
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022964591.8U Active CN214920842U (en) | 2020-12-11 | 2020-12-11 | Aircraft nose case stable structure based on numerically controlled fraise machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214920842U (en) |
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2020
- 2020-12-11 CN CN202022964591.8U patent/CN214920842U/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 |
Address after: 528000 No. 68-1 (residence declaration) compiled by ourselves (TU Ming Da Sha Pian) to the north of Hefeng section, Guanhe Road, Heshun Hefeng village, Lishui Town, Nanhai District, Foshan City, Guangdong Province Patentee after: Lishan Intelligent Equipment (Guangdong) Co.,Ltd. Address before: 528000 No. 68-1 (residence declaration) compiled by ourselves (TU Ming Da Sha Pian) to the north of Hefeng section, Guanhe Road, Heshun Hefeng village, Lishui Town, Nanhai District, Foshan City, Guangdong Province Patentee before: FOSHAN LISHAN MACHINERY CO.,LTD. |
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| CP01 | Change in the name or title of a patent holder |