CN206083763U - Aircraft rack part wax matrix structure - Google Patents
Aircraft rack part wax matrix structure Download PDFInfo
- Publication number
- CN206083763U CN206083763U CN201620714684.6U CN201620714684U CN206083763U CN 206083763 U CN206083763 U CN 206083763U CN 201620714684 U CN201620714684 U CN 201620714684U CN 206083763 U CN206083763 U CN 206083763U
- Authority
- CN
- China
- Prior art keywords
- auricle
- base plate
- rack part
- plane
- aircraft rack
- 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
Landscapes
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
The utility model belongs to fired mold precision casting field relates to the improvement to a precision casting aircraft rack part wax matrix structure. The utility model discloses aircraft rack part wax matrix structure includes auricle (1), last brace rod (2), bottom plate (3), under bracing muscle (4), lower auricle (6) and the shape muscle (7) of preapring for an unfavorable turn of events. Wherein, the interior outside boss of going up auricle (1) and lower auricle (6) respectively increases L1=3mm, L2=3mm, bottom plate (3) are plane bodiness L4=3mm down, and plane bodiness L5=1~1.5mm is gone up in bottom plate (3), use diameter as D technology muscle (7) to be connected D=6mm between auricle (6) at last auricle (1) under and. The utility model provides a wax matrix structure of modified precision casting aircraft rack part, it is inharmonious the size to appear in eliminating rough casting production and processing, improves the qualification rate of foundry goods.
Description
Technical field
This utility model belongs to precision-investment casting field, is related to a kind of hot investment casting aircraft rack part wax-pattern structure
Improvement.
Background technology
During the actual manufacture of aircraft rack part, lost wax casting technology is typically adopted, that is, first passes through the wax of design trestle component
Mould, then poured into a mould.Existing aircraft trestle component wax-pattern structure is made up of upper auricle, base plate and lower auricle.Wherein, upper ear
Piece and lower auricle are a pair similar gengons, and from side circular sliding slopes, distance is L, respectively has one on the inside of upper auricle and lower auricle
The round boss of individual a height of L1.On base plate, plane keeps angle a with the centrage of upper auricle and lower auricle.Upper auricle and lower auricle
On have a concentric holes, the centrage of concentric holes with the intersection point of upper auricle and the center line of lower auricle to the distance of the lower plane of base plate is
H.Which has the disadvantage：Due to the processing of the interior outside boss of the base plate lower plane, upper auricle and lower auricle of aircraft rack part wax-pattern
Surplus is too little, and on base plate, plane is without allowance, when processing on the basis of the center line for causing above auricle and lower auricle, the thickness of base plate
Degree cannot meet no anti-deformation muscle connection, L chis between upper auricle and lower auricle between drawing requirement, and upper auricle and lower auricle
It is very little to meet drawing required precision.Therefore size L, a, H are frequently found in spray production and in processing uncoordinated, are caused
Size L1 skewness on upper auricle and lower auricle, assembles unqualified.
The content of the invention
The purpose of this utility model is：Propose a kind of can effectively eliminate the production of trestle component blank and occur in processing
Size is uncoordinated, improves the aircraft rack part wax-pattern structure of trestle component qualification rate.
The technical solution of the utility model is：A kind of aircraft rack part wax-pattern structure, which includes auricle 1, upper support
Muscle 2, base plate 3, lower brace rod 4, lower auricle 6 and anti-deformation muscle 7, upper auricle 1 and lower auricle 6 are mutually corresponding, and the two distance is
L, and bottom is connected as one, and be fixed on base plate 3, respectively there is the convex of an a height of L1 on the inside of upper auricle 1 and lower auricle 6
Platform, on base plate 3, plane keeps angle a, upper brace rod 2 and lower brace rod 4 to be arranged on the centrage of upper auricle 1 and lower auricle 6
On base plate 3, upper auricle 1 and lower auricle 6 are supported respectively, has a concentric holes 5, the center of concentric holes 5 on upper auricle 1 and lower auricle 6
Line is H with the distance of intersection point to the lower plane of base plate 3 of upper auricle 1 and the center line of lower auricle 6, and anti-deformation muscle 7 is a cylinder
Body, is connected with the inner convex platform on the inside of upper auricle 1, the inner convex platform on the inside of lower auricle 6 respectively.
Upper auricle 1 and lower auricle 6 are respectively provided with an outer lug boss.
The height L2 of the height L1 of upper auricle 1 and lower 6 inner convex platform of auricle, upper auricle 1 and lower 6 outer lug boss of auricle, wherein, it is high
Degree L1 is more than height L2, and height L2 is at least 3mm.
3 lower plane of base plate thickens L4:3mm, on base plate 3, plane thickens L5:1～1.5mm.
7 diameter dimension D of anti-deformation muscle between upper auricle 1 and lower auricle 6:6mm.
Upper brace rod 2 and lower brace rod 4 are the irregular thin plate of profile.
The utility model has the advantages that：Propose a kind of wax-pattern structure of improved hot investment casting aircraft rack part, energy
It is enough effectively to eliminate spray production and in processing, occur that size is uncoordinated, improve the qualification rate of foundry goods.Of the present utility model one
Individual embodiment, tests prove that, the qualification rate of foundry goods reaches 100%.
Description of the drawings
Fig. 1 is the structural representation of this utility model aircraft rack part wax-pattern structure,
Wherein, auricle, 7- anti-deformations under brace rod, 5- concentric holes, 6- under the upper auricles of 1-, the upper brace rods of 2-, 3- base plates, 4-
Muscle.
Specific embodiment
Below this utility model is described in further details.Referring to Fig. 1, a kind of wax of hot investment casting aircraft rack part
Mode structure, it is made up of upper auricle 1, upper brace rod 2, base plate 3, lower brace rod 4, lower auricle 6 and anti-deformation muscle 7,1 He of upper auricle
Lower auricle 6 is a pair similar gengons, and from side circular sliding slopes, distance is L, respectively has one on the inside of upper auricle 1 and lower auricle 6
The round boss of a height of L1, outside also respectively have a boss, and base plate 3 is a square, on base plate 3 plane and upper auricle 1 and under
Auricle 6 is connected in entirety at upper auricle 1 and lower 6 circular sliding slopes of auricle, plane and upper auricle 1 and the center of lower auricle 6 on base plate 3
Line keeps angle a.Upper brace rod 2 and lower brace rod 4 are the irregular thin plates of profile, with base plate and upper and lower auricle shape phase
Match somebody with somebody, and auricle 1 and lower auricle 6 on the midfoot support of base plate 3.There are a concentric holes 5, concentric holes 5 on upper auricle 1 and lower auricle 6
Centrage and upper auricle 1 and the center line of lower auricle 6 intersection point to the lower plane of base plate 3 distance be H, anti-deformation muscle 7 is one
Individual cylinder, is connected with the round boss on the inside of upper auricle 1, the round boss on the inside of lower auricle 6 respectively.
Wherein, the interior outside boss (everywhere) of upper auricle 1 and lower auricle 6 respectively increases L1=3mm, L2=3mm；Under base plate 3
Plane thickens L4=3mm, and on base plate 3, plane thickens L5=1～1.5mm；With a diameter of D's between upper auricle 1 and lower auricle 6
Anti-deformation muscle 7 is connected, D=6mm.
Operation principle of the present utility model is：This utility model increases surplus L5 to the upper plane of base plate 3, increases base plate 3
The inner convex platform allowance L1 of lower plane allowance L4, upper auricle 1 and lower auricle 6, outer lug boss allowance L2, and in upper ear
It is connected with anti-deformation muscle 7 between piece 1 and lower auricle 6.So when processing to blank, scribing inspection is carried out to blank first anti-
Push away, with baseplane as roughing standard, review notch angles a and deflection size, after determining angle zero deflection, it is ensured that base plate thickness,
Cooperative dimensioning L and inner convex platform finished size, to ensure the friendship of the centrage of concentric holes 5 and upper auricle 1 and the center line of lower auricle 6
The distance of point to the lower plane of base plate 3 is H, and following process size gives in frock and ensure, reduces processing intensity, improves zero
Part machining accuracy, so as to ensure that the dimensional accuracy after Mechanical processing of casting.
Embodiment
On base plate 3, plane thickens L5=1.5mm.8 kinds of trial production medium-height trestle foundry goods, has been used uniformly across similar optimization side
Case, produces trestle component blank 16 altogether, and 16 foundry goods are all qualified through processing.
Claims (6)
1. a kind of aircraft rack part wax-pattern structure, it is characterised in that including upper auricle (1), upper brace rod (2), base plate (3),
Lower brace rod (4), lower auricle (6) and anti-deformation muscle (7), upper auricle (1) and lower auricle (6) are mutually corresponding, and the two distance is
L, and bottom is connected as one, and be fixed on base plate (3), respectively have an a height of L1's on the inside of upper auricle (1) and lower auricle (6)
Inner convex platform, on base plate (3), the centrage of plane and upper auricle (1) and lower auricle (6) keeps angle a, upper brace rod (2) and lower
Support muscle (4) is arranged on base plate (3), is supported upper auricle (1) and lower auricle (6) respectively, is had on upper auricle (1) and lower auricle (6)
Under one concentric holes (5), the centrage of concentric holes (5) and the intersection point of upper auricle (1) and the center line of lower auricle (6) to base plate (3)
The distance of plane is H, and anti-deformation muscle (7) is a cylinder, respectively with upper auricle (1) on the inside of inner convex platform, in lower auricle (6)
The inner convex platform connection of side.
2. aircraft rack part wax-pattern structure according to claim 1, it is characterised in that upper auricle (1) and lower auricle (6)
It is respectively provided with an outer lug boss.
3. aircraft rack part wax-pattern structure according to claim 2, it is characterised in that upper auricle (1) and lower auricle (6)
The height L2 of the height L1 of inner convex platform, upper auricle (1) and lower auricle (6) outer lug boss, wherein, height L1 is more than height L2, and high
Degree L2 is at least 3mm.
4. aircraft rack part wax-pattern structure according to claim 1, it is characterised in that base plate (3) lower plane thickens L4:
3mm, on base plate (3), plane thickens L5:1～1.5mm.
5. aircraft rack part wax-pattern structure according to claim 1, it is characterised in that upper auricle (1) and lower auricle (6)
Between anti-deformation muscle (7) diameter dimension D:6mm.
6. aircraft rack part wax-pattern structure according to claim 1, it is characterised in that upper brace rod (2) and lower support
Muscle (4) is the irregular thin plate of profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620714684.6U CN206083763U (en) | 2016-07-08 | 2016-07-08 | Aircraft rack part wax matrix structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620714684.6U CN206083763U (en) | 2016-07-08 | 2016-07-08 | Aircraft rack part wax matrix structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206083763U true CN206083763U (en) | 2017-04-12 |
Family
ID=58465948
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620714684.6U Active CN206083763U (en) | 2016-07-08 | 2016-07-08 | Aircraft rack part wax matrix structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206083763U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108213345A (en) * | 2018-03-02 | 2018-06-29 | 沈阳飞机工业（集团）有限公司 | A kind of " C " shape perforated wall is thicker than crossing violent Al-Cu line aluminium alloy Melt casting deformation control methods |
-
2016
- 2016-07-08 CN CN201620714684.6U patent/CN206083763U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108213345A (en) * | 2018-03-02 | 2018-06-29 | 沈阳飞机工业（集团）有限公司 | A kind of " C " shape perforated wall is thicker than crossing violent Al-Cu line aluminium alloy Melt casting deformation control methods |
| CN108213345B (en) * | 2018-03-02 | 2019-10-08 | 沈阳飞机工业（集团）有限公司 | A kind of Al-Cu system investment-casting deformation control method that the wall thickness transition of " C " shape is violent |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107282892A (en) | A kind of 3D printing core formative method of aluminium alloy castings | |
| CN204035566U (en) | The shaping mould of powder metallurgy structural part | |
| CN103433416A (en) | AZ80A magnesium alloy engine case isothermal forging forming mould and method | |
| CN206083763U (en) | Aircraft rack part wax matrix structure | |
| CN103433460A (en) | Mold for bracket provided with sunken platform on pin hole part | |
| CN106584012B (en) | A kind of amorphous alloy shaping methods | |
| CN104550755A (en) | Precision casting method for graphite mould-ceramic core titanium alloy | |
| CN104759592A (en) | Preparation method of sand core for manufacturing large-sized thin-wall framework-type casting | |
| CN105562613B (en) | A kind of one-time formed method of aero-engine porous plate diverging cooling turbo blade ceramic core | |
| CN204308354U (en) | A kind of multi-cavity type electric machining graphite electrode | |
| CN205551402U (en) | Transversely cast psammitolite equipment tool | |
| CN205927014U (en) | Return bend sand -lined metal mold mould | |
| CN203356546U (en) | Reinforcing device for large-scale complex wax pattern piece during investment casting and coating | |
| CN210475410U (en) | Hollow structure wax mould for producing thick and large parts | |
| CN208644024U (en) | A kind of hardened sand mould positioning pin with venting plug | |
| CN202621830U (en) | Precision casting dust preventing device | |
| CN105903964A (en) | 3D printing equipment with double-station structure | |
| CN201735742U (en) | Steel ingot for forging or rolling | |
| CN203448595U (en) | Forging equipment for forming annealing furnace bottom plate | |
| CN204912722U (en) | Galileo base casting mold | |
| CN206662195U (en) | A kind of ejector beam | |
| CN205673601U (en) | There is the 3D printing device of double structure | |
| CN205967352U (en) | Module location structure of production aluminum alloy knuckle | |
| CN202946843U (en) | Low-cost inertial unit foundation bed | |
| CN204035475U (en) | A kind of steel ball lateral leakage protection pouring device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |