CN107570626A - A kind of process for the shaping of helicopter blade iron clad - Google Patents
A kind of process for the shaping of helicopter blade iron clad Download PDFInfo
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- CN107570626A CN107570626A CN201710586093.4A CN201710586093A CN107570626A CN 107570626 A CN107570626 A CN 107570626A CN 201710586093 A CN201710586093 A CN 201710586093A CN 107570626 A CN107570626 A CN 107570626A
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Abstract
The present invention relates to a kind of process for the shaping of helicopter blade iron clad, comprise the following steps：1：It will deploy on plate placement and plate support frame 4；2：Upper and lower die body matched moulds, press-bending preform is carried out to plate；3：Both sides clamping jaw 8 carries out clamping to part both sides preform woollen；4：Upper and lower die body divides mould, and both sides clamping jaw 8 stretches to part；5：While both sides tensile force is kept, upper and lower die body matched moulds, swaging is carried out to part；6：Upper and lower die body divides mould, and both sides clamping jaw 8 stretches to part；7：Die body divides mould up and down after circulating 3~5 times, unclamps both sides clamping jaw, takes out part；8：Cutting profile, remove unnecessary clout.Composite material blade coating iron at the leading edge Forming Technique of the present invention can complete the manufacture of the long scope blade iron clads of 1000~7000mm, ensure within patch tire degree 0.5, without manual correction, ensure that the workmanship of part, improve operating efficiency, reduce production cost.
Description
Technical field
The invention belongs to a kind of Forming Technique of composite material blade coating iron at the leading edge, is related to one kind and is used for coating iron at the leading edge
The process of part manufacture.
Background technology
Coating iron at the leading edge part, as shown in Figure of description 1, it is mainly used in helicopter and protects rotor blade to keep away among flight
From to wind sand contamination erosion and foreign matter hit etc..To by resin-bonded iron clad together and glass fibre reinforced composion it
Between main blade for, the shaping of coating iron at the leading edge part patch tire degree, form accuracy and part edge state are directly connected to blade
Integral die forming quality, its surface quality directly influences the aerodynamic configuration of main blade.Such part aerofoil section is general
About 2.13 ° are uniformly reversed along its length, and nearly blade tip lateral wing type cross-sectional width uniformly narrows.Part height is 128mm, and deformation is most
General goal is arc top R7 fillets, and remaining is big radian side wall.Resilience is big after being shaped with existing manufacturing process, is difficult to school by hand
Just, and surface quality is poor.
The content of the invention
In view of the deficienciess of the prior art, the present invention provides a kind of system suitable for the long blade iron clads of 1000-7000mm
Process and special tooling are made, is pasted naturally within tire degree 0.5mm after ensureing part forming.
The technical scheme is that：A kind of special tooling for the shaping of helicopter blade iron clad, including shaping main mould
Body portion and stretching gripping portions, main mould body portion include upper mould metal and hold frame 1, epoxy resin packed layer 2, flexible cavity plate 3, exhibition
Open plate support frame 4, frock limited block 5, metal die 6, metal lower template 7；In flexible cavity plate 3 outside lumen type face and forming part
Type face is consistent, and metal die 6 is consistent with part forming inner mold face, and both form forming parts groundwork face；Outside flexible cavity plate 3
Side is provided with mould metal and holds frame 1, and upper mould metal, which holds, fills epoxy resin 2 between frame 1 and flexible cavity plate 3, epoxy resin 2 is simultaneously
Also serve connecting the two, form independent upper mould die body；Frock limited block 5 is arranged on the non-working surface region of metal die 6,
For limiting frock stroke, prevent from causing excess compression to flexible cavity plate 3；The lower end of metal die 6 is provided with metal lower template 7,
Metal lower template 7 is provided with expansion plate support frame 4, metal die 6, frock limited block 5, expansion plate support frame 4 and metal
Lower template 7 is integrated, forms independent lower mould die body.Expansion plate support frame 4 is used to support part forming woollen.Stretch clamping jaw portion
Dividing includes combining fixture block 8 and sandwich 9, and stretching clamping jaw is distributed in shaping main mould body both ends, for pressing part after bending to enter at lock
Row grab tensile, the outer mold surface of sandwich 9 is consistent with part inner mold face, and combination fixture block 8 is consistent with the outer mold surface of part, and material uses
No. 45 steel or other rigid metallic materials.
The flexible material of cavity plate 3 is 4061 rubber, and the material hardness is moderate, and has certain decrement, complexed metal punch-pin 6
Shaping, allows part in whole length direction uniform force, transformation rule.And flexible cavity plate can reach to a certain extent
The bending of similar drawing state, bending quality can also be improved accordingly.Therefore flexible cavity plate uses 4061 flexible type faces, shore hardness
70 or so, to ensure that part all forming faces in forming process are pressed against punch-pin, between concave panel and metal framework mould
Fill epoxy resin.Metal die holds mount structure using metal, and material is No. 45 steel.Remaining associate member such as plate rack, limit
Position block and connecting plate etc., can use A3 steel, the visual actual conditions of structure freely adjust.
The surface roughness of metal die 6 is along type face 1.6.
When carrying out lock pressure bending forming to part, while tangential or longitudinal pulling force is applied to part, change slab interior
Stress state and distribution situation, plate is shaped in the presence of three-dimensional stress.The tension size applied should make bending
The combined stress of each point is slightly larger than the yield stress of material in deformed area, allows whole section to be in plastic elongation deformation range, this
The inside and outside area's ess-strain direction of sample is agreed, and after unloading, the trend of rebound of ectonexine is cancelled out each other, and reduces resilience.And
In the presence of tension, while the agitating and the defects of slack list of raw material can be eliminated.By Dynaform softwares to the technique
Scheme carries out analogue simulation, the more conventional 10mm of part springback capacity or so and is down to 0.5mm or so, substantially eliminates resilience.
For the process of helicopter blade iron clad shaping, comprise the following steps：
Step 1：It will deploy on plate placement and plate support frame 4；
Step 2：Upper and lower die body matched moulds, press-bending preform is carried out to plate；
Step 3：Both sides clamping jaw 8 carries out clamping to part both sides preform woollen；
Step 4：Upper and lower die body divides mould, and both sides clamping jaw 8 stretches to part；
Step 5：While both sides tensile force is kept, upper and lower die body matched moulds, swaging is carried out to part；
Step 6：Upper and lower die body divides mould, and both sides clamping jaw 8 stretches to part；
Step 7：Die body divides mould up and down after circulating 3~5 times, unclamps both sides clamping jaw, takes out part；
Step 8：Cutting profile, remove unnecessary clout.
It is an advantage of the invention that：Composite material blade coating iron at the leading edge Forming Technique of the present invention can complete 1000~
The manufacture of the long scope blade iron clads of 7000mm, ensure within patch tire degree 0.5, without manual correction, ensure that the manufacture of part
Quality, operating efficiency is improved, reduce production cost.
Brief description of the drawings
Fig. 1 is blade iron clad part axial view；
Fig. 2 is tension and compression combined shaping special tooling section view, 1, upper mould metal hold frame；2nd, epoxy resin packed layer；3、
4061 flexible cavity plates；4th, plate support frame is deployed；5th, frock limited block；6th, metal die；7th, metal lower template；
Fig. 3 is stretching clamping jaw structure view.
Embodiment
The present invention is described in further detail with reference to Figure of description.
A kind of special tooling for the shaping of helicopter blade iron clad, including shaping main mould body portion and stretching clamping jaw portion
Point, main mould body portion includes upper mould metal and holds frame 1, epoxy resin packed layer 2, flexible cavity plate 3, expansion plate support frame 4, frock
Limited block 5, metal die 6, metal lower template 7；Lumen type face is consistent with forming part outer mold surface in flexible cavity plate 3, metal die 6
Consistent with part forming inner mold face, both form forming parts groundwork face；The flexible outside of cavity plate 3 is provided with mould metal appearance
Frame 1, upper mould metal, which holds, fills epoxy resin 2 between frame 1 and flexible cavity plate 3, epoxy resin 2 also plays work connecting the two simultaneously
With forming independent upper die body；Frock limited block 5 is arranged on the non-working surface region of metal die 6, for limiting frock stroke,
Prevent from causing excess compression to flexible cavity plate 3；The lower end of metal die 6 is provided with metal lower template 7, and metal lower template 7 is provided with
Deploy plate support frame 4, metal die 6, frock limited block 5, expansion plate support frame 4 are integrated with metal lower template 7, are formed only
Vertical lower mould die body, as shown in Figure 2.Expansion plate support frame 4 is used to support part forming woollen.Stretching gripping portions include group
Co-clip block 8 and sandwich 9, stretching clamping jaw are distributed in shaping main mould body both ends, for pressing part after bending to carry out clamping drawing at lock
Stretch, the outer mold surface of sandwich 9 is consistent with part inner mold face, and combination fixture block 8 is consistent with the outer mold surface of part, as shown in figure 3, material is adopted
With No. 45 steel or other rigid metallic materials.
The flexible material of cavity plate 3 is 4061 rubber, and the material hardness is moderate, and has certain decrement, complexed metal punch-pin 6
Shaping, allows part in whole length direction uniform force, transformation rule.And flexible cavity plate can reach to a certain extent
The bending of similar drawing state, bending quality can also be improved accordingly.Therefore flexible cavity plate uses 4061 flexible type faces, shore hardness
70 or so, to ensure that part all forming faces in forming process are pressed against punch-pin, between concave panel and metal framework mould
Fill epoxy resin.Metal die holds mount structure using metal, and material is No. 45 steel.Remaining associate member such as plate rack, limit
Position block and connecting plate etc., can use A3 steel, the visual actual conditions of structure freely adjust.
The surface roughness of metal die 6 is along type face 1.6.
For the process of helicopter blade iron clad shaping, comprise the following steps：
Step 1：It will deploy on plate placement and plate support frame 4；
Step 2：Upper and lower die body matched moulds, press-bending preform is carried out to plate；
Step 3：Both sides clamping jaw 8 carries out clamping to part both sides preform woollen；
Step 4：Upper and lower die body divides mould, and both sides clamping jaw 8 stretches to part；
Step 5：While both sides tensile force is kept, upper and lower die body matched moulds, swaging is carried out to part；
Step 6：Upper and lower die body divides mould, and both sides clamping jaw 8 stretches to part；
Step 7：Die body divides mould up and down after circulating 3~5 times, unclamps both sides clamping jaw, part is taken out, according to part dimension size
Determine the number of circulation；
Step 8：Cutting profile, unnecessary clout is removed, helicopter blade iron clad needed for formation.
When carrying out lock pressure bending forming to part, while tangential or longitudinal pulling force is applied to part, change slab interior
Stress state and distribution situation, plate is shaped in the presence of three-dimensional stress.The tension size applied should make bending
The combined stress of each point is slightly larger than the yield stress of material in deformed area, allows whole section to be in plastic elongation deformation range, this
The inside and outside area's ess-strain direction of sample is agreed, and after unloading, the trend of rebound of ectonexine is cancelled out each other, and reduces resilience.And
In the presence of tension, while the agitating and the defects of slack list of raw material can be eliminated.By Dynaform to the process program
Carry out analogue simulation, the more conventional 10mm of part springback capacity or so and be down to 0.5mm or so, substantially eliminate resilience.
Claims (5)
- A kind of 1. special tooling for the shaping of helicopter blade iron clad, it is characterised in that：Including shaping main mould body portion and drawing Gripping portions are stretched, shaping main mould body portion includes upper mould metal and holds frame (1), epoxy resin packed layer (2), flexible cavity plate (3), exhibition Open plate support frame (4), frock limited block (5), metal die (6), metal lower template (7)；The flexible interior lumen type face of cavity plate (3) with Part outer mold surface is consistent, and metal die (6) is consistent with part forming inner mold face, and both form forming parts groundwork face；It is soft Property cavity plate (3) on the outside of mould metal be installed hold frame (1), upper mould metal holds fills asphalt mixtures modified by epoxy resin between frame (1) and flexible cavity plate (3) Fat (2), upper mould metal hold frame (1) and form independent upper die body with flexible cavity plate (3) and filling epoxy resin (2)；Frock limits Position block (5) is arranged on metal die (6) non-working surface region, and metal die (6) lower end is provided with metal lower template (7), metal Expansion plate support frame (4), metal die (6), frock limited block (5), expansion plate support frame are installed in lower template (7) (4) it is integrated with metal lower template (7), form independent lower mould die body；Stretching gripping portions includes combination fixture block (8) and sandwich (9), stretching clamping jaw is distributed in shaping main mould body both ends, and for pressing part after bending to carry out grab tensile at lock, sandwich (9) is outside Type face is consistent with part inner mold face, and combination fixture block (8) is consistent with the outer mold surface of part.
- 2. the special tooling according to claim 1 for the shaping of helicopter blade iron clad, it is characterised in that：Flexible cavity plate (3) material is 4061 rubber.
- 3. the special tooling according to claim 1 for the shaping of helicopter blade iron clad, it is characterised in that：Metal die Mount structure is held using metal, material is No. 45 steel.
- 4. the special tooling according to claim 1 for the shaping of helicopter blade iron clad, it is characterised in that：Metal die (6) surface roughness is along type face 1.6.
- 5. a kind of process for the shaping of helicopter blade iron clad, comprise the following steps：Step 1：It will deploy on plate placement and plate support frame (4)；Step 2：Upper and lower die body matched moulds, press-bending preform is carried out to plate；Step 3：Both sides clamping jaw (8) carries out clamping to part both sides preform woollen；Step 4：Upper and lower die body divides mould, and both sides clamping jaw (8) stretches to part；Step 5：While both sides tensile force is kept, upper and lower die body matched moulds, swaging is carried out to part；Step 6：Upper and lower die body divides mould, and both sides clamping jaw (8) stretches to part；Step 7：Die body divides mould up and down after circulating 3~5 times, unclamps both sides clamping jaw, takes out part；Step 8：Cutting profile, remove unnecessary clout.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710586093.4A CN107570626A (en) | 2017-07-18 | 2017-07-18 | A kind of process for the shaping of helicopter blade iron clad |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710586093.4A CN107570626A (en) | 2017-07-18 | 2017-07-18 | A kind of process for the shaping of helicopter blade iron clad |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107570626A true CN107570626A (en) | 2018-01-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710586093.4A Pending CN107570626A (en) | 2017-07-18 | 2017-07-18 | A kind of process for the shaping of helicopter blade iron clad |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109500156A (en) * | 2018-12-28 | 2019-03-22 | 天津航天长征火箭制造有限公司 | Grid siding bend molding apparatus and method in a kind of high muscle thickness rate |
| CN109591326A (en) * | 2018-10-12 | 2019-04-09 | 江西昌河航空工业有限公司 | One kind being used for the molding iron clad elastic mould manufacturing method of blade leading edge |
| CN111421077A (en) * | 2020-03-30 | 2020-07-17 | 成都飞机工业（集团）有限责任公司 | Half-mode brake press forming method and device for thin-wall sheet metal part |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101890453A (en) * | 2010-07-19 | 2010-11-24 | 哈尔滨飞机工业集团有限责任公司 | Method and die for molding skins front edges of rotary wings of aircraft by stretching and compressing |
| US20120137749A1 (en) * | 2010-12-06 | 2012-06-07 | Hyundai Motor Company | Press system |
| CN203343285U (en) * | 2013-06-17 | 2013-12-18 | 哈尔滨飞机工业集团有限责任公司 | Pulling-pressing forming mould for helicopter rotor front edge wrapping piece |
| CN105642755A (en) * | 2014-11-14 | 2016-06-08 | 江西昌河航空工业有限公司 | Molding tool for cladding iron at front edge of blade |
-
2017
- 2017-07-18 CN CN201710586093.4A patent/CN107570626A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101890453A (en) * | 2010-07-19 | 2010-11-24 | 哈尔滨飞机工业集团有限责任公司 | Method and die for molding skins front edges of rotary wings of aircraft by stretching and compressing |
| US20120137749A1 (en) * | 2010-12-06 | 2012-06-07 | Hyundai Motor Company | Press system |
| CN203343285U (en) * | 2013-06-17 | 2013-12-18 | 哈尔滨飞机工业集团有限责任公司 | Pulling-pressing forming mould for helicopter rotor front edge wrapping piece |
| CN105642755A (en) * | 2014-11-14 | 2016-06-08 | 江西昌河航空工业有限公司 | Molding tool for cladding iron at front edge of blade |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109591326A (en) * | 2018-10-12 | 2019-04-09 | 江西昌河航空工业有限公司 | One kind being used for the molding iron clad elastic mould manufacturing method of blade leading edge |
| CN109500156A (en) * | 2018-12-28 | 2019-03-22 | 天津航天长征火箭制造有限公司 | Grid siding bend molding apparatus and method in a kind of high muscle thickness rate |
| CN111421077A (en) * | 2020-03-30 | 2020-07-17 | 成都飞机工业（集团）有限责任公司 | Half-mode brake press forming method and device for thin-wall sheet metal part |
| CN111421077B (en) * | 2020-03-30 | 2021-12-10 | 成都飞机工业（集团）有限责任公司 | Half-mode brake press forming method and device for thin-wall sheet metal part |
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Application publication date: 20180112 |