CN105773990A - Method for preventing fiber damage in helicopter tail rotor blade forming process - Google Patents
Method for preventing fiber damage in helicopter tail rotor blade forming process Download PDFInfo
- Publication number
- CN105773990A CN105773990A CN201610161178.3A CN201610161178A CN105773990A CN 105773990 A CN105773990 A CN 105773990A CN 201610161178 A CN201610161178 A CN 201610161178A CN 105773990 A CN105773990 A CN 105773990A
- Authority
- CN
- China
- Prior art keywords
- tail
- cloth
- rotor leaf
- die joint
- protection cloth
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
Abstract
The invention belongs to the technical field of composite materials and relates to a method for preventing fiber damage in a helicopter tail rotor blade forming process. According to the method, pre-cured protective cloth is arranged at a parting surface of a tail rotor blade forming die and used for preventing continuous glass cloth at the front edge of a tail rotor blade from being extruded out of a die body during die assembly, and cloth clamping is avoided in the tail rotor blade forming process, so that the tail rotor blade product quality is improved, and the reliability and safety of a helicopter are improved. Complete prevention of the cloth clamping condition is proved with adoption of the method at present, and the method is applied to production at present.
Description
Technical field
The invention belongs to technical field of composite materials, relate to a kind of method for preventing from damaging fiber in helicopter tail rotor leaf forming process.
Background technology
Helicopter tail rotor leaf moulding process adopts matched moulds die press technology for forming, before forming and hardening, owing to composite tail-rotor leaf has molding capacity, when matched moulds, near mould die joint edge, there is raw material extrusion situation.After forming and hardening cleaning, owing to being cleaned out by the raw material of extrusion, thus damage product glass fibre, thus reducing product strength.
Summary of the invention
The purpose of the present invention is to propose to a kind of a kind of method for preventing from damaging fiber in helicopter tail rotor leaf forming process that raw material is not easily extruded when matched moulds.The technical solution of the present invention is,
1) protection cloth is made
The first step: determine the length of protection cloth by the span-wise length of the die joint of tail-rotor leaf shaping mould; the span-wise length of die joint is be more than or equal to protection cloth length; and monolateral reservation 10mm surplus; the width of protection cloth is centered by die joint; upwards mould direction and counterdie direction are along stretching 20-30mm respectively, and material is identical with the material of tail-rotor leaf；
Second step: be laid in the frock identical with blade leading edge profile by the raw material of protection cloth, adopt vacuum bag-solidification of hot-press tank, determines cure parameter according to the protection raw-material material standard of cloth, solidifies；
3rd step: after having solidified, cuts the length of protection cloth, the monolateral removal 10mm of width of protection cloth according to the span-wise length of tail-rotor leaf shaping mould die joint；
2) molding tail-rotor leaf
The first step: according to the paved tail-rotor leaf of designing requirement; paved complete after; the bonding glued membrane one layer corresponding with protection cloth material of protection cloth inner surface that will have solidified, places one section of protection cloth along tail-rotor leaf shaping mould die joint or places multi-stage protective cloth along tail-rotor leaf shaping mould die joint；
Second step: matched moulds solidifies, and curing process carries out according to designing requirement.
The present invention has the advantage that and beneficial effect; adopt and place the protection cloth solidified in advance at the die joint place of tail-rotor leaf shaping mould; stoping tail-rotor leaf leading edge continuous print glass cloth extrusion die body during matched moulds, avoiding producing folder cloth in tail-rotor leaf forming process, thus improving tail-rotor leaf product quality; improve aircraft reliability, safety; at present, after adopting the method, empirical tests; folder cloth situation can be avoided completely, applied at present in production.
Accompanying drawing explanation
Fig. 1 is operation chart of the present invention, wherein: 1 tail-rotor leaf, 2 precuring protection glass cloth, 3 moulding upper moulds, 4 shaping mould counterdies.
Detailed description of the invention
1) protection cloth is made
The first step: determine the length of protection cloth 2 by the span-wise length of the die joint of paddle molding mould; the span-wise length of die joint is be more than or equal to protection cloth length; and monolateral reservation 10mm surplus; the width of protection cloth is centered by die joint; upwards mould 3 direction and counterdie 4 direction are along stretching 20-30mm respectively, and material is identical with the material of tail-rotor leaf 1；
Second step: be laid in the frock identical with blade leading edge profile by the raw material of protection cloth, adopt vacuum bag-solidification of hot-press tank, determines cure parameter according to the protection raw-material material standard of cloth, solidifies；
3rd step: after having solidified, cuts the length of protection cloth, the monolateral removal 10mm of width of protection cloth according to the span-wise length of tail-rotor leaf shaping mould die joint；
2) molding tail-rotor leaf
The first step: according to the paved tail-rotor leaf 1 of designing requirement, paved complete after, protection glass cloth 2 inner surface that will solidify bonding one layer with protect the corresponding glued membrane of cloth material, be rotated on the die joint of tail-rotor leaf shaping mould；
Second step: matched moulds solidifies, and curing process carries out according to designing requirement.
Embodiment
For helicopter tail rotor leaf shape, making protection cloth, protection cloth raw material is 3238A/EW250F/45,
The first step: by long 120mm, wide 50mm, 45 ° of direction is by glass cloth 3238A/EW250F/45 blanking；
Second step: be laid in special tooling by raw material, adopts vacuum bag-solidification of hot-press tank, cure parameter: temperature 100 DEG C～110 DEG C, 2～2.5 hours time, negative pressure 0.06-0.08MPa, malleation 0.4 ± 0.015Mpa；Precuring parameter is: temperature 100 DEG C～110 DEG C, 2～2.5 hours time, negative pressure 0.06-0.08MPa, malleation 0.4 ± 0.015Mpa；
3rd step: after having solidified, carries out trimming by frock line of cut to protection cloth；Layer of cloth is of a size of exhibition to long 100mm, tangential wide 30mm；
4th step: when tail-rotor leaf is paved complete after, precuring is protected the bonding 1 layer of SY-24CII glued membrane of cloth inner surface, is symmetrically disposed between tail-rotor leaf leading edge 440-540 section along leading edge die joint；
5th step: matched moulds solidifies.
Claims (2)
1., for preventing the method damaging fiber in tail-rotor leaf forming process, it is characterized in that,
1) protection cloth is made
The first step: determine the length of protection cloth by the span-wise length of the die joint of paddle molding mould; the span-wise length of die joint is be more than or equal to protection cloth length; and monolateral reservation 10mm surplus; the width of protection cloth is centered by die joint; upwards mould direction and counterdie direction are along stretching 20-30mm respectively, and material is identical with the material of tail-rotor leaf；
Second step: be laid in the frock identical with blade leading edge profile by the raw material of protection cloth, adopt vacuum bag-solidification of hot-press tank, determines cure parameter according to the protection raw-material material standard of cloth, solidifies；
3rd step: after having solidified, cuts the length of protection cloth, the monolateral removal 10mm of width of protection cloth according to the span-wise length of tail-rotor leaf shaping mould die joint；
2) molding tail-rotor leaf
The first step: according to the paved tail-rotor leaf of designing requirement, paved complete after, the protection cloth inner surface that will solidify bonding one layer with protect the corresponding glued membrane of cloth material, be rotated on the die joint of tail-rotor leaf shaping mould；
Second step: matched moulds solidifies, and curing process carries out according to designing requirement.
2. according to claim 1 a kind of it is characterized in that for preventing the method damaging fiber in tail-rotor leaf forming process, place one section of protection cloth along tail-rotor leaf shaping mould die joint or place multi-stage protective cloth along tail-rotor leaf shaping mould die joint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610161178.3A CN105773990A (en) | 2016-03-21 | 2016-03-21 | Method for preventing fiber damage in helicopter tail rotor blade forming process |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610161178.3A CN105773990A (en) | 2016-03-21 | 2016-03-21 | Method for preventing fiber damage in helicopter tail rotor blade forming process |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105773990A true CN105773990A (en) | 2016-07-20 |
Family
ID=56394255
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610161178.3A Pending CN105773990A (en) | 2016-03-21 | 2016-03-21 | Method for preventing fiber damage in helicopter tail rotor blade forming process |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105773990A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2655459A (en) * | 1948-06-11 | 1953-10-13 | James E Gordon | Method of producing an aerofoil having a core and a laminated molded skin |
| FR2562834A1 (en) * | 1984-04-12 | 1985-10-18 | Ranjon Marc | Process for manufacturing strong hollow components, especially parts of aircraft or of missiles, and components obtained thereby |
| CN204773155U (en) * | 2015-04-07 | 2015-11-18 | 中国直升机设计研究所 | Combined material paddle forming die |
| CN105082563A (en) * | 2014-05-16 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Method for preventing glue accumulating and cloth clamping on folding positions of composite workpieces formed through segment molds |
-
2016
- 2016-03-21 CN CN201610161178.3A patent/CN105773990A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2655459A (en) * | 1948-06-11 | 1953-10-13 | James E Gordon | Method of producing an aerofoil having a core and a laminated molded skin |
| FR2562834A1 (en) * | 1984-04-12 | 1985-10-18 | Ranjon Marc | Process for manufacturing strong hollow components, especially parts of aircraft or of missiles, and components obtained thereby |
| CN105082563A (en) * | 2014-05-16 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Method for preventing glue accumulating and cloth clamping on folding positions of composite workpieces formed through segment molds |
| CN204773155U (en) * | 2015-04-07 | 2015-11-18 | 中国直升机设计研究所 | Combined material paddle forming die |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160720 |