CN108068354A - A kind of positional punch method of composite material honeycomb interlayer part packing area - Google Patents

A kind of positional punch method of composite material honeycomb interlayer part packing area Download PDF

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Publication number
CN108068354A
CN108068354A CN201611001004.7A CN201611001004A CN108068354A CN 108068354 A CN108068354 A CN 108068354A CN 201611001004 A CN201611001004 A CN 201611001004A CN 108068354 A CN108068354 A CN 108068354A
Authority
CN
China
Prior art keywords
honeycomb interlayer
packing area
conical section
die face
composite material
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
Application number
CN201611001004.7A
Other languages
Chinese (zh)
Inventor
陈晨
管海新
徐大鹏
丁奇锋
李锦�
李伟
钟景兴
谈健
刘望子
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Jiangxi Changhe Aviation Industries Co Ltd
Original Assignee
Jiangxi Changhe Aviation Industries Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Jiangxi Changhe Aviation Industries Co Ltd filed Critical Jiangxi Changhe Aviation Industries Co Ltd
Priority to CN201611001004.7A priority Critical patent/CN108068354A/en
Publication of CN108068354A publication Critical patent/CN108068354A/en
Pending legal-status Critical Current

Links

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
    • 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
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/541—Positioning reinforcements in a mould, e.g. using clamping means for the reinforcement
    • 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
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/545—Perforating, cutting or machining during or after moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/60—Multitubular or multicompartmented articles, e.g. honeycomb
    • B29L2031/608—Honeycomb structures

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Laminated Bodies (AREA)
  • Underground Structures, Protecting, Testing And Restoring Foundations (AREA)

Abstract

The invention belongs to aviation composite part manufacturing fields, and in particular to a kind of positional punch method of composite material honeycomb interlayer part packing area.Some composite materials honeycomb interlayer part, below minor diameter clear size of opening Φ 50mm, setting-out positioning easily cause deviations, and filling filler of doing over again is needed after causing drilling part.The positional punch method of the composite material honeycomb interlayer part packing area of the present invention, cone pin is provided on the theoretical punch position of frock and only exposes conical section, die face prepreg is pasted in paving on the type face of the frock, then according to the patch die face prepreg of conical section excision protrusion；Honeycomb interlayer is placed, filler is filled centered on the conical section；The non-patch die face prepreg of paving, global transfer and temperature-pressure curing；It is drilled according to the bellmouth that bottom is formed.Reduce packing area positioning difficulty in part manufacturing process, improve packing area positional precision, reduce repair rate of doing over again, improve product quality.

Description

A kind of positional punch method of composite material honeycomb interlayer part packing area
Technical field
The invention belongs to aviation composite part manufacturing fields, and in particular to a kind of composite material honeycomb interlayer part is filled out Expect the positional punch method in area.
Background technology
Some composite materials honeycomb interlayer part, below minor diameter clear size of opening Φ 50mm, such fill area need to be in part It is filled during laying process.Since process is setting-out positioning, deviations are easily caused, need to do over again after causing drilling part Fill filler.
The content of the invention
The present invention protrudes from the conical dowel pin in frock type face by increasing in forming parts frock, to complete laying work Packing area is accurately positioned during sequence.
The positional punch method of the composite material honeycomb interlayer part packing area of the present invention, for processing diameter in fill area Less than the through hole of Φ 50mm, this method is provided with cone pin on the theoretical punch position of frock and only exposes conical section, Die face prepreg is pasted in paving on the type face of the frock, then according to the patch die face prepreg of conical section excision protrusion； Honeycomb interlayer is placed, filler is filled centered on the conical section, scope is more than the through-hole diameter；The non-patch die face of paving Prepreg, global transfer and temperature-pressure cure；After part removal, according to the bellmouth that bottom is formed, drill.
Further, the top angle of the cone pin is 90 degree.
The beneficial effects of the invention are as follows：Reduce packing area positioning difficulty in part manufacturing process, improve filler zone position essence Degree reduces repair rate of doing over again, and improves product quality.
Description of the drawings
Fig. 1 is the structure diagram of the upper conical pin of forming frock of the present invention；
Fig. 2 is paving schematic diagram of the composite material honeycomb interlayer part of the present invention on forming frock.
Specific embodiment
A kind of positional punch method of composite material honeycomb interlayer part packing area, for being less than in fill area processing diameter The through hole of Φ 50mm, this method is provided with cone pin 2 on the theoretical punch position of frock 1 and only exposes conical section, in institute Paving patch die face prepreg 3 on the type face of frock 1 is stated, then according to the patch die face prepreg 3 of conical section excision protrusion； Honeycomb interlayer 4 is placed, filler is filled centered on the conical section, scope is more than the through-hole diameter；The non-patch mould of paving Face prepreg 5, global transfer and temperature-pressure cure；After part removal, according to the bellmouth that bottom is formed, drill.Institute The top angle for stating cone pin 2 is 90 degree.

Claims (2)

1. a kind of positional punch method of composite material honeycomb interlayer part packing area, for being less than Φ in fill area processing diameter The through hole of 50mm, it is characterised in that：This method is provided with cone pin (2) on the theoretical punch position of frock (1) and only exposes Conical section, the paving patch die face prepreg (3) on the type face of the frock (1) are then cut off convex according to the conical section The patch die face prepreg (3) risen；Honeycomb interlayer (4) is placed, filler is filled centered on the conical section, scope is more than institute State through-hole diameter；The non-patch die face prepreg (5) of paving, global transfer and temperature-pressure curing；After part removal, according to bottom shape Into bellmouth, drill.
2. positional punch method according to claim 1, it is characterised in that：The top angle of the cone pin (2) is 90 Degree.
CN201611001004.7A 2016-11-14 2016-11-14 A kind of positional punch method of composite material honeycomb interlayer part packing area Pending CN108068354A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201611001004.7A CN108068354A (en) 2016-11-14 2016-11-14 A kind of positional punch method of composite material honeycomb interlayer part packing area

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201611001004.7A CN108068354A (en) 2016-11-14 2016-11-14 A kind of positional punch method of composite material honeycomb interlayer part packing area

Publications (1)

Publication Number Publication Date
CN108068354A true CN108068354A (en) 2018-05-25

Family

ID=62162368

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201611001004.7A Pending CN108068354A (en) 2016-11-14 2016-11-14 A kind of positional punch method of composite material honeycomb interlayer part packing area

Country Status (1)

Country Link
CN (1) CN108068354A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109591334A (en) * 2018-10-12 2019-04-09 江西昌河航空工业有限公司 A kind of localization method of pair of honeycomb parts punching
CN112372924A (en) * 2020-10-14 2021-02-19 东风汽车集团有限公司 Hole making method of foaming sandwich structure

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102950781A (en) * 2012-11-23 2013-03-06 成都飞机工业（集团）有限责任公司 Hole making method of thin-walled honeycomb sandwich composite structural member
CN103240888A (en) * 2013-04-27 2013-08-14 哈尔滨飞机工业集团有限责任公司 Glass steel die positioning hole processing method
CN103586500A (en) * 2013-11-04 2014-02-19 中航成飞民用飞机有限责任公司 Hole making method for honeycomb interlayer composite materials

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102950781A (en) * 2012-11-23 2013-03-06 成都飞机工业（集团）有限责任公司 Hole making method of thin-walled honeycomb sandwich composite structural member
CN103240888A (en) * 2013-04-27 2013-08-14 哈尔滨飞机工业集团有限责任公司 Glass steel die positioning hole processing method
CN103586500A (en) * 2013-11-04 2014-02-19 中航成飞民用飞机有限责任公司 Hole making method for honeycomb interlayer composite materials

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109591334A (en) * 2018-10-12 2019-04-09 江西昌河航空工业有限公司 A kind of localization method of pair of honeycomb parts punching
CN109591334B (en) * 2018-10-12 2021-04-30 江西昌河航空工业有限公司 Positioning method for punching honeycomb part
CN112372924A (en) * 2020-10-14 2021-02-19 东风汽车集团有限公司 Hole making method of foaming sandwich structure

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RJ01 Rejection of invention patent application after publication

Application publication date: 20180525

RJ01 Rejection of invention patent application after publication