CN105173109A - Repairing method for honeycomb sandwich structure - Google Patents
Repairing method for honeycomb sandwich structure Download PDFInfo
- Publication number
- CN105173109A CN105173109A CN201410249812.XA CN201410249812A CN105173109A CN 105173109 A CN105173109 A CN 105173109A CN 201410249812 A CN201410249812 A CN 201410249812A CN 105173109 A CN105173109 A CN 105173109A
- Authority
- CN
- China
- Prior art keywords
- honeycomb
- laying
- sandwich construction
- repaired
- repair method
- 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
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
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/04—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements
- B29C73/10—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements using patches sealing on the surface of the article
Abstract
The invention belongs to the aircraft maintenance technology, and particularly relates to a repairing method for a honeycomb sandwich structure. The repairing method includes the steps that firstly, a placement layer and a honeycomb at the damaged portion are ground away, and a lower panel can not be damaged; secondly, a new honeycomb is prepared, and the surface of the honeycomb is glued; thirdly, the honeycomb is put in a cavity of the original honeycomb after being processed; and finally, placement layer replacement is carried out according to the original placement layer. Prepreg, glue film and glass cloth can not be spliced but in seamless butt joint. When the repaired structure is a surface concave as shown, the pneumatic outline can be repaired through filler. Raw materials are used for replacing the honeycomb and the placement layer, and the placement layer is repaired through a wet method. The strength design requirement is met, the structural weight after repairing is reduced, and good compatibility can be kept.
Description
Technical field
The invention belongs to aircraft repair or reworking techniques, be specifically related to a kind of honeycomb sandwich construction repair method, be only applicable to part in the damage manufactured and occur in fitting process, be not suitable for the part just under arms repaired at repair plant.
Background technology
Honeycomb sandwich construction is widely used on aircraft skin and fairing, under the prerequisite not improving weight, effectively can improve rigidity, ensures aerodynamic configuration.
When aircraft cellular sandwich structure needs to be serviced repairing, general taking-up defect honeycomb, then uses 17# filler (ECS2010.10) to replace, however due to filler weight larger, after making to repair, framing member weightening finish is more, thus have impact on the in-use performance of part.Need a kind of new repair method to alleviate the structural weight after repairing for this reason, meet requirement of strength design simultaneously.
Summary of the invention
The object of the invention is: provide a kind of and can meet the requirement of strength design after maintenance, can avoid again repairing the honeycomb sandwich construction method for maintaining that rear structural weight strengthens.
Technical scheme of the present invention: a kind of honeycomb sandwich construction repair method, its detailed process is as follows:
Step 1: remove laying and damage honeycomb
The laying of damaged part and honeycomb are polished off, does not damage lower faceplate;
Step 2: material prepares and process
Prepare the material that honeycomb sandwich construction REPSH repair shop needs: prepreg, glued membrane, honeycomb, dry laying, and certain process is carried out to former part and new material;
Step 3: honeycomb is replaced
When replacing honeycomb, cellular direction must be checked, and it is consistent with original cellular direction to ensure to replace honeycomb, places new honeycomb core after treatment in the cavity of original honeycomb;
Step 4: laying is replaced
Prepreg, glued membrane and glass woven fabric do not allow splicing, answer gapless to dock, and carry out laying replace Post RDBMS by former laying, and when repairing structure is shown as surface indentation, aerodynamic configuration is repaired in available filler agent.
1, laying and the corresponding milling tools polishing of honeycomb are removed, and can not damage lower faceplate.
2, cleaning agent should be used to carry out surface treatment before laying is replaced, and must be removed priming paint and primer by the region of repairing, periphery exceeds 50 millimeters, the laying region that will replace.
When 3, changing honeycomb, cellular direction must be checked, and it is consistent with original cellular direction to ensure to replace honeycomb, can select scheme more suitable in two schemes as required.
4, prepreg, glued membrane and glass woven fabric do not allow splicing, answer gapless to dock, and before laying is replaced in placement, answer lay one deck adhesive film.
Beneficial effect of the present invention: reduce the structural weight after repairing, improves the in-use performance of part.
Accompanying drawing explanation
Fig. 1 is the schematic diagram that the present invention removes damage honeycomb and laying;
Honeycomb alternative 1):
Fig. 2 is that schematic diagram replaced by honeycomb;
Fig. 3 is honeycomb seal schematic diagram;
Fig. 4 is that laying replaces schematic diagram.
Honeycomb alternative 2):
Fig. 5 is that schematic diagram replaced by honeycomb;
Fig. 6 is honeycomb seal schematic diagram;
Fig. 7 is that laying replaces schematic diagram.
Wherein, 1-honeycomb, 2-expansion glue, 3-pasty state glue, 4-glued membrane, 5-prepreg cloth.
Detailed description of the invention
Below in conjunction with drawings and Examples, the invention will be further described:
A kind of its principle of honeycomb sandwich construction repair method is
Below in conjunction with Fig. 1, Fig. 2 and Fig. 3, conduct further description the specific implementation process of honeycomb sandwich construction repair method of the present invention, its detailed process is as follows:
Step 1: remove laying and damage honeycomb
The laying of removing plane or slightly appearing areas uses with the pneumatic milling tools of 60 granularity emery disc, and then the manual sand papering by about 320 granularities completes this operation; Behind laying place to go, honeycomb must use pneumatic polishing place to go, until near the 0.5-1 millimeter place of honeycomb lower faceplate.Usually this region is glued membrane; Remaining honeycomb must use No. 150 sand paper or thinner craft or automatically grinding, does not carefully damage laying.
Step 2: material prepares and process
Prepare the material that honeycomb sandwich construction REPSH repair shop needs: prepreg, glued membrane, honeycomb, dry laying.New honeycomb cutting, machine add to be undertaken by corresponding regulation and stipulation with cleaning operation.Unless repaired instruction special stipulation, alcohol (Z-23.113) or butanone (Z-23.117) are as general cleaning solvent, when preparing before composite material surface glueds joint or prepreg overlay prepares, use straight ethanol (Z-23.933) or pure butanone (Z-23.934).Phozy cleaning cloth (Z-23.930) should be used during cleaning to dip in solvent, and the wiping of replacing cleaning cloth and repetition continually, until do not have dust, after having operated, uses clean dry cloth wiping, evaporates become dry to prevent solvent.Must be removed priming paint and primer by the region of repairing, periphery exceeds 50 millimeters, the laying region that will replace.
Step 3: honeycomb is replaced
When replacing honeycomb, cellular direction must be checked, and it is consistent with original cellular direction to ensure to replace honeycomb, new honeycomb core is placed in the cavity of original honeycomb after following process, scheme 1) when original honeycomb with when replacing honeycomb splicing, use expansion glue Z-15.415, glued membrane must be placed between the covering of bonding pad and honeycomb, and expansion glued membrane is placed on the bonding pad between new honeycomb and original honeycomb.The periphery of new honeycomb must contact original honeycomb, maximum permissible clearance 0.6 millimeter.Scheme 2), as shown in Fig. 5, Fig. 6, Fig. 7, when the honeycomb of original honeycomb and replacement uses pasty state glue Z-15.262 in bonding pad, this glue should be applied to skin panel and original honeycomb surface, and the surface of new honeycomb.Necessary close installation, can not leave gap between honeycomb.Honeycomb need carry out encapsulation process, makes pasty state glue enter in honeycomb hole, keeps concordant with honeycomb after solidification with sand papering glue.
Step 4: laying is replaced
Prepreg, glued membrane and glass woven fabric do not allow splicing, answer gapless to dock, and before laying is replaced in placement, answer lay one deck adhesive film; According to different repairing types, select different glue.Glued membrane exceedes repairs at least 5 millimeters, layer border.Cold compaction should be carried out, to compress laying.Adopt wet lamination, carry out the dipping of dry cloth, after dipping, material carries out laying replacement by former laying, prepares vacuum bag and vacuumizes and complete solidification.When repairing structure is shown as surface indentation, aerodynamic configuration is repaired in available filler agent.
The present invention adopts raw MAT'L replace honeycomb and laying and repair with wet lamination, requirement of strength design can be met, alleviate again the structural weight after repairing, good compatibility can be kept again, largely improve the in-use performance of part compared with former repair method.
Claims (5)
1. a honeycomb sandwich construction repair method, is characterized in that, detailed process is as follows:
Step 1: remove laying and damage honeycomb
The laying of damaged part and honeycomb are polished off, does not damage lower faceplate;
Step 2: material prepares and process
Prepare the material that honeycomb sandwich construction REPSH repair shop needs: prepreg, glued membrane, honeycomb, dry laying, and certain process is carried out to former part and new material;
Step 3: honeycomb is replaced
When replacing honeycomb, cellular direction must be checked, and it is consistent with original cellular direction to ensure to replace honeycomb, places new honeycomb core after treatment in the cavity of original honeycomb;
Step 4: laying is replaced
Prepreg, glued membrane and glass woven fabric do not allow splicing, answer gapless to dock, and carry out laying replace Post RDBMS by former laying, and when repairing structure is shown as surface indentation, aerodynamic configuration is repaired in available filler agent.
2. honeycomb sandwich construction repair method according to claim 1, is characterized in that, laying and honeycomb polishing are removed, and avoid damaging lower faceplate.
3. honeycomb sandwich construction repair method according to claim 2, is characterized in that, cleaning agent should be used to carry out surface treatment before laying is replaced, and removes by the priming paint in region repaired and primer, and periphery exceeds 50 millimeters, the laying region that will replace.
4. honeycomb sandwich construction repair method according to claim 3, is characterized in that, when replacing honeycomb, must check cellular direction, and it is consistent with original cellular direction to ensure to replace honeycomb.
5. honeycomb sandwich construction repair method according to claim 4, is characterized in that, prepreg, glued membrane and glass woven fabric do not allow splicing, answer gapless to dock, and before laying is replaced in placement, answers lay one deck adhesive film.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410249812.XA CN105173109A (en) | 2014-06-06 | 2014-06-06 | Repairing method for honeycomb sandwich structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410249812.XA CN105173109A (en) | 2014-06-06 | 2014-06-06 | Repairing method for honeycomb sandwich structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105173109A true CN105173109A (en) | 2015-12-23 |
Family
ID=54895692
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410249812.XA Pending CN105173109A (en) | 2014-06-06 | 2014-06-06 | Repairing method for honeycomb sandwich structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105173109A (en) |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275499A (en) * | 2016-08-22 | 2017-01-04 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Anti-corrosion design method at aircaft configuration dead angle |
| CN106628240A (en) * | 2016-12-14 | 2017-05-10 | 中航通飞研究院有限公司 | Repairing method of airplane composite material foam interlayer structure |
| CN106863856A (en) * | 2017-02-08 | 2017-06-20 | 湖南博翔新材料有限公司 | A kind of method for repairing and mending of PE armours |
| CN107512403A (en) * | 2017-09-30 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft outfield honeycomb panel is come unglued repair method |
| CN107856331A (en) * | 2016-09-22 | 2018-03-30 | 成都飞机工业（集团）有限责任公司 | A kind of repair method of big thickness composite material parts defect |
| CN109649679A (en) * | 2018-10-15 | 2019-04-19 | 西北工业大学 | Plate repair method |
| CN109834748A (en) * | 2017-11-29 | 2019-06-04 | 波音公司 | The structure of honeycomb core material panel is rebuild |
| CN110154495A (en) * | 2019-05-21 | 2019-08-23 | 安徽佳力奇碳纤维科技股份公司 | A kind of honeycomb core sag compensation method |
| CN110182383A (en) * | 2019-05-17 | 2019-08-30 | 陕西飞机工业（集团）有限公司 | A kind of solution of metal skin sandwich part covering bulge failure |
| CN110573328A (en) * | 2017-05-01 | 2019-12-13 | 赫克赛尔公司 | plugged sound insulation honeycomb |
| CN110561796A (en) * | 2019-09-19 | 2019-12-13 | 哈尔滨哈飞航空工业有限责任公司 | Reinforcing and repairing method for damaged composite material blade skin |
| CN110962377A (en) * | 2018-09-28 | 2020-04-07 | 成都飞机工业（集团）有限责任公司 | Honeycomb sandwich structure part repairing method capable of reducing structure loss |
| CN110978712A (en) * | 2019-11-28 | 2020-04-10 | 上海绚丽包装彩印有限公司 | Multilayer corrugated container board |
| CN112026207A (en) * | 2020-08-03 | 2020-12-04 | 国营芜湖机械厂 | Method for repairing damage of composite aramid fiber paper honeycomb core in outfield low-temperature environment |
| CN112140596A (en) * | 2020-09-25 | 2020-12-29 | 中国直升机设计研究所 | Honeycomb sandwich structure penetrating damage repairing method |
| CN112743880A (en) * | 2020-12-11 | 2021-05-04 | 哈尔滨飞机工业集团有限责任公司 | Repairing method for large-area damage of honeycomb sandwich structural member |
| CN113478946A (en) * | 2021-07-12 | 2021-10-08 | 重庆泛锐科技有限公司 | Repairing method of sandwich composite material plate |
| CN114013170A (en) * | 2021-10-22 | 2022-02-08 | 中车工业研究院有限公司 | Damage repairing method for honeycomb sandwich structure composite material |
| CN114986948A (en) * | 2021-03-01 | 2022-09-02 | 中国航发商用航空发动机有限责任公司 | Repairing process and method for composite material honeycomb sandwich structure |
| CN115091795A (en) * | 2022-05-31 | 2022-09-23 | 国营芜湖机械厂 | Repairing method for metal honeycomb sandwich structural member composite material by patching, gluing and repairing |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7069830B1 (en) * | 2000-06-19 | 2006-07-04 | The United States Of America As Represented By The Secretary Of The Air Force | Surface repair method and tool therefor |
| CN102086961A (en) * | 2010-11-26 | 2011-06-08 | 北京空间机电研究所 | Process for manufacturing flexible honeycomb sandwich structure |
-
2014
- 2014-06-06 CN CN201410249812.XA patent/CN105173109A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7069830B1 (en) * | 2000-06-19 | 2006-07-04 | The United States Of America As Represented By The Secretary Of The Air Force | Surface repair method and tool therefor |
| CN102086961A (en) * | 2010-11-26 | 2011-06-08 | 北京空间机电研究所 | Process for manufacturing flexible honeycomb sandwich structure |
Non-Patent Citations (2)
| Title |
|---|
| 孔娇月等: "复合材料胶接修理工艺过程及其影响因素", 《航空制造技术》 * |
| 王晓澎: "热补仪在复合材料部件湿法修理中的应用", 《航空制造技术》 * |
Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275499A (en) * | 2016-08-22 | 2017-01-04 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Anti-corrosion design method at aircaft configuration dead angle |
| CN106275499B (en) * | 2016-08-22 | 2018-07-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Anti-corrosion design method at aircaft configuration dead angle |
| CN107856331A (en) * | 2016-09-22 | 2018-03-30 | 成都飞机工业（集团）有限责任公司 | A kind of repair method of big thickness composite material parts defect |
| CN106628240A (en) * | 2016-12-14 | 2017-05-10 | 中航通飞研究院有限公司 | Repairing method of airplane composite material foam interlayer structure |
| CN106863856A (en) * | 2017-02-08 | 2017-06-20 | 湖南博翔新材料有限公司 | A kind of method for repairing and mending of PE armours |
| CN106863856B (en) * | 2017-02-08 | 2019-04-09 | 湖南博翔新材料有限公司 | A kind of method for repairing and mending of PE armour |
| CN110573328A (en) * | 2017-05-01 | 2019-12-13 | 赫克赛尔公司 | plugged sound insulation honeycomb |
| CN107512403A (en) * | 2017-09-30 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft outfield honeycomb panel is come unglued repair method |
| CN109834748A (en) * | 2017-11-29 | 2019-06-04 | 波音公司 | The structure of honeycomb core material panel is rebuild |
| CN109834748B (en) * | 2017-11-29 | 2022-05-10 | 波音公司 | Structural rework of honeycomb core panel |
| CN110962377A (en) * | 2018-09-28 | 2020-04-07 | 成都飞机工业（集团）有限责任公司 | Honeycomb sandwich structure part repairing method capable of reducing structure loss |
| CN109649679A (en) * | 2018-10-15 | 2019-04-19 | 西北工业大学 | Plate repair method |
| CN110182383A (en) * | 2019-05-17 | 2019-08-30 | 陕西飞机工业（集团）有限公司 | A kind of solution of metal skin sandwich part covering bulge failure |
| CN110154495A (en) * | 2019-05-21 | 2019-08-23 | 安徽佳力奇碳纤维科技股份公司 | A kind of honeycomb core sag compensation method |
| CN110561796A (en) * | 2019-09-19 | 2019-12-13 | 哈尔滨哈飞航空工业有限责任公司 | Reinforcing and repairing method for damaged composite material blade skin |
| CN110561796B (en) * | 2019-09-19 | 2021-08-03 | 哈尔滨哈飞航空工业有限责任公司 | Reinforcing and repairing method for damaged composite material blade skin |
| CN110978712A (en) * | 2019-11-28 | 2020-04-10 | 上海绚丽包装彩印有限公司 | Multilayer corrugated container board |
| CN112026207A (en) * | 2020-08-03 | 2020-12-04 | 国营芜湖机械厂 | Method for repairing damage of composite aramid fiber paper honeycomb core in outfield low-temperature environment |
| CN112140596A (en) * | 2020-09-25 | 2020-12-29 | 中国直升机设计研究所 | Honeycomb sandwich structure penetrating damage repairing method |
| CN112743880A (en) * | 2020-12-11 | 2021-05-04 | 哈尔滨飞机工业集团有限责任公司 | Repairing method for large-area damage of honeycomb sandwich structural member |
| CN114986948A (en) * | 2021-03-01 | 2022-09-02 | 中国航发商用航空发动机有限责任公司 | Repairing process and method for composite material honeycomb sandwich structure |
| CN114986948B (en) * | 2021-03-01 | 2023-06-02 | 中国航发商用航空发动机有限责任公司 | Repair process and method for honeycomb sandwich structure of composite material |
| CN113478946A (en) * | 2021-07-12 | 2021-10-08 | 重庆泛锐科技有限公司 | Repairing method of sandwich composite material plate |
| CN114013170A (en) * | 2021-10-22 | 2022-02-08 | 中车工业研究院有限公司 | Damage repairing method for honeycomb sandwich structure composite material |
| CN114013170B (en) * | 2021-10-22 | 2024-03-22 | 中车工业研究院有限公司 | Damage repairing method for honeycomb sandwich structure composite material |
| CN115091795A (en) * | 2022-05-31 | 2022-09-23 | 国营芜湖机械厂 | Repairing method for metal honeycomb sandwich structural member composite material by patching, gluing and repairing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105173109A (en) | Repairing method for honeycomb sandwich structure | |
| US10850460B2 (en) | Processes for repairing complex laminating composites | |
| CN109514891B (en) | High-temperature glue repairing method for inner surface of composite material culvert casing | |
| CN108437497B (en) | Typical damage repair process for reverse thrust grid of engine | |
| CN112026207A (en) | Method for repairing damage of composite aramid fiber paper honeycomb core in outfield low-temperature environment | |
| CN103231464A (en) | Honeycomb preforming method for large-curvature composite material interlayer piece | |
| CN104741864A (en) | Fast repair method for structural damage | |
| CN106903899A (en) | A kind of wind wheel blade web cemented in place installation method | |
| CN104691779A (en) | Process method for replacement and repair of iron clad of main blade made of composite material | |
| CN108656417B (en) | Coating method of wind power blade surface coating | |
| CN105730715B (en) | A kind of repair method of composite wing flap local damage | |
| CN113146142A (en) | Device and method for rapidly repairing cracks on hole edge of metal skin of airplane by using composite material | |
| CN113734462B (en) | Skin maintenance method for sports aircraft | |
| CN101915222B (en) | Method for repairing cracks of blade adhesive | |
| CN113103834B (en) | Method for repairing aerocar component | |
| CN103523116A (en) | Method for covering top of passenger car | |
| CN105538753A (en) | Repairing method for paper honeycomb sandwich structure | |
| CN110497630B (en) | Method for repairing bulge defect on surface of heat insulation layer of solid rocket engine shell | |
| CN109049753A (en) | A kind of preparation method of heat-resisting nose cone | |
| CN116373358A (en) | Repairing method of carbon fiber composite material | |
| CN112014473A (en) | Wet-process glue-joint repairing method for solving cracks of complex metal profile structure of airplane | |
| CN102179938B (en) | Bonding reinforcement process for rear edge of wind turbine blade | |
| CN113942249A (en) | Method for repairing woven texture of carbon fiber composite material appearance | |
| CN105643318A (en) | Honeycomb material machining clamping method | |
| CN113511346A (en) | Method for repairing composite material of general airplane and method for repairing damaged, unfilled corner and foreign body part |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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 |
Application publication date: 20151223 |
|
| WD01 | Invention patent application deemed withdrawn after publication |