CN109605019A - Carrier rocket empennage glue riveting assembly technique - Google Patents
Carrier rocket empennage glue riveting assembly technique Download PDFInfo
- Publication number
- CN109605019A CN109605019A CN201811459894.5A CN201811459894A CN109605019A CN 109605019 A CN109605019 A CN 109605019A CN 201811459894 A CN201811459894 A CN 201811459894A CN 109605019 A CN109605019 A CN 109605019A
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- China
- Prior art keywords
- empennage
- face
- carrier rocket
- skeleton
- glue
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
Abstract
The present invention provides a kind of carrier rocket empennage glue riveting assembly techniques, this method is pre-installed on assembly jig into component by empennage part, and cellular cutting processing is completed with form using single, after part surface treated, rivet face secondary use type frame completes the riveting assembly of skeleton, and pumping nail face paste applies glue film and carries out pre- heat cure；Honeycomb is assembled in rivet facial bone frame, takes tacking form that pumping nail face is located by connecting therewith.After component assembles, by curing mold tire, component and the positioning of mould tire are fixed using type face and three-point fix mode, enter autoclave curing molding under vacuum, high temperature, condition of high voltage, and carry out online process monitoring, autoclave is removed after the completion of solidification, carries out riveting operation with other of furnace test piece intensity detection and pumping nail face.This method is by that can complete the riveting assembly of carrier rocket empennage, realize that the reliable bonding of sandwich, intensity index are met the requirements using tooling devices such as assembly jig, curing mold tire, autoclaves.
Description
Technical field
The present invention relates to carrier rocket empennage manufacturing technology fields, and in particular, to carrier rocket empennage glue is riveted allotment of labor
Process.Especially it is that by splicing molding, the riveting assembly method of Al-alloy metal panel and honeycomb sandwich construction part.
Background technique
Welding, riveting, splicing are the big interconnection techniques of carrier rocket three, and welding technique is commonly used in tank class product, riveting
Technology is chiefly used in semi-monocoque non-tight riveting bay section product, and adhesive bonding technique is chiefly used in the materials such as metal-metal, metal-non-metal
Connection between material.Important component one of of the empennage as carrier rocket, it is connect by three connectors with endpiece product, is risen
Balance whole rocket important function, the main connection type used is riveting and splicing.
Tail structure part is mainly made of covering, skeleton, honeycomb, and covering and honeycomb are using splicing connection, covering and skeleton
Using riveting；Due to structure open, covering is divided into rivet face and pumping nail face, and rivet face covering and skeleton are assembling
It is completed in type frame, pumping nail face covering completes assembly under frame.Skeleton includes the parts such as rib, beam, edge, using riveting, drill form
Connection.To guarantee empennage morpheme size, type face quality and glue-joint strength, assembling process needs to borrow assembly jig, solidification
The process equipments such as mould tire, autoclave cooperate through multiple processes such as riveting, surface treatment, splicing and complete.
Empennage process for making is extremely complex, therefore carrier rocket is basically divided into two classes both at home and abroad, first is that without empennage
Class, gesture stability are mainly realized by engine；One kind is that have empennage class, but only covering and skeleton, no honeycomb are right
Riveting intensity requires high.The empennage product assembled using glue, riveter skill, bonding strength is significantly due to hollow structure；To taking
For traditional semi-monocoque bay section, develops new generation's carrier rocket rocket body structure loss of weight and be of great significance.
Currently without the explanation or report for finding technology similar to the present invention, it is also not yet collected into money similar both at home and abroad
Material.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of carrier rocket empennage glue riveting assembly technology sides
Method.
A kind of carrier rocket empennage glue riveting assembly technique provided according to the present invention, comprising:
Step 1) empennage skeleton pre-assembled；
The processing of step 2) honeycomb and cleaning；
Step 3) surface treatment；
The assembly of step 4) rivet face, pumping nail face pre glued joint；
Step 5) rivet face pre glued joint, honeycomb assembly；
Step 6) takes out top surface tacking；
Step 7) empennage and curing mold tire assemble；
Step 8) solidification by cement；
The riveting in step 9) pumping nail face.
Preferably, in the step 1), empennage skeleton is pre-assembled on empennage assembly jig and carries out, assembly jig and solidification
Mould tire is coordinated using empennage exemplar.
Preferably, the cell dimensions size is singly matched one by one with the pre-assembled skeleton completed in step 1)；It is carried out when cleaning
Oil removal treatment, and dry at a set temperature.
Preferably, empennage part is handled using phosphoric acid anodised surfaces in the step 3), it is strong to improve splicing interface
Degree.
Preferably, tail structure is divided into two parts assembly in the step 4), and the rivet face containing skeleton is on assembly jig
All rivetings are completed, pumping nail face covering and glue film carry out pre glued joint.
Preferably, the rivet face in the step 5) containing skeleton is keeping skeleton set temperature item first with glue film pre glued joint
Honeycomb installation is carried out under part.
Preferably, pumping nail face and empennage skeleton are assembled using tacking form in the step 6), guarantee the company in pumping nail face
Connect hole after hardening with skeleton dislocation-free.
Preferably, the empennage component assembled in the step 7) guarantees molding surface size by curing mold tire, and according to tail
Wing structure feature carries out three-point fix, and curing mold fetalism face and empennage exemplar are coordinated.
Preferably, the solidification by cement of empennage carries out in autoclave in the step 8), and is solidified, and overall process carries out
Computer monitoring.
Preferably, in the step 9) pumping nail face be riveted on out autoclave after carry out.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, using method proposed by the present invention, the aerofoil profile product of honeycomb sandwich construction, intensity and size can be developed
It can be better than traditional riveting bay section, can effectively ensure that carrier rocket balance quality.
2, the present invention is by that can complete carrier rocket tail using tooling devices such as assembly jig, curing mold tire, autoclaves
The riveting of the wing is assembled, and realizes that the reliable bonding of sandwich, intensity index are met the requirements.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is the carrier rocket empennage glue riveting assembly technique flow chart of the embodiment of the present invention.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
A kind of carrier rocket empennage glue riveting assembly technique provided according to the present invention, comprising:
Step 1) empennage skeleton pre-assembled；
The processing of step 2) honeycomb and cleaning；
Step 3) surface treatment；
The assembly of step 4) rivet face, pumping nail face pre glued joint；
Step 5) rivet face pre glued joint, honeycomb assembly；
Step 6) takes out top surface tacking；
Step 7) empennage and curing mold tire assemble；
Step 8) solidification by cement；
The riveting in step 9) pumping nail face.
In the step 1), empennage skeleton is pre-assembled on empennage assembly jig and carries out, and assembly jig is adopted with curing mold tire
Coordinated with empennage exemplar.
The cell dimensions size is singly matched one by one with the pre-assembled skeleton completed in step 1)；It is carried out at oil removing when cleaning
Reason, and dry at a set temperature.
Empennage part is handled using phosphoric acid anodised surfaces in the step 3), to improve splicing boundary strength.
Tail structure is divided into two parts assembly in the step 4), and the rivet face containing skeleton is completed all on assembly jig
Riveting, pumping nail face covering and glue film carry out pre glued joint.
Rivet face in the step 5) containing skeleton carries out under the conditions of keeping skeleton set temperature first with glue film pre glued joint
Honeycomb installation.
Pumping nail face and empennage skeleton are assembled using tacking form in the step 6), guarantee the connecting hole in pumping nail face solid
After change with skeleton dislocation-free.
The empennage component assembled in the step 7) guarantees molding surface size by curing mold tire, and according to tail structure spy
Point carries out three-point fix, and curing mold fetalism face and empennage exemplar are coordinated.
The solidification by cement of empennage carries out in autoclave in the step 8), and is solidified, and overall process carries out computer
Monitoring.
In the step 9) pumping nail face be riveted on out autoclave after carry out.
More specifically, in the carrier rocket empennage glue riveting assembly technique, by empennage part in assembly jig
Upper prepackage completes cellular cutting processing with form at component, and using single, after part surface treated, rivet face secondary use
Type frame completes the riveting assembly of skeleton, and pumping nail face paste applies glue film and carries out pre- heat cure；Honeycomb is assembled in rivet facial bone frame, is taken
Pumping nail face is located by connecting by tacking form therewith.After component assembles, by curing mold tire, using type face and three-point fix
Mode fixes component and the positioning of mould tire, and is laid with insulating layer, arranges thermocouple and vacuum nozzle, is taken out into autoclave equipment
Vacuum, high temperature, high pressure are glued, and carry out online process monitoring, and autoclave is removed after the completion of solidification, examine with furnace test piece intensity
Other of survey and pumping nail face riveting operations.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of carrier rocket empennage glue riveting assembly technique characterized by comprising
Step 1) empennage skeleton pre-assembled；
The processing of step 2) honeycomb and cleaning；
Step 3) surface treatment；
The assembly of step 4) rivet face, pumping nail face pre glued joint；
Step 5) rivet face pre glued joint, honeycomb assembly；
Step 6) takes out top surface tacking；
Step 7) empennage and curing mold tire assemble；
Step 8) solidification by cement；
The riveting in step 9) pumping nail face.
2. carrier rocket empennage glue riveting assembly technique according to claim 1, which is characterized in that the step 1)
In, empennage skeleton is pre-assembled on empennage assembly jig and carries out, and assembly jig and curing mold tire are coordinated using empennage exemplar.
3. carrier rocket empennage glue riveting assembly technique according to claim 1, which is characterized in that the cell dimensions
Size is singly matched one by one with the pre-assembled skeleton completed in step 1)；Oil removal treatment is carried out when cleaning, and is dried at a set temperature.
4. carrier rocket empennage glue riveting assembly technique according to claim 1, which is characterized in that in the step 3)
Empennage part is handled using phosphoric acid anodised surfaces, to improve splicing boundary strength.
5. carrier rocket empennage glue riveting assembly technique according to claim 1, which is characterized in that in the step 4)
Tail structure is divided into two parts assembly, and the rivet face containing skeleton completes all to rivet on assembly jig, pumping nail face covering and glue
Film carries out pre glued joint.
6. carrier rocket empennage glue riveting assembly technique according to claim 1, which is characterized in that in the step 5)
Rivet face containing skeleton first with glue film pre glued joint, carries out honeycomb installation under the conditions of keeping skeleton set temperature.
7. carrier rocket empennage glue riveting assembly technique according to claim 1, which is characterized in that in the step 6)
Pumping nail face and empennage skeleton are assembled using tacking form, the connecting hole in guarantee pumping nail face after hardening with skeleton dislocation-free.
8. carrier rocket empennage glue riveting assembly technique according to claim 1, which is characterized in that in the step 7)
The empennage component assembled guarantees molding surface size by curing mold tire, and carries out three-point fix, solidification according to tail structure feature
Mould fetalism face and empennage exemplar are coordinated.
9. carrier rocket empennage glue riveting assembly technique according to claim 1, which is characterized in that in the step 8)
The solidification by cement of empennage carries out in autoclave, and is solidified, and overall process carries out computer monitoring.
10. carrier rocket empennage glue riveting assembly technique according to claim 1, which is characterized in that the step 9)
Middle pumping nail face be riveted on out autoclave after carry out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811459894.5A CN109605019B (en) | 2018-11-30 | 2018-11-30 | Glue riveting assembly process method for tail wing of carrier rocket |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811459894.5A CN109605019B (en) | 2018-11-30 | 2018-11-30 | Glue riveting assembly process method for tail wing of carrier rocket |
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| Publication Number | Publication Date |
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| CN109605019A true CN109605019A (en) | 2019-04-12 |
| CN109605019B CN109605019B (en) | 2020-01-10 |
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| CN201811459894.5A Active CN109605019B (en) | 2018-11-30 | 2018-11-30 | Glue riveting assembly process method for tail wing of carrier rocket |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111795721A (en) * | 2020-06-04 | 2020-10-20 | 成都飞机工业（集团）有限责任公司 | Real-time online detection method for autoclave curing data |
| CN113001125A (en) * | 2021-03-19 | 2021-06-22 | 沈阳万事达机械有限公司 | Process flow of empennage framework |
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| CN102225703A (en) * | 2011-04-12 | 2011-10-26 | 江西洪都航空工业集团有限责任公司 | Manufacturing method of integral glass fiber reinforced plastic unmanned aerial vehicle wing |
| CN104670491A (en) * | 2013-11-29 | 2015-06-03 | 空客直升机德国有限公司 | Shrouded Rotary Assembly From Segmented Composite For Aircraft |
| CN104943849A (en) * | 2015-05-07 | 2015-09-30 | 哈尔滨飞机工业集团有限责任公司 | Manufacturing method of aluminum skin honeycomb sandwich floor |
| CN105065393A (en) * | 2015-07-07 | 2015-11-18 | 奇瑞汽车股份有限公司 | Vehicle carbon fiber part assembling composition and mode |
| CN105437537A (en) * | 2015-12-08 | 2016-03-30 | 成都飞机设计研究所 | Assembling method for airfoil total composite transonic flutter model |
| CN107628232A (en) * | 2017-08-11 | 2018-01-26 | 精功（绍兴）复合材料技术研发有限公司 | A kind of composite unmanned airplane empennage and its manufacture method |
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2018
- 2018-11-30 CN CN201811459894.5A patent/CN109605019B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102225703A (en) * | 2011-04-12 | 2011-10-26 | 江西洪都航空工业集团有限责任公司 | Manufacturing method of integral glass fiber reinforced plastic unmanned aerial vehicle wing |
| CN104670491A (en) * | 2013-11-29 | 2015-06-03 | 空客直升机德国有限公司 | Shrouded Rotary Assembly From Segmented Composite For Aircraft |
| CN104943849A (en) * | 2015-05-07 | 2015-09-30 | 哈尔滨飞机工业集团有限责任公司 | Manufacturing method of aluminum skin honeycomb sandwich floor |
| CN105065393A (en) * | 2015-07-07 | 2015-11-18 | 奇瑞汽车股份有限公司 | Vehicle carbon fiber part assembling composition and mode |
| CN105437537A (en) * | 2015-12-08 | 2016-03-30 | 成都飞机设计研究所 | Assembling method for airfoil total composite transonic flutter model |
| CN107628232A (en) * | 2017-08-11 | 2018-01-26 | 精功（绍兴）复合材料技术研发有限公司 | A kind of composite unmanned airplane empennage and its manufacture method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111795721A (en) * | 2020-06-04 | 2020-10-20 | 成都飞机工业（集团）有限责任公司 | Real-time online detection method for autoclave curing data |
| CN113001125A (en) * | 2021-03-19 | 2021-06-22 | 沈阳万事达机械有限公司 | Process flow of empennage framework |
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| Publication number | Publication date |
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| CN109605019B (en) | 2020-01-10 |
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| CB03 | Change of inventor or designer information |
Inventor after: Liang Ying Inventor after: Que Wenjun Inventor after: Zhang Shen Inventor after: Wang Liang Inventor after: Wu Minjun Inventor after: Hu Xu Inventor after: Gu Chen Inventor before: Liang Ying Inventor before: Kan Wenjun Inventor before: Zhang Shen Inventor before: Wang Liang Inventor before: Wu Minjun Inventor before: Hu Xu Inventor before: Gu Chen |
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