CN106828879A - A kind of composite jointing - Google Patents
A kind of composite jointing Download PDFInfo
- Publication number
- CN106828879A CN106828879A CN201510895337.8A CN201510895337A CN106828879A CN 106828879 A CN106828879 A CN 106828879A CN 201510895337 A CN201510895337 A CN 201510895337A CN 106828879 A CN106828879 A CN 106828879A
- Authority
- CN
- China
- Prior art keywords
- jointing
- rudder face
- joint
- composite
- rudder
- 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
- 239000002131 composite material Substances 0.000 title claims abstract description 21
- 239000002184 metal Substances 0.000 claims abstract description 11
- 229910052751 metal Inorganic materials 0.000 claims abstract description 11
- 210000005069 ears Anatomy 0.000 claims abstract 3
- 239000000463 material Substances 0.000 claims description 6
- 150000002739 metals Chemical class 0.000 abstract 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000007665 sagging Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
The invention belongs to field of airplane structure, it is related to the improvement to aircraft rudder surface jointing, it is a band dismountable composite ears joint of bushing.It is characterized in that：Dismountable composite rudder face jointing 1, joint two ends Bonding Metals bushing 2, the system of rudder face covering 3 is sunk, and gap, rudder face jointing 1 is connected by plate nut with rudder face covering 3.Present invention composite jointing instead of metal jointing, and rudder face leading edge profile is ensure that well, and a few font joints of indent make joint be located at before spindle central, reduce rudder balance weight.
Description
Technical field
Patent of the present invention is a kind of composite jointing
Background technology
The rudder face of general aircraft uses the composite structure, rudder face jointing to have with composite rudder face frequently with metal joint, metal joint
The stress that couple corrosion problem and thermal expansion cause, influences structural fatigue and life-span.And metal joint is typically using the connected mode of concentrated force, rudder
Face must have respective beam, rib reinforcement structure, and skins front edges profile must correction of the flank shape or gap, the influence pneumatic property of rudder face leading edge for the connection of metalwork
Energy.And metal joint has certain altitude, joint is located at behind shaft centerline, and rotating shaft leading portion must increase more balance weights.
The content of the invention
Not enough for rudder face jointing, patent of the present invention uses composite jointing, and joint is several font structures of indent, on joint
Bushing mounting holes are provided with, metal lining is glued onto on multiple material joint, the perpendicularity of bush end face and axially bored line, rudder face covering upper shed are ensured during splicing
System is sagging, and composite joint is connected by plate nut with rudder face covering, and joint is used and is connected with rudder face covering distribution, only needs local adding
The skin thickness in strong ties area.This joint ensure that rudder face profile, and the requirement of joint rigging position well, improve joint connection lifetime
And connection reliability.Joint is located at before spindle central, reduce rudder balance weight.
In order to solve the above-mentioned technical problem, the technical scheme of patent use of the present invention is：Composite jointing is molded by formpiston paving,
Bushing mounting holes are made on mould, the demoulding, Bonding Metal bushing outputs joint mounting hole on rudder face, with plate nut by joint and rudder face covering
Connection.
For prior art, the beneficial effect of patent of the present invention is：Mitigate rudder balance weight, it is to avoid metal is connected one with composite
Series of problems, improves the reliability of connection, and rudder face leading edge profile is ensure that well.
Brief description of the drawings
Fig. 1 is composite joint schematic diagram；Fig. 2 is composite joint cut away view；
Fig. 3 is composite joint schematic view of the mounting position
1 is composite rudder face jointing in figure, and 2 is that metal lining 3 is rudder face covering
Specific embodiment
The specific embodiment of patent of the present invention is further illustrated below in conjunction with the accompanying drawings.Based on the implementation method in the present invention, the common skill in this area
All other implementation that art personnel are obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
Refer to shown in Fig. 1 to Fig. 3, composite joint perforate is made on 3, an entirety is assembled into by splicing by 2 and 1, then
1 and 2 splicing assembly parts are connected by plate nut with 3.
Claims (2)
1. a kind of composite jointing, including composite rudder face jointing, metal lining, rudder face covering, its feature exists
In：Composite jointing is a few shape ears structures, and bushing mounting holes are provided with ears, and bushing is glued onto multiple material jointing
On, multiple material jointing profile is consistent with rudder face skin shape, is connected with rudder face covering by plate nut, can in fact answer material and now connect
Joint is changed.
2. the composite jointing according to right 1, it is characterised in that：Multiple material jointing is molded using formpiston paving, multiple
Material jointing bushing perforate is made on mould, rudder face covering upper shed, ensures that end face is vertical with hole center when two bushings are glued
Degree.This joint ensure that rudder face leading edge profile, and the requirement of joint rigging position well, improve joint connection lifetime and company
Connect reliability.Joint is located at before spindle central, reduce rudder balance weight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510895337.8A CN106828879A (en) | 2015-12-07 | 2015-12-07 | A kind of composite jointing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510895337.8A CN106828879A (en) | 2015-12-07 | 2015-12-07 | A kind of composite jointing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106828879A true CN106828879A (en) | 2017-06-13 |
Family
ID=59152010
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510895337.8A Pending CN106828879A (en) | 2015-12-07 | 2015-12-07 | A kind of composite jointing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106828879A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111452990A (en) * | 2019-01-20 | 2020-07-28 | 成都飞机工业（集团）有限责任公司 | Gluing positioning method for control surface of composite material airplane with multiple joints |
| CN111452991A (en) * | 2019-01-20 | 2020-07-28 | 成都飞机工业（集团）有限责任公司 | Gluing positioning method for control surface of composite material airplane with multiple joints |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202593868U (en) * | 2012-05-11 | 2012-12-12 | 中国航空工业集团公司西安飞机设计研究所 | Flutter model structure of movable surface |
| CN103538715A (en) * | 2013-10-14 | 2014-01-29 | 航天特种材料及工艺技术研究所 | Composite material pi-type lug interface and integral co-curing forming method |
| CN103552681A (en) * | 2013-11-19 | 2014-02-05 | 中国科学院宁波材料技术与工程研究所 | Composite material joint lug and preparation method thereof |
| CN104802982A (en) * | 2015-04-22 | 2015-07-29 | 北京航空航天大学 | Three-dimensional weaving composite integrally-formed rotor wing blade and manufacturing method thereof |
-
2015
- 2015-12-07 CN CN201510895337.8A patent/CN106828879A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202593868U (en) * | 2012-05-11 | 2012-12-12 | 中国航空工业集团公司西安飞机设计研究所 | Flutter model structure of movable surface |
| CN103538715A (en) * | 2013-10-14 | 2014-01-29 | 航天特种材料及工艺技术研究所 | Composite material pi-type lug interface and integral co-curing forming method |
| CN103552681A (en) * | 2013-11-19 | 2014-02-05 | 中国科学院宁波材料技术与工程研究所 | Composite material joint lug and preparation method thereof |
| CN104802982A (en) * | 2015-04-22 | 2015-07-29 | 北京航空航天大学 | Three-dimensional weaving composite integrally-formed rotor wing blade and manufacturing method thereof |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111452990A (en) * | 2019-01-20 | 2020-07-28 | 成都飞机工业（集团）有限责任公司 | Gluing positioning method for control surface of composite material airplane with multiple joints |
| CN111452991A (en) * | 2019-01-20 | 2020-07-28 | 成都飞机工业（集团）有限责任公司 | Gluing positioning method for control surface of composite material airplane with multiple joints |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for 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: 20170613 |