CN108621056A - Aircraft pipe fitting joint installs auxiliary mould - Google Patents
Aircraft pipe fitting joint installs auxiliary mould Download PDFInfo
- Publication number
- CN108621056A CN108621056A CN201810638564.6A CN201810638564A CN108621056A CN 108621056 A CN108621056 A CN 108621056A CN 201810638564 A CN201810638564 A CN 201810638564A CN 108621056 A CN108621056 A CN 108621056A
- Authority
- CN
- China
- Prior art keywords
- pipe fitting
- fitting joint
- link block
- aircraft
- screw rod
- 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
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
Abstract
The invention discloses a kind of aircraft pipe fitting joints to install auxiliary mould, include for playing the link block of position-limiting action to pipe fitting joint in the axial direction and being the screw rod that is threadedly coupled and may pass through the mounting hole being arranged on aircraft skin with link block, exhaust joint is sheathed on screw rod and exhaust joint is matched for clamping tightly by screw rod and link block.The aircraft pipe fitting joint of the present invention installs auxiliary mould, it can ensure that pipe fitting joint can be positioned fast and accurately when pipe fitting joint is assembled with aircraft skin, the setting angle and quality of pipe fitting joint is also ensured in the installation effectiveness for improving pipe fitting joint and aircraft skin.
Description
Technical field
The invention belongs to General Aviation technical field of auxiliary equipment, specifically, the present invention relates to a kind of aircraft pipe fittings to connect
Head installation auxiliary mould.
Background technology
It needs that multiple pipe fitting joints are arranged on aircraft skin, is respectively used to and dynamic and static pressure system, the aerating system on aircraft
It is attached with drainage.When pipe fitting joint is installed, the trepanning on aircraft skin, pipe fitting joint is needed generally to use cementing
Mode is installed on aircraft skin, does not have any rivet or screw in aircraft outer surface in this way, increases aesthetics.But it is adopting
When pipe fitting joint being installed with bonding mode, needs operator to be positioned manually to pipe fitting joint, pipe fitting joint can be caused in this way
Setting angle and quality can not ensure, and installation effectiveness is low.
Invention content
The present invention is directed at least solve one of the technical problems existing in the prior art.For this purpose, the present invention provides a kind of fly
Machine pipe fitting joint installs auxiliary mould, it is therefore an objective to improve the installation effectiveness of pipe fitting joint and aircraft skin.
To achieve the goals above, the technical solution that the present invention takes is：Aircraft pipe fitting joint installs auxiliary mould, including
For playing the link block of position-limiting action to pipe fitting joint in the axial direction and being to be threadedly coupled and may pass through aircraft skin with link block
The screw rod of the mounting hole of upper setting, exhaust joint is sheathed on screw rod and exhaust joint is matched for clamping tightly by screw rod and link block.
The link block is equipped with the protective pad contacted for the outer surface with aircraft skin, and protective pad uses softwood matter system
At link block is located at the outside of aircraft skin.
The material of the protective pad is rubber.
The protective pad is cirque structure, and protective pad is coaxial arrangement with the screw rod.
The link block is cylinder, and internal thread hole, link block and the screw coaxial are equipped at the center of link block.
The screw rod includes the flange set gradually in an axial direction, optical axis section and thread segment, and thread segment is with the link block
It is threadedly coupled and thread segment is equipped with external screw thread.
The flange and the optical axis section are cylinder, and the diameter of flange is more than the diameter of the diameter of optical axis section and flange not
More than the diameter of the mounting hole on the aircraft skin, the diameter of flange is more than the diameter of the centre bore of pipe fitting joint.
The aircraft pipe fitting joint of the present invention installs auxiliary mould, can be true when pipe fitting joint is assembled with aircraft skin
Protecting pipe fitting joint can fast and accurately be positioned, and the installation effectiveness of pipe fitting joint and aircraft skin is improved, can also be true
Protect the setting angle and quality of pipe fitting joint.
Description of the drawings
This specification includes the following drawings, and shown content is respectively：
Fig. 1 is the structural schematic diagram of aircraft pipe fitting joint installation auxiliary mould of the present invention；
Fig. 2 is the use state diagram of aircraft pipe fitting joint installation auxiliary mould of the present invention；
In figure label for：1, protective pad；2, link block；3, screw rod；301, flange；302, optical axis section；303, thread segment；4、
Pipe fitting joint；5, aircraft skin.
Specific implementation mode
Below against attached drawing, by the description of the embodiment, making to the specific implementation mode of the present invention further details of
Explanation, it is therefore an objective to those skilled in the art be helped to have more complete, accurate and deep reason to the design of the present invention, technical solution
Solution, and contribute to its implementation.
As depicted in figs. 1 and 2, the present invention provides a kind of aircraft pipe fitting joints to install auxiliary mould, including is used in axis
The link block 2 of position-limiting action is played to pipe fitting joint upwards and is arranged on aircraft skin to be threadedly coupled and may pass through with link block 2
Mounting hole screw rod 3, exhaust joint is sheathed on screw rod 3 and exhaust joint is matched for clamping tightly by screw rod 3 and link block 2.
Specifically, as shown in Fig. 2, pipe fitting joint and aircraft skin are by adhesive bonding connection, on aircraft skin
The mounting hole of setting is circular through hole, needs that multiple pipe fitting joints are arranged on aircraft skin, correspondingly, being provided on aircraft skin
With the mounting hole of pipe fitting joint equivalent amount, each pipe fitting joint is inserted into a mounting hole and is installed respectively.Pipe fitting joint
For both ends open and the cylinder of inner hollow, the diameter phase of the overall diameter of pipe fitting joint and the mounting hole on aircraft skin
Together, the centre bore of pipe fitting joint is circular hole, and pipe fitting joint is by dynamic and static pressure system, aerating system or the row on hose and aircraft
Dirty system connection so that dynamic and static pressure system, aerating system or the drainage on aircraft and atmosphere.In pipe fitting joint and fly
After machine covering is adhesively fixed, one end of pipe fitting joint is located in the mounting hole on aircraft skin and the end of pipe fitting joint and aircraft
The rest part of covering bonding connection, pipe fitting joint is inserted into inside and the partial insertion hose of pipe fitting joint of aircraft, is kept away
Exempt from the outside for being exposed to aircraft and influence the aesthetics of aircraft, while also ensuring that and being connect with hose reliably.
As depicted in figs. 1 and 2, the material of link block 2 is metal, in use, link block 2 is located at the outside of aircraft skin,
Link block 2 is equipped with the protective pad 1 contacted for the outer surface with aircraft skin, and protective pad 1 is made of softwood matter, link block
2 do not contact with aircraft skin, avoid causing to damage to aircraft skin, it is ensured that product quality.Protective pad 1 is Nian Jie with link block 2
Connection, protective pad 1 is fixedly connected integrally with link block 2, in use, protective pad 1 is clipped between link block 2 and aircraft skin.
Preferably, the material of protective pad 1 is rubber.As depicted in figs. 1 and 2, protective pad 1 is cirque structure, is prevented
Protection pad 1 is coaxial arrangement with screw rod 3, and the diameter of protective pad 1 is more than the diameter of screw rod 3, and the diameter of protective pad 1 is covered also greater than aircraft
The diameter of mounting hole on skin, protective pad 1 are fixedly connected with one end of link block 2.
As depicted in figs. 1 and 2, preferably, link block 2 is cylinder, internal thread is equipped at the center of link block 2
Hole, link block 2 and screw rod 3 are coaxial, and screw rod 3 is inserted into the internal thread hole of link block 2, which is in link block 2
Axially through the through-hole of setting at the heart.Link block 2 is coaxial arrangement with protective pad 1, and the overall diameter of link block 2 is less than protective pad
1 overall diameter, the interior diameter (namely diameter of internal thread hole) of link block 2 are less than the interior diameter of protective pad 1.Link block 2 and spiral shell
Bar 3 is to be threadedly coupled, and easy disassembly helps to improve the installation effectiveness of pipe fitting joint.It, need to be first by pipe when installing pipe fitting joint
Then screw rod 3 is inserted into the internal thread hole of link block 2 by part fitting sleeve on screw rod 3, then tighten screw rod 3, screw rod 3 and company
It connects block 2 and matches clamping pipe fitting joint, then pipe fitting joint is inserted into the mounting hole on aircraft skin, until protective pad 1 connects
It contacts that the outer surface of aircraft skin, pipe fitting joint are inserted in place, completes the positioning of pipe fitting joint, at this time protective pad 1 and link block 2
Positioned at the outside of aircraft skin, position-limiting action is played to pipe fitting joint in the axial direction of pipe fitting joint, and ensure pipe fitting joint
It is in coaxial state with the mounting hole on aircraft skin, ensures that the setting angle of pipe fitting joint meets the requirements.
As depicted in figs. 1 and 2, screw rod 3 includes flange 301, optical axis section 302 and the thread segment 303 set gradually in an axial direction,
Thread segment 303 is threadedly coupled with link block 2 and thread segment 303 is equipped with external screw thread.Flange 301, optical axis section 302 and thread segment
303 be cylinder and flange 301, optical axis section 302 and thread segment 303 be coaxial arrangement, one end of optical axis section 302 and flange
301 are fixedly connected, and the other end of optical axis section 302 is fixedly connected with one end of thread segment 303.The diameter of flange 301 is more than optical axis
The diameter of the diameter of section 302 and thread segment 303 and flange 301 is not more than the diameter of the mounting hole on aircraft skin, flange 301
Diameter is more than the diameter of the centre bore of pipe fitting joint, and the length of optical axis section 302 is more than the length of flange 301 and thread segment 303, spiral shell
External screw thread is arranged in the outer surface of line section 303, and optical axis section 302 is the part that surface is smooth, is not threaded.In use, pipe fitting connects
Headgear is set in the optical axis section 302 of screw rod 3, and the thread segment 303 of screw rod 3 is inserted into the internal thread hole of link block 2, is tightening screw rod
After 3, pipe fitting joint is clamped by the flange 301 and link block 2 of screw rod 3, and the end face of pipe fitting joint is contacted with flange 301, pipe fitting
The other end of connector is contacted with the end face of link block 2, and protective pad 1 is around pipe fitting joint.When installing pipe fitting joint, need to first by
Pipe fitting joint is sleeved on screw rod 3, is then inserted into the thread segment 303 of screw rod 3 in the internal thread hole of link block 2, is then tightened spiral shell
The flange 301 of bar 3, screw rod 3 matches clamping pipe fitting joint with link block 2, then holds link block 2 by operating personnel, prepares
Pipe fitting joint is inserted into the mounting hole on aircraft skin.Operating personnel by pipe fitting joint be inserted into aircraft skin on mounting hole
During, screw rod 3 is directed at the mounting hole on aircraft skin by operating personnel first, and then connection is pushed axially in operating personnel
Block 2, the flange 301 of screw rod 3 pass through the mounting hole on aircraft skin, and then pipe fitting joint is inserted into the installation on aircraft skin
Kong Zhong, final until protective pad 1 touches the outer surface of aircraft skin, pipe fitting joint is inserted in place, and is completed pipe fitting joint and is being flown
Positioning on machine covering.Screw rod 3 using the above structure, and screw rod 3 is to be threadedly coupled with link block 2, is screwed convenient for passing through
To control the depth that screw rod 3 is inserted into link block 2, namely convenient for control the distance between flange 301 and link block 2, Jin Erke
It is suitable for the installation of the pipe fitting joint of different length, versatility is good.
After completing positioning of the pipe fitting joint on aircraft skin, pipe fitting joint and aircraft skin are carried out using adhesive
Bonding connection.After completing the bonding connection of pipe fitting joint and aircraft skin, adhesive need to be cured, and wait for that adhesive is completely solid
After change, pipe fitting joint and aircraft skin close and firm is made to link together, pipe fitting joint is fixed on aircraft skin, completes pipe fitting
Installation of the connector on aircraft skin.
In the curing process, it is to make adhesive through solidification after a period of time by the way of naturally dry.Cure herein
During, link block 2 matches clamping pipe fitting joint with screw rod 3, and link block 2 and screw rod 3 remain stationary as, and link block 2 is in axis
Position-limiting action is played to pipe fitting joint upwards, and aircraft skin provides a supporting role pipe fitting joint so that pipe fitting joint
Position remains stationary as, it is ensured that the setting angle of pipe fitting joint meets the requirements.
After completing installation of the pipe fitting joint on aircraft skin, screw rod 3 is unscrewed, under screw rod 3 is dismantled from link block 2
Come, then remove link block 2, completes the dismounting of aircraft pipe fitting joint installation auxiliary mould, wait for next pipe fitting joint
Installation.
The present invention is exemplarily described above in association with attached drawing.Obviously, present invention specific implementation is not by above-mentioned side
The limitation of formula.As long as using the improvement of the various unsubstantialities of inventive concept and technical scheme of the present invention progress；Or not
It is improved, the above-mentioned design of the present invention and technical solution are directly applied into other occasions, in protection scope of the present invention
Within.
Claims (7)
1. aircraft pipe fitting joint installs auxiliary mould, it is characterised in that：Make including being used to play limit to pipe fitting joint in the axial direction
Link block and be the screw rod that is threadedly coupled and may pass through the mounting hole being arranged on aircraft skin, exhaust joint set with link block
On screw rod and exhaust joint is matched for clamping tightly by screw rod and link block.
2. aircraft pipe fitting joint according to claim 1 installs auxiliary mould, it is characterised in that：The link block is equipped with
For the protective pad that the outer surface with aircraft skin contacts, protective pad is made of softwood matter, and link block is located at aircraft skin
Outside.
3. aircraft pipe fitting joint according to claim 2 installs auxiliary mould, it is characterised in that：The material of the protective pad
For rubber.
4. aircraft pipe fitting joint according to claim 2 or 3 installs auxiliary mould, it is characterised in that：The protective pad is
Cirque structure, protective pad are coaxial arrangement with the screw rod.
5. aircraft pipe fitting joint according to any one of claims 1 to 4 installs auxiliary mould, it is characterised in that：The connection
Block is cylinder, and internal thread hole, link block and the screw coaxial are equipped at the center of link block.
6. aircraft pipe fitting joint according to claim 5 installs auxiliary mould, it is characterised in that：The screw rod includes along axis
To flange, optical axis section and the thread segment set gradually, thread segment is threadedly coupled with the link block and thread segment is equipped with outer spiral shell
Line.
7. aircraft pipe fitting joint according to claim 6 installs auxiliary mould, it is characterised in that：The flange and the light
Shaft part is cylinder, and the diameter of flange is more than the diameter of optical axis section and the diameter of flange is no more than the installation on the aircraft skin
The diameter in hole, the diameter of flange are more than the diameter of the centre bore of pipe fitting joint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810638564.6A CN108621056A (en) | 2018-06-20 | 2018-06-20 | Aircraft pipe fitting joint installs auxiliary mould |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810638564.6A CN108621056A (en) | 2018-06-20 | 2018-06-20 | Aircraft pipe fitting joint installs auxiliary mould |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108621056A true CN108621056A (en) | 2018-10-09 |
Family
ID=63692042
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810638564.6A Pending CN108621056A (en) | 2018-06-20 | 2018-06-20 | Aircraft pipe fitting joint installs auxiliary mould |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108621056A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2925760Y (en) * | 2006-06-28 | 2007-07-25 | 宝山钢铁股份有限公司 | Large roller-bearing integrated disattachable clamp |
| KR101441893B1 (en) * | 2013-03-26 | 2014-09-22 | 주식회사 오비피이엔지 | Jig of Pipe for fitting |
| CN204195579U (en) * | 2014-10-15 | 2015-03-11 | 江门市南洋船舶工程有限公司 | A kind of grip device of flanged fitting marking machine peculiar to vessel |
| CN207273074U (en) * | 2017-10-11 | 2018-04-27 | 江西昌河航空工业有限公司 | A kind of Journal housing frock |
| CN208451436U (en) * | 2018-06-20 | 2019-02-01 | 中电科芜湖钻石飞机制造有限公司 | Aircraft pipe fitting joint installs auxiliary mould |
-
2018
- 2018-06-20 CN CN201810638564.6A patent/CN108621056A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2925760Y (en) * | 2006-06-28 | 2007-07-25 | 宝山钢铁股份有限公司 | Large roller-bearing integrated disattachable clamp |
| KR101441893B1 (en) * | 2013-03-26 | 2014-09-22 | 주식회사 오비피이엔지 | Jig of Pipe for fitting |
| CN204195579U (en) * | 2014-10-15 | 2015-03-11 | 江门市南洋船舶工程有限公司 | A kind of grip device of flanged fitting marking machine peculiar to vessel |
| CN207273074U (en) * | 2017-10-11 | 2018-04-27 | 江西昌河航空工业有限公司 | A kind of Journal housing frock |
| CN208451436U (en) * | 2018-06-20 | 2019-02-01 | 中电科芜湖钻石飞机制造有限公司 | Aircraft pipe fitting joint installs auxiliary mould |
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