CN108791949A - Aircraft wing assembly auxiliary mould - Google Patents
Aircraft wing assembly auxiliary mould Download PDFInfo
- Publication number
- CN108791949A CN108791949A CN201810671700.1A CN201810671700A CN108791949A CN 108791949 A CN108791949 A CN 108791949A CN 201810671700 A CN201810671700 A CN 201810671700A CN 108791949 A CN108791949 A CN 108791949A
- Authority
- CN
- China
- Prior art keywords
- sliding bar
- aircraft wing
- auxiliary mould
- assembly auxiliary
- wing assembly
- 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.)
- Granted
Links
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 20
- 235000004443 Ricinus communis Nutrition 0.000 claims description 11
- 229910000831 Steel Inorganic materials 0.000 claims description 5
- 239000010959 steel Substances 0.000 claims description 5
- 125000006850 spacer group Chemical group 0.000 description 6
- 230000001681 protective effect Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 240000000528 Ricinus communis Species 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000011122 softwood Substances 0.000 description 1
- 230000002459 sustained effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Load-Engaging Elements For Cranes (AREA)
Abstract
The invention discloses a kind of aircraft wing assembly auxiliary moulds, including rack body, the moveable lifting device being set on rack body and for being connect with wing and the jack for being set on rack body and be used to jack lifting device.The aircraft wing assembly auxiliary mould of the present invention is matched by the way that lifting device and jack is arranged, is conveniently operated personnel and wing is assembled on airframe, it is simple in structure, it is easy to use, it is at low cost, it is easy to maintain, the efficiency of assembling of aircraft wing and fuselage can be improved.
Description
Technical field
The invention belongs to General Aviation technical field of auxiliary equipment, specifically, the present invention relates to a kind of aircraft wing dresses
Adapted auxiliary mould.
Background technology
The features such as wing of aircraft is one of important feature of aircraft, and wing has size larger, and weight is larger.It is assembling
When, need the location and installation for realizing wing and fuselage using assembly tooling, existing assembly tooling that can also realize aircraft wing
Assembly.But the maneuverability of existing assembly tooling is poor, needs to be promoted using manpower, then carries out location and installation,
Quickly it can not be adjusted and be promoted according to actual needs, labor intensity when aircraft wing being caused to be assembled with fuselage is big, effect
Rate 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 wing assembly auxiliary mould, it is therefore an objective to improve the efficiency of assembling of aircraft wing and fuselage.
To achieve the goals above, the technical solution that the present invention takes is：Aircraft wing assembly auxiliary mould, including branch
Frame body, the moveable lifting device being set on rack body and for being connect with wing and be set on rack body and
Jack for jacking lifting device.
The lifting device include be vertically arranged and connect with the jack middle part sliding bar, be vertically arranged and with institute
It is the side sliding bar being slidably connected, the connecting rod being connect with middle part sliding bar and side sliding bar and setting to state rack body
In the wing connection on the sliding bar of middle part and for being connect with wing, jack is located at the lower section of middle part sliding bar.
The side sliding bar is arranged two, and the middle part sliding bar is located between two side sliding bars, middle part sliding
Bar is fixedly connected by the connecting rod with two side sliding bars.
The length of the middle part sliding bar is more than the length of the side sliding bar, and middle part sliding bar passes through multiple companies
Extension bar is fixedly connected with side sliding bar.
The middle part sliding bar and the rectangular steel pipe that the side sliding bar is inner hollow.
The rack body includes pedestal and is vertically arranged on pedestal and is used to play the guiding role to the lifting device
Guide rod, the side sliding bar is sheathed on guide rod.
The guide rod is arranged two, and the jack is located between two guide rods.
The rack body further includes the bracing piece being connect with the pedestal and the guide rod, and bracing piece setting is multiple.
The bracing piece be obliquely installed, the upper end of bracing piece is fixedly connected with the guide rod, the lower end of bracing piece and
The pedestal is fixedly connected, and each guide rod is at least fixedly connected with two bracing pieces.
The rack body further includes the castor being set on the pedestal.
The aircraft wing assembly auxiliary mould of the present invention is matched by the way that lifting device and jack is arranged, facilitates behaviour
Make personnel wing is assembled on airframe, it is simple in structure, it is easy to use, it is at low cost, it is easy to maintain, aircraft machine can be improved
The efficiency of assembling of the wing and fuselage.
Description of the drawings
This specification includes the following drawings, and shown content is respectively：
Fig. 1 is the structural schematic diagram of aircraft wing assembly auxiliary mould of the present invention；
Fig. 2 is the diagrammatic cross-section of lifting device and guide rod；
Fig. 3 is the schematic diagram that jack is connect with lifting device；
Fig. 4 is the structural schematic diagram of wing connection；
In figure label for：1, castor；2, middle part sliding bar；3, side sliding bar；4, connecting rod；5, wing connection；
501, connecting shaft；502, the first supporting block；503, the second supporting block；504, pin hole；6, guide rod；7, first crossbeam；8, second
Crossbeam；9, bracing piece；10, jack.
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 shown in Figure 1 to Figure 3, the present invention provides a kind of aircraft wing assembly auxiliary mould, including rack body, can
It the mobile lifting device being set on rack body and for connect with wing and is set on rack body and is used to jack
The jack 10 of lifting device.
Specifically, as depicted in figs. 1 and 2, lifting device is vertically arranged on rack body, lifting device relative to
Rack body is vertically to move, and lifting device is connect with aircraft wing to be assembled, and lifting device is being lifted
When aircraft wing to be assembled can be driven to synchronize lifted, facilitate and control aircraft wing to be assembled and fuselage into luggage
Match.In use, lifting device is connect with the wing tip of aircraft wing to be assembled, then reusing manpower will be to be assembled
The other end opposite with wing tip of aircraft wing be put into fuselage, lifting device is then jacked by jack 10, promotes dress
It sets and aircraft wing is driven to synchronize and move up, aircraft wing is jacked to predetermined altitude, makes the mounting hole on aircraft wing and machine
Mounting pin, is finally inserted into the mounting hole of aircraft wing and fuselage, to complete aircraft wing by mounting hole alignment with it
With the assembly of fuselage.
As shown in Figure 1 to Figure 3, lifting device includes the middle part sliding bar 2, vertical for being vertically arranged and being connect with jack 10
The connection for being arranged and being the side sliding bar 3 being slidably connected with rack body, connect with middle part sliding bar 2 and side sliding bar 3
It bar 4 and is set on the sliding bar 2 of middle part and for the wing connection that is connect with wing, jack 10 is located at middle part sliding bar
2 lower section.Jack 10 is vertically arranged on rack body, and the structure of jack 10 is as known to one of skill in the art
As, include mainly the pump housing and ejection piston, the pump housing is fixedly connected with rack body, and the pump housing is inserted into the lower end for ejecting piston
Inside, the upper end for ejecting piston is fixedly connected with middle part sliding bar 2.By the flexible of jack 10, lifting device is realized
Jacking and decline.It is driven using jack 10, can realize aircraft wing upper and lower directions under the conditions of more light labour-saving
Movement, while be more prone to control and adjust promoted height, increase flexibility and the maneuverability of assembly.
As shown in Figure 1 to Figure 3, side sliding bar 3 is arranged two, middle part sliding bar 2 be located at two side sliding bars 3 it
Between, middle part sliding bar 2 is fixedly connected by connecting rod 4 with two side sliding bars 3.Two side sliding bars 3 are in same height
Degree, middle part sliding bar 2 are arranged one, and middle part sliding bar 2 is located at the middle position of two side sliding bars 3, middle part sliding bar 2
Length be more than the length of side sliding bar 3, middle part sliding bar 2 is fixedly connected by multiple connecting rods 4 with side sliding bar 3,
Two side sliding bars 3 are fixedly connected by multiple connecting rods 4 with middle part sliding bar 2 respectively, and connecting rod 4 is horizontally disposed, is connected
The length direction of extension bar 4 and the length direction of middle part sliding bar 2 are perpendicular, and one end of connecting rod 4 is fixed with side sliding bar 3 to be connected
It connects, the other end of connecting rod 4 is fixedly connected with middle part sliding bar 2.Middle part sliding bar 2 and side sliding bar 3 pass through multiple connections
Bar 4 links into an integrated entity structure, and multiple connecting rods 4 are arranged between side sliding bar 3 and middle part sliding bar 2 and all connecting rods 4 are
It is vertically sequentially arranged, the lifting device of formation is simple in structure, easy to process, and intensity is high, stable.
As depicted in figs. 1 and 2, each side sliding bar 3 is connect with middle part sliding bar 2 by two connecting rods 4, even
Extension bar 4 is arranged four altogether.Two connecting rods 4 are set between side sliding bar 3 and middle part sliding bar 2, and two connecting rods 4 are along perpendicular
Histogram is to being sequentially arranged, top and bottom of two connecting rods 4 respectively close to side sliding bar 3.
Preferably, middle part sliding bar 2 and the rectangular steel pipe that side sliding bar 3 is inner hollow, connecting rod 4 is also interior
The hollow rectangular steel pipe in portion, connecting rod 4 are to be welded to connect with middle part sliding bar 2 and side sliding bar 3.
The wing connection of lifting device is attached with the wing tip of aircraft wing, and the wing tip of aircraft wing has the machine that allows
The axis hole that wing connector is inserted into.As shown in Figure 1 and Figure 4, wing connection is located at the top of middle part sliding bar, wing connection packet
Connecting shaft 501, the first supporting block 502 and the second supporting block 503 being connect with the first supporting block 502 and connecting shaft 501 are included, the
One supporting block 502 is fixedly connected with the top of middle part sliding bar 2 and the top of the first supporting block 502 towards middle part sliding bar 2 is prolonged
It stretches, the first supporting block 502 is vertically arranged.Second supporting block 503 is fixedly connected with the upper end of the first supporting block 502, first
The lower end of supporting block 502 is fixedly connected with middle part sliding bar 2.Connecting shaft 501 is horizontally disposed, and connecting shaft 501 is for insertion into
In axis hole on the wing tip of aircraft wing, to be provided a supporting role to aircraft wing.Connecting shaft 501 is cylinder, connecting shaft 501
Axis and middle part sliding bar length direction it is perpendicular, the diameter of connecting shaft 501 and the axis hole on the wing tip of aircraft wing
Diameter is roughly the same.Connecting shaft 501 and the second supporting block 503 all have certain length, and the second supporting block 503, which is located at, to be connected
In the axial direction of spindle 501, the second supporting block 503 be also it is horizontally disposed, one end on the length direction of connecting shaft 501 with second
One end on the length direction of bracer 503 is fixedly connected, and connecting shaft 501 is stretched out towards the outside of the second supporting block 503, convenient for inserting
In the axis hole for entering the wing tip of aircraft wing.The size of second supporting block 503 is more than the diameter of connecting shaft 501, by lifting device
After being connect with the wing tip of aircraft wing to be assembled, the second supporting block 503 is located at the lower section of aircraft wing and on wing tip
The outside of axis hole, the second supporting block 503 to aircraft wing in the axial direction of connecting shaft 501 for playing position-limiting action, it is ensured that even
Spindle 501 can be properly inserted in place.Connecting shaft 501 be equipped with allow spacer pin be inserted into pin hole 504, spacer pin be also for
Position-limiting action is played to aircraft wing in the axial direction of connecting shaft 501, spacer pin is located on the outside of the axis hole on wing tip and wing tip
Axis hole be located between spacer pin and the second supporting block 503, so as to prevent connecting shaft 501 and aircraft wing from falling off, it is ensured that
The reliability that lifting device is connect with aircraft wing.Pin hole 504 is to be set in 501 extending radially through for upper edge connecting shaft 501 of connecting shaft
The through-hole set so that the both ends of spacer pin can extend out to the outside of connecting shaft 501, and pin hole 504 is located at the length of connecting shaft 501
One end on direction, the other end on the length direction of connecting shaft 501 are fixedly connected with the second supporting block 503.Spacer pin can
It is inserted into pin hole 504, can also be extracted out from pin hole 504, facilitate the dismounting between wing connection and aircraft wing.
Preferably, as shown in Figure 1 and Figure 4, the second supporting block 503 is semicircle block structure, the second supporting block 503
Axis is parallel with the axis of connecting shaft 501 and the axis of the second supporting block 503 and the axis of connecting shaft 501 are in same perpendicular
In facing directly, the top of the axis of the second supporting block 503 and the axis positioned at connecting shaft 501, the radius of the second supporting block 503 is more than
The diameter of connecting shaft 501, so as to play good position-limiting action to aircraft wing.The top surface of second supporting block 503 is flat
Face, the bottom surface of the second supporting block 503 are that the radian of arc surface and the arc surface is 180 degree, the bottom surface of the second supporting block 503 and the
One supporting block 502 is fixedly connected.The material of first supporting block 502, the second supporting block 503 and connecting shaft 501 be metal, second
The top surface of bracer 503 is equipped with the protective pad for being contacted with aircraft wing, and protective pad is supported using softwood matter, such as protective pad
Material is rubber, and the second supporting block 503 is not in direct contact with the surface of aircraft wing, to play branch to aircraft wing
Support can cause to damage while acting on to avoid to aircraft wing, it is ensured that product quality.The top surface of second supporting block 503 is flat
Face, the top surface of the second supporting block 503 and the length direction of middle part sliding bar are perpendicular, and protective pad all covers the second supporting block
503 top surface, protective pad are contacted with the surface of aircraft wing, and contact area is big, it is ensured that the stability of aircraft wing support.
As depicted in figs. 1 and 2, rack body includes pedestal and is vertically arranged on pedestal and is led for being risen to lifting device
To the guide rod 6 of effect, side sliding bar 3 is sheathed on guide rod 6.The top and bottom of side sliding bar 3 all have to allow and lead
To bar 6 by opening, guide rod 6 be inner hollow rectangular steel pipe, guide rod 6 be arranged two, the lower end and bottom of guide rod 6
Seat is fixedly connected, and guide rod 6 extends towards the top of pedestal, and each side sliding bar 3 is sheathed on respectively on a guide rod 6,
Guide rod 6 and side sliding bar 3 match, and lifting device can carry out the movement of upper and lower directions relative to guide rod 6, lead simultaneously
It is arranged two to bar 6, ensures that lifting device will not run-off the straight.
As shown in Figure 1 to Figure 3, middle part sliding bar 2 and jack 10 are located between two guide rods 6, and jack 10 is perpendicular
It is directly set on the base, jack 10 is to be welded to connect with pedestal, ensure that the stability on a thousand pieces of gold top, ensures jack 10 and carries
Rising device will not shake.
As shown in Figure 1, rack body further includes the bracing piece 9 being connect with pedestal and guide rod 6, bracing piece 9 be arranged it is multiple,
Two guide rods 6 are fixedly connected with the bracing piece of equivalent amount 9 respectively.Bracing piece 9 be obliquely installed, the upper end of bracing piece 9 with
Guide rod 6 is fixedly connected, and the lower end of bracing piece 9 is fixedly connected with pedestal, and each guide rod 6 is at least fixed with two bracing pieces 9
Connection.Rack body improves integral strength, the setting of bracing piece 9 can make auxiliary mould stress equal by the way that bracing piece 9 is arranged
It is even, ensure the stability of auxiliary mould, helps to improve the stability of strutting system to aircraft wing.
As shown in Figure 1, pedestal is formed by connecting by first crossbeam 7 and second cross beam 8, first crossbeam 7 and second cross beam 8 are
Horizontally disposed, the length direction of the length direction and second cross beam 8 of first crossbeam 7 is perpendicular, the axis of connecting shaft 501 and second
The length direction of crossbeam 8 is parallel, and first crossbeam 7 is arranged one, and second cross beam 8 is arranged two, and two second cross beams 8 are equal
Row, first crossbeam 7 are located between two second cross beams 8, and one end of first crossbeam 7 is fixedly connected with one of second cross beam 8,
The other end of first crossbeam 7 is fixedly connected with another second cross beam 8, and first crossbeam 7 is on the length direction of second cross beam 8
Middle position be fixedly connected with second cross beam 8.Jack 10 is the middle position on the length direction of first crossbeam 7
It is fixedly connected with first crossbeam 7, two guide rods 6 are fixedly connected with first crossbeam 7, and guide rod 6 and first crossbeam 7 are perpendicular.
Bracing piece 9 is fixedly connected with second cross beam 8, and two guide rods 6 are located between two second cross beams 8, and each guide rod 6 leads to respectively
It crosses two bracing pieces 9 to connect with apart from a nearest second cross beam 8, two bracing pieces 9 connecting with the same guide rod 6 are in
V-arrangement arrange, the upper end for two bracing pieces 9 being connect with the same guide rod 6 be located at sustained height and the upper end of bracing piece 9 with lead
Be fixedly connected to bar 6, the lower end for two bracing pieces 9 being connect with the same guide rod 6 with apart from the guide rod 6 it is nearest second
Crossbeam 8 is fixedly connected and the lower end of two bracing pieces 9 is respectively close to one end on the length direction of second cross beam 8, is arranged in this way
Auxiliary mould integral strength is improved, the stability of auxiliary mould is further ensured.
As shown in Figure 1, rack body further includes the castor 1 being set on pedestal, castor 1 is located at the lower section of pedestal, castor 1
It is fixedly connected with the second cross beam 8 of pedestal, two castors 1 is at least set on each second cross beam 8.Castor 1 contacted with ground and
It can roll on the ground, personnel easy to operation push auxiliary mould and aircraft wing integrally to move, and improve the behaviour of tooling
Vertical property and flexibility.
In the present embodiment, as shown in Figure 1, castor 1 is arranged four altogether, four 1 rectangular distributions of castor, each second is horizontal
Two castors 1 are respectively set on beam 8.
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 (10)
1. aircraft wing assembly auxiliary mould, it is characterised in that：Including rack body, movably it is set on rack body
And for the lifting device that connect with wing and it is set on rack body and is used to jack the jack of lifting device.
2. aircraft wing assembly auxiliary mould according to claim 1, it is characterised in that：The lifting device includes perpendicular
The straight middle part sliding bar for being arranged and being connect with the jack is vertically arranged and is the side being slidably connected with the rack body
It sliding bar, the connecting rod being connect with middle part sliding bar and side sliding bar and is set on the sliding bar of middle part and is used for and wing
The wing connection of connection, jack are located at the lower section of middle part sliding bar.
3. aircraft wing assembly auxiliary mould according to claim 2, it is characterised in that：The side sliding bar setting
Two, the middle part sliding bar is located between two side sliding bars, and middle part sliding bar passes through the connecting rod and two sides
Sliding bar is fixedly connected.
4. aircraft wing assembly auxiliary mould according to claim 2 or 3, it is characterised in that：The middle part sliding bar
Length be more than the length of the side sliding bar, middle part sliding bar, which passes through multiple connecting rods, to be fixed with side sliding bar and connects
It connects.
5. according to any aircraft wing assembly auxiliary mould of claim 2 to 4, it is characterised in that：It slides at the middle part
Lever and the rectangular steel pipe that the side sliding bar is inner hollow.
6. according to any aircraft wing assembly auxiliary mould of claim 2 to 5, it is characterised in that：The holder master
Body includes pedestal and is vertically arranged at the guide rod on pedestal and for playing the guiding role to the lifting device, and the side is slided
Lever is sheathed on guide rod.
7. aircraft wing assembly auxiliary mould according to claim 6, it is characterised in that：The guide rod setting two
A, the jack is located between two guide rods.
8. aircraft wing assembly auxiliary mould according to claim 6, it is characterised in that：The rack body further includes
The bracing piece being connect with the pedestal and the guide rod, bracing piece setting are multiple.
9. aircraft wing assembly auxiliary mould according to claim 8, it is characterised in that：The bracing piece is to tilt to set
It sets, the upper end of bracing piece is fixedly connected with the guide rod, and the lower end of bracing piece is fixedly connected with the pedestal, each guide rod
At least it is fixedly connected with two bracing pieces.
10. aircraft wing assembly auxiliary mould according to claim 8, it is characterised in that：The rack body also wraps
Include the castor being set on the pedestal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810671700.1A CN108791949B (en) | 2018-06-26 | 2018-06-26 | Auxiliary tool for aircraft wing assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810671700.1A CN108791949B (en) | 2018-06-26 | 2018-06-26 | Auxiliary tool for aircraft wing assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108791949A true CN108791949A (en) | 2018-11-13 |
| CN108791949B CN108791949B (en) | 2024-01-12 |
Family
ID=64070821
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810671700.1A Active CN108791949B (en) | 2018-06-26 | 2018-06-26 | Auxiliary tool for aircraft wing assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108791949B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114104324A (en) * | 2021-11-15 | 2022-03-01 | 山东省复材成型技术与装备研究院 | Assembly fixture of lightweight wing |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB303993A (en) * | 1927-12-10 | 1929-01-17 | George Machray | Improvements in or relating to lifting jacks |
| US20100119343A1 (en) * | 2005-11-15 | 2010-05-13 | The Boeing Company | Aircraft Landing Gear Loader |
| CN104210983A (en) * | 2014-09-01 | 2014-12-17 | 郝迎吉 | Mechanical airplane jack |
| CN104281771A (en) * | 2013-07-12 | 2015-01-14 | 波音公司 | Apparatus and Method for Moving a Structure in a Manufacturing Environment |
| CN205614141U (en) * | 2016-04-11 | 2016-10-05 | 常州兆邦液压成套设备有限公司 | Height -adjustable and sawing machine configuration work material remove support frame |
| JP2017077741A (en) * | 2015-10-19 | 2017-04-27 | 三菱航空機株式会社 | Aircraft landing device handling dolly, landing device fitting method and detaching method using the same |
| US20180118537A1 (en) * | 2016-11-01 | 2018-05-03 | Vernon Roy Goodsell | Airplane Jack Apparatus |
| CN208453259U (en) * | 2018-06-26 | 2019-02-01 | 中电科芜湖钻石飞机制造有限公司 | Auxiliary mould is used in aircraft wing assembly |
-
2018
- 2018-06-26 CN CN201810671700.1A patent/CN108791949B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB303993A (en) * | 1927-12-10 | 1929-01-17 | George Machray | Improvements in or relating to lifting jacks |
| US20100119343A1 (en) * | 2005-11-15 | 2010-05-13 | The Boeing Company | Aircraft Landing Gear Loader |
| CN104281771A (en) * | 2013-07-12 | 2015-01-14 | 波音公司 | Apparatus and Method for Moving a Structure in a Manufacturing Environment |
| CN104210983A (en) * | 2014-09-01 | 2014-12-17 | 郝迎吉 | Mechanical airplane jack |
| JP2017077741A (en) * | 2015-10-19 | 2017-04-27 | 三菱航空機株式会社 | Aircraft landing device handling dolly, landing device fitting method and detaching method using the same |
| CN205614141U (en) * | 2016-04-11 | 2016-10-05 | 常州兆邦液压成套设备有限公司 | Height -adjustable and sawing machine configuration work material remove support frame |
| US20180118537A1 (en) * | 2016-11-01 | 2018-05-03 | Vernon Roy Goodsell | Airplane Jack Apparatus |
| CN208453259U (en) * | 2018-06-26 | 2019-02-01 | 中电科芜湖钻石飞机制造有限公司 | Auxiliary mould is used in aircraft wing assembly |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114104324A (en) * | 2021-11-15 | 2022-03-01 | 山东省复材成型技术与装备研究院 | Assembly fixture of lightweight wing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108791949B (en) | 2024-01-12 |
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