CN107161325A - Inside and outside wing flap crosslinking apparatus - Google Patents
Inside and outside wing flap crosslinking apparatus Download PDFInfo
- Publication number
- CN107161325A CN107161325A CN201710643247.9A CN201710643247A CN107161325A CN 107161325 A CN107161325 A CN 107161325A CN 201710643247 A CN201710643247 A CN 201710643247A CN 107161325 A CN107161325 A CN 107161325A
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- China
- Prior art keywords
- wing flap
- piston
- wedge
- cartridge module
- outside
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- 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
- 238000004132 cross linking Methods 0.000 title claims abstract description 46
- 230000003139 buffering effect Effects 0.000 claims abstract description 5
- 238000001514 detection method Methods 0.000 claims description 18
- 230000035939 shock Effects 0.000 claims description 16
- 230000014759 maintenance of location Effects 0.000 claims description 15
- 230000000694 effects Effects 0.000 abstract description 8
- 238000010276 construction Methods 0.000 abstract description 4
- 238000011176 pooling Methods 0.000 abstract description 4
- 230000033001 locomotion Effects 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 229910000883 Ti6Al4V Inorganic materials 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000002929 anti-fatigue Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/20—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by multiple flaps
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Actuator (AREA)
- Fluid-Damping Devices (AREA)
- Vibration Dampers (AREA)
Abstract
The present invention relates to inside and outside wing flap crosslinking apparatus.The inside and outside wing flap crosslinking apparatus includes：Piston cartridge module；Piston rod assembly, the piston rod assembly is arranged in the piston cartridge module, and relative to the piston cartridge module it is radially fixed, be axially moveable；Arc wedge, the arc wedge is fixed on the outside of the piston cartridge module, and the arc wedge includes the first wedge-shaped compressive plane；Recessed circle, the recessed circle is fixed on the outside of the piston rod assembly, and the recessed circle includes the second wedge shaped squeeze face；When the described first wedge-shaped compressive plane is contacted with the second wedge shaped squeeze face, produce axial force to realize positive buffering.The inside and outside wing flap crosslinking apparatus of the present invention can play following advantageous effects：The positive pooling feature of overtravel can be realized, and it is simple in construction, install and safeguard easy.
Description
Technical field
The present invention relates to inside and outside wing flap crosslinking apparatus.
Background technology
Due to being limited and by airport runway length, gear tyre speed in order to improve takeoff and landing security,
High-lift device is able to continue to develop and extensive use in the design of modern large aircraft.It is arranged in the height essence in trailing edge cabin
Close and complicated motion and drive system, realize high-lift aerofoil freely changing between each aerodynamic configuration/screens.
Drive system is general to be made up of power take-off unit, torque transmission linear system and high transmission ratio power/torque output actuator, actuator
Main Force transmission partses are generally high intensity high-quality steel and are machined into, with higher durability mechanical performance, but it is antifatigue and
Initial imperfection Crack Extension performance is poor.In the case of not dismantling and decomposing actuator during airplane operation, ground maintenance people
Member can not carry out effective damage inspection to it.Airworthiness regulation requirement must be subject to the single failure of such system in the design
Consider (and no matter how low its fault rate is), must ensure that aircraft still has continuation safe flight and landing after the system failure
Ability.
Every piece of trailing edge flap typically has two or more drive ram, when wherein a certain actuator occurs to disengage failure
When, aerofoil will produce and largely tilt (being mainly shown as the tangential motion of aerofoil end rib), when this deformation displacement is excessive,
Both sides wing exceeds the rolling moment of airplane trim ability by producing, so as to hinder flight safety.Arranged between inside and outside wing flap
One is inside and outside wing flap crosslinking apparatus along the tangential single-degree-of-freedom actuator of wing flap, can play reduction failure aerofoil over-tilting and carry
The effect of constraint is aided in for aerofoil, and then ensures that aircraft still has continuation safe flight and throwing power after the system failure.
However, the inside and outside wing flap crosslinking apparatus general structure of prior art is complex, and maintenance inconvenience is installed.
The content of the invention
It is an object of the present invention to overcome the defect of existing inside and outside wing flap crosslinking apparatus there is provided it is a kind of it is new inside and outside
Wing flap crosslinking apparatus, it can realize the positive pooling feature of overtravel, and simple in construction, install and safeguard easy.
The present invention object above realized by a kind of inside and outside wing flap crosslinking apparatus, the inside and outside wing flap crosslinking apparatus bag
Include：
Piston cartridge module；
Piston rod assembly, the piston rod assembly is arranged in the piston cartridge module, and relative to the piston cylinder group
Part is radially fixed, be axially moveable；
Arc wedge, the arc wedge is fixed on the outside of the piston cartridge module, the arc wedge
Including the first wedge-shaped compressive plane；
Recessed circle, the recessed circle is fixed on the outside of the piston rod assembly, and the recessed circle includes the second wedge shaped squeeze face；
When the described first wedge-shaped compressive plane is contacted with the second wedge shaped squeeze face, it is positive slow to realize to produce axial force
Punching.
According to above-mentioned technical proposal, inside and outside wing flap crosslinking apparatus of the invention can play following advantageous effects：Can be real
The existing positive pooling feature of overtravel, and it is simple in construction, install and safeguard easy.
It is preferred that the piston cartridge module is provided with piston cylinder sawtooth in its middle inside, the piston rod assembly is at it
Outside two ends are provided with piston rod sawtooth, wherein, when the described first wedge-shaped compressive plane is contacted with the second wedge shaped squeeze face, also
Radial load is produced, the piston cylinder sawtooth and the piston rod sawtooth are held tightly, is realized reverse locked.
According to above-mentioned technical proposal, inside and outside wing flap crosslinking apparatus of the invention can play following advantageous effects：Can be real
The reverse locking function of existing overtravel.
It is preferred that the piston cartridge module is the piston cartridge module of evagination in the middle part of three pieces of separate types, the piston cylinder group
Part has elastomeric radial ability.
It is preferred that the inside and outside wing flap crosslinking apparatus also includes：
Axial stroke retainer, the axial stroke retainer is fixed on the outside of the piston cartridge module；
Detection sensor, the detection sensor is fixed on the axial stroke retainer；
Target, the target is fixed on the recessed circle；
Wherein, when the distance between the detection sensor and the target are less than predetermined threshold, the detection sensing
Device sends electric signal to realize that overtravel is detected.
According to above-mentioned technical proposal, inside and outside wing flap crosslinking apparatus of the invention can play following advantageous effects：Can be real
Existing overtravel detecting function.
It is preferred that the axial stroke retainer also includes the first axial retention shock surface；
The recessed circle also includes the second axial retention shock surface；
When the first axial retention shock surface is contacted with the second axial retention shock surface, positive stop is realized.
According to above-mentioned technical proposal, inside and outside wing flap crosslinking apparatus of the invention can play following advantageous effects：Can be real
The existing positive locking function of overtravel.
It is preferred that the inside and outside wing flap crosslinking apparatus also includes being arranged at the arc wedge and the piston cylinder group
Radial direction pad between part, to realize that arc wedge compressive plane external diameter is adjusted.
It is preferred that the inside and outside wing flap crosslinking apparatus also includes being arranged between the recessed circle and the piston rod assembly
Axial pad, with realize free travel adjust.
Brief description of the drawings
Fig. 1 is the stereogram of the inside and outside wing flap crosslinking apparatus of one embodiment of the invention.
Fig. 2 is the sectional view of the inside and outside wing flap crosslinking apparatus of one embodiment of the invention.
Reference numerals list
1st, piston rod assembly
2nd, piston cartridge module
3rd, arc wedge
4th, recessed circle
5th, detection sensor
6th, target
7th, the first wedge-shaped compressive plane
8th, the second wedge shaped squeeze face
9th, the first axial retention shock surface
10th, the second axial retention shock surface
11st, piston cylinder sawtooth
12nd, piston rod sawtooth
13rd, axial stroke retainer
Embodiment
Embodiment of the invention explained below, it should be pointed out that in the specific descriptions of these embodiments
During, in order to carry out brief and concise description, this specification can not possibly be made in detail to all features of actual embodiment
Most description.It is to be understood that in the actual implementation process of any one embodiment, as in any one work
During journey project or design object, in order to realize the objectives of developer, in order to meet system it is related or business
The related limitation of industry, can usually make various specific decision-makings, and this can also be implemented from a kind of embodiment to another
Changed between mode.Although moreover, it is to be understood that effort made in this development process is probably complicated
And it is tediously long, but for one of ordinary skill in the art related to present disclosure, in the disclosure
The changes such as some designs, manufacture or the production that are carried out on the basis of the technology contents of exposure are conventional technology, no
It should be understood to that content of this disclosure is insufficient.
Unless otherwise defined, the technical term or scientific terminology used in claims and specification should be this hair
The ordinary meaning that the personage with general technical ability is understood in bright art.Present patent application specification and power
" first ", " second " that is used in sharp claim and similar word are not offered as any order, quantity or importance, and
It is used only to distinguish different parts.The similar word such as " one " or " one " is not offered as quantity limitation, but represents
In the presence of at least one.The similar word such as " comprising " or "comprising" means to appear in the element before " comprising " or "comprising"
Or object covers the element or object and its equivalent element for appearing in " comprising " or "comprising" presented hereinafter, it is not excluded that
Other elements or object.The similar word such as " connection " or " connected " is not limited to physics or machinery connection,
It is also not necessarily limited to direct or indirect connection.
Fig. 1 is the stereogram of the inside and outside wing flap crosslinking apparatus of one embodiment of the invention.Fig. 2 is the interior of one embodiment of the invention
The sectional view of outer wing flap crosslinking apparatus.
As shown in Figure 1-2, according to an exemplary rather than exclusive embodiment of the invention, inside and outside wing flap crosslinking apparatus bag
Include：
Piston cartridge module 2；
Piston rod assembly 1, piston rod assembly 1 is arranged in piston cartridge module 2, and radially solid relative to piston cartridge module 2
Determine, be axially moveable；
Arc wedge 3, arc wedge 3 is fixed on the outside of piston cartridge module 2, and arc wedge 3 includes first
Wedge shaped squeeze face 7；
Recessed circle 4, recessed circle 4 is fixed on the outside of piston rod assembly 1, and recessed circle 4 includes the second wedge shaped squeeze face 8；
When the first wedge-shaped compressive plane 7 is contacted with the second wedge shaped squeeze face 8, produce axial force to realize positive buffering.
So, inside and outside wing flap crosslinking apparatus of the invention can realize the positive pooling feature of overtravel, and simple in construction, peace
Dress is safeguarded easy.Moreover, the inside and outside wing flap crosslinking apparatus small volume of the present invention, lighter in weight.
When any drive ram of trailing edge flap disengages failure, inside and outside wing flap crosslinking apparatus of the invention can play reduction
Failure aerofoil over-tilting and the effect for avoiding the unfavorable vibration of failure aerofoil, to meet airworthiness regulation to the single start of aircraft flap
Device disengages continuation safe flight and throwing power requirement under failure.
Specifically, when any drive ram of trailing edge flap disengages failure, inside and outside two difference of wing flap crosslinking apparatus
The distance between mount point of inside and outside wing flap end rib is fixed on by the change elongated or shortened, so as to cause piston rod assembly
1 stretches or compresses motion in the axial direction relative to piston cartridge module 2.
It is preferred that inside and outside wing flap crosslinking apparatus also includes：
Axial stroke retainer 13, axial stroke retainer 13 is fixed on the outside of piston cartridge module 2；
Detection sensor 5, detection sensor 5 is fixed on axial stroke retainer 13；
Target 6, target 6 is fixed on recessed circle 4；
Wherein, when the distance between detection sensor 5 and target 6 are less than predetermined threshold, detection sensor 5 sends telecommunications
Number detected with the overtravel for realizing the inside and outside mount point distance of wing flap crosslinking apparatus two.
It is preferred that axial stroke retainer 13 also includes the first axial retention shock surface 9；
Recessed circle 4 also includes the second axial retention shock surface 10；
When the first axial retention shock surface 9 is contacted with the second axial retention shock surface 10, positive stop is realized.
Specifically, when piston rod assembly 1 relative to piston cartridge module 2 moves overtravel along any direction, detection sensing
When the distance between device 5 and target 6 are less than predetermined threshold, detection sensor 5 will send electric signal to realize that overtravel is detected.Connect
, the first wedge-shaped compressive plane 7 of arc wedge 3 is contacted with the second wedge shaped squeeze face 8 of recessed circle 4, axial force is produced, to realize
Positive (axial direction) buffering.Finally, the first axial retention shock surface 9 of axial stroke retainer 13 axially stops with the second of recessed circle 4
Dynamic shock surface 10 is contacted, and realizes positive (axial direction) stop.
It is preferred that the inside and outside wing flap crosslinking apparatus axis of the present invention is tangential approximately along wing flap, rear end is installed on interior wing flap
End rib, front end is installed on outer wing flap end rib.Free movement travel limit is, it is necessary to reference to total travel many-body dynamics and having vertically
The first deformation simulation result of limit is determined.It is poor that the free movement travel limit need to cover flap kinematics mechanism inside and outside total travel scope
Caused by different gentle dynamic load effect between inside and outside wing flap two mount points of crosslinking apparatus distance change, and inside and outside wing flap is crosslinked
Device must not hinder the normal of wing flap to use.
It is preferred that piston cartridge module 2 is provided with piston cylinder sawtooth 11 in its middle inside, piston rod assembly 1 is on the outside of it
Two ends are provided with piston rod sawtooth 12, wherein, when the second wedge shaped squeeze of the first wedge-shaped compressive plane 7 and recessed circle 4 of arc wedge 3
When face 8 is contacted, radial load is also produced, piston cylinder sawtooth 11 and piston rod sawtooth 12 are held tightly, realized reverse locked.
That is, according to the above preferred embodiment of the present invention, inside and outside wing flap crosslinking apparatus is except that can provide overtravel
Target may also provide the reverse locking function of overtravel close to beyond detection and positive buffering locking function.
It is preferred that piston cartridge module 2 is the piston cartridge module of evagination in the middle part of three pieces of separate types, piston cartridge module 2 has
Elastomeric radial ability.
So, piston cylinder sawtooth 11 and piston rod sawtooth 12 can preferably be realized under radial load holds tightly.
It is preferred that piston cartridge module 2 is the piston cartridge module of middle part evagination predeformation.
So, piston cartridge module 2 has certain convex shape at middle part and/or with certain predeformation, therefore, when
When the wedge-shaped compressive plane 7 of the first of arc wedge 3 is contacted with the second wedge shaped squeeze face 8 of recessed circle 4, radial load is also produced, will
Piston cylinder sawtooth 11 and piston rod sawtooth 12 are held tightly, are realized reverse locked.That is, outside the above-mentioned middle part of piston cartridge module 2
Convex predeformation provides the nargin that piston cylinder sawtooth 11 and piston rod sawtooth 12 are held tightly.
It is preferred that piston cartridge module 2 and recessed circle 4 are made up of high-strength metal material, such as by Ti-6Al-4V material systems
Into.
It is preferred that piston cylinder sawtooth 11 and piston rod sawtooth 12 are made up of high-strength metal material, such as by Ti-6Al-
4V materials are made.
Certainly, above-mentioned Ti-6Al-4V materials be only piston cartridge module inside and outside the application in wing flap crosslinking apparatus, it is recessed
A kind of preferred materials form of circle, piston cylinder sawtooth and/or piston rod sawtooth, those skilled in the art are in present disclosure
On the basis of it is appreciated that also can use other suitable materials, without departing from the application scope of the claims.
It is preferred that detection sensor 5 is close to detection sensor.
It is preferred that inside and outside wing flap crosslinking apparatus also includes the footpath being arranged between arc wedge 3 and piston cartridge module 2
To pad (such as metal strippable gasket), to realize that arc wedge compressive plane external diameter is adjusted.
So, by installing (setting) radial direction pad additional between arc wedge and piston cartridge module, arc wedge can be changed
The external diameter of the wedge-shaped compressive plane of the first of shape part, can preferably realize the outer field control of shock-absorbing capacity.
It is preferred that inside and outside wing flap crosslinking apparatus also includes the axial pad being arranged between recessed circle 4 and piston rod assembly 1
(such as metallic gasket), to realize that free travel is adjusted.
So, by installing (setting) axial pad additional between recessed circle and piston rod assembly, freedom can preferably be realized
Stroke adjustment.
Some exemplary embodiments are described above.It should be understood, however, that various modifications may be made.Example
Such as, if described technology is executed in different order and/or if in described system, framework, equipment or circuit
Component is combined and/or is substituted or supplemented by other component or its equivalent by different way, then can realize suitable knot
Really.Correspondingly, other embodiment is also fallen into scope of the claims.
Claims (7)
1. a kind of inside and outside wing flap crosslinking apparatus, including：
Piston cartridge module；
Piston rod assembly, the piston rod assembly is arranged in the piston cartridge module, and relative to the piston cartridge module footpath
To fixation, it is axially moveable；
Arc wedge, the arc wedge is fixed on the outside of the piston cartridge module, and the arc wedge includes
First wedge-shaped compressive plane；
Recessed circle, the recessed circle is fixed on the outside of the piston rod assembly, and the recessed circle includes the second wedge shaped squeeze face；
When the described first wedge-shaped compressive plane is contacted with the second wedge shaped squeeze face, produce axial force to realize positive buffering.
2. inside and outside wing flap crosslinking apparatus as claimed in claim 1, it is characterised in that the piston cartridge module is in its middle inside
Provided with piston cylinder sawtooth, piston rod assembly two ends on the outside of it are provided with piston rod sawtooth, wherein, when the described first wedge shape is squeezed
When pressure surface is contacted with the second wedge shaped squeeze face, radial load is also produced, the piston cylinder sawtooth and the piston rod are sawed
Tooth is held tightly, is realized reverse locked.
3. inside and outside wing flap crosslinking apparatus as claimed in claim 2, it is characterised in that the piston cartridge module is three pieces of separate types
The piston cartridge module of middle part evagination, the piston cartridge module has elastomeric radial ability.
4. the inside and outside wing flap crosslinking apparatus as described in any one in claim 1-3, it is characterised in that the inside and outside wing flap
Crosslinking apparatus also includes：
Axial stroke retainer, the axial stroke retainer is fixed on the outside of the piston cartridge module；
Detection sensor, the detection sensor is fixed on the axial stroke retainer；
Target, the target is fixed on the recessed circle；
Wherein, when the distance between the detection sensor and the target are less than predetermined threshold, the detection sensor hair
Go out electric signal to realize that overtravel is detected.
5. inside and outside wing flap crosslinking apparatus as claimed in claim 4, it is characterised in that
The axial stroke retainer also includes the first axial retention shock surface；
The recessed circle also includes the second axial retention shock surface；
When the first axial retention shock surface is contacted with the second axial retention shock surface, positive stop is realized.
6. the inside and outside wing flap crosslinking apparatus as described in any one in claim 1-3, it is characterised in that the inside and outside wing flap
Crosslinking apparatus also includes the radial direction pad being arranged between the arc wedge and the piston cartridge module, to realize arc wedge
Shape part compressive plane external diameter is adjusted.
7. the inside and outside wing flap crosslinking apparatus as described in any one in claim 1-3, it is characterised in that the inside and outside wing flap
Crosslinking apparatus also includes the axial pad being arranged between the recessed circle and the piston rod assembly, to realize that free travel is adjusted
Section.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710643247.9A CN107161325B (en) | 2017-07-31 | 2017-07-31 | Inside and outside wing flap crosslinking apparatus |
| PCT/CN2017/117727 WO2019024398A1 (en) | 2017-07-31 | 2017-12-21 | Coupling device for inner and outer flaps |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710643247.9A CN107161325B (en) | 2017-07-31 | 2017-07-31 | Inside and outside wing flap crosslinking apparatus |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107161325A true CN107161325A (en) | 2017-09-15 |
| CN107161325B CN107161325B (en) | 2018-09-11 |
Family
ID=59817650
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710643247.9A Active CN107161325B (en) | 2017-07-31 | 2017-07-31 | Inside and outside wing flap crosslinking apparatus |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN107161325B (en) |
| WO (1) | WO2019024398A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019024398A1 (en) * | 2017-07-31 | 2019-02-07 | 中国商用飞机有限责任公司 | Coupling device for inner and outer flaps |
| CN112678151A (en) * | 2021-01-13 | 2021-04-20 | 中国商用飞机有限责任公司 | Device for cross-linking between flaps |
| CN113291458A (en) * | 2021-06-25 | 2021-08-24 | 庆安集团有限公司 | Inner and outer flap cross-linking device for high-lift system of airplane |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3505839A1 (en) * | 1985-02-20 | 1986-08-21 | Messerschmitt-Bölkow-Blohm GmbH, 2800 Bremen | Failure protection device for flap systems on aircraft mainplanes |
| DE3522449A1 (en) * | 1985-06-22 | 1987-01-02 | Messerschmitt Boelkow Blohm | Damping element |
| CN101432546A (en) * | 2006-05-03 | 2009-05-13 | 空中客车德国有限公司 | Interconnecting strut for arranging between adjacent landing flaps of an aircraft |
| CN102712358A (en) * | 2009-11-05 | 2012-10-03 | 空中客车运作有限责任公司 | A wing of an aircraft |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4336868A (en) * | 1978-05-10 | 1982-06-29 | Textron, Inc. | Composite fibrous tube energy absorber |
| CN107161325B (en) * | 2017-07-31 | 2018-09-11 | 中国商用飞机有限责任公司 | Inside and outside wing flap crosslinking apparatus |
-
2017
- 2017-07-31 CN CN201710643247.9A patent/CN107161325B/en active Active
- 2017-12-21 WO PCT/CN2017/117727 patent/WO2019024398A1/en active Application Filing
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3505839A1 (en) * | 1985-02-20 | 1986-08-21 | Messerschmitt-Bölkow-Blohm GmbH, 2800 Bremen | Failure protection device for flap systems on aircraft mainplanes |
| DE3522449A1 (en) * | 1985-06-22 | 1987-01-02 | Messerschmitt Boelkow Blohm | Damping element |
| CN101432546A (en) * | 2006-05-03 | 2009-05-13 | 空中客车德国有限公司 | Interconnecting strut for arranging between adjacent landing flaps of an aircraft |
| CN102712358A (en) * | 2009-11-05 | 2012-10-03 | 空中客车运作有限责任公司 | A wing of an aircraft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019024398A1 (en) * | 2017-07-31 | 2019-02-07 | 中国商用飞机有限责任公司 | Coupling device for inner and outer flaps |
| CN112678151A (en) * | 2021-01-13 | 2021-04-20 | 中国商用飞机有限责任公司 | Device for cross-linking between flaps |
| CN112678151B (en) * | 2021-01-13 | 2022-04-01 | 中国商用飞机有限责任公司 | Device for cross-linking between flaps |
| CN113291458A (en) * | 2021-06-25 | 2021-08-24 | 庆安集团有限公司 | Inner and outer flap cross-linking device for high-lift system of airplane |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2019024398A1 (en) | 2019-02-07 |
| CN107161325B (en) | 2018-09-11 |
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Effective date of registration: 20190821 Address after: 201210 Zhang Yang Road, Shanghai, Pudong New Area, No. 25 Co-patentee after: Shanghai Aircraft Design Research Institute Co.,Ltd. Patentee after: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Ltd. Address before: 201210 Zhang Yang Road, Shanghai, Pudong New Area, No. 25 Co-patentee before: COMAC SHANGHAI AIRCRAFT DESIGN & Research Institute Patentee before: Commercial Aircraft Corporation of China, Ltd. |
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