CN107161325B - Inner and outer flap cross-linking device - Google Patents
Inner and outer flap cross-linking device Download PDFInfo
- Publication number
- CN107161325B CN107161325B CN201710643247.9A CN201710643247A CN107161325B CN 107161325 B CN107161325 B CN 107161325B CN 201710643247 A CN201710643247 A CN 201710643247A CN 107161325 B CN107161325 B CN 107161325B
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- piston
- wedge
- wing flap
- cartridge module
- outside
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- 238000004132 cross linking Methods 0.000 title claims abstract description 45
- 230000003139 buffering effect Effects 0.000 claims abstract description 6
- 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 7
- 230000000694 effects Effects 0.000 abstract description 8
- 238000009434 installation Methods 0.000 abstract description 7
- 238000012423 maintenance Methods 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 abstract 1
- 238000001125 extrusion Methods 0.000 abstract 1
- 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
- 238000011176 pooling Methods 0.000 description 3
- 229910000883 Ti6Al4V Inorganic materials 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000002929 anti-fatigue Effects 0.000 description 1
- 238000010668 complexation reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 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
- 235000013399 edible fruits Nutrition 0.000 description 1
- 238000007689 inspection Methods 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)
- Fluid-Damping Devices (AREA)
- Actuator (AREA)
- Vibration Dampers (AREA)
Abstract
The invention relates to an inner and outer flap cross-linking device. The inner and outer flap cross-linking device comprises: a piston cylinder assembly; a piston rod assembly disposed within the piston cylinder assembly and radially fixed and axially movable relative to the piston cylinder assembly; an arcuate wedge secured to an outer side of the piston barrel assembly, the arcuate wedge including a first wedge pressing surface; a female ring secured to an outer side of the piston rod assembly, the female ring including a second wedge-shaped extrusion surface; when the first wedge-shaped pressing surface is in contact with the second wedge-shaped pressing surface, an axial force is generated to realize positive buffering. The inner flap and outer flap cross-linking device of the invention can achieve the following beneficial technical effects: the over-travel forward buffering function can be realized, the structure is simple, and the installation and the maintenance are easy.
Description
Technical field
The present invention relates to inside and outside wing flap crosslinking apparatus.
Background technology
Due to being limited by airport runway length, gear tyre speed and in order to improve takeoff and landing safety,
High-lift device is able to continue to develop in the design of modern large aircraft and extensive use.It is arranged in the height essence in trailing edge cabin
Close and complicated motion and drive system realizes high-lift aerofoil freely converting between each aerodynamic configuration/screens.
Drive system generally transmits linear system by power take-off unit, torque and high transmission ratio power/torque output actuator forms, actuator
Main Force transmission parts are generally the high-quality steel of high intensity and are machined into, and have a higher durability mechanical performance, but it is antifatigue and
Initial imperfection crack propagation performance is poor.Actuator, ground maintenance people are not dismantled and decomposed during airplane operation
Member can not carry out effective damage inspection to it.Airworthiness regulation requires in the design to be subject to the single failure of such system
Consider (and no matter how low its fault rate is), aircraft still has continuation safe flight and landing after must ensuring the system failure
Ability.
Every piece of trailing edge flap generally has more than two drive rams, when wherein a certain actuator occurs to disengage failure
When, aerofoil will generate and largely tilt (being mainly shown as the tangential movement of aerofoil end rib), when this deformation displacement is excessive,
Both sides wing will generate the rolling moment beyond airplane trim ability, to interfere flight safety.It is arranged between inside and outside wing flap
One, along the i.e. inside and outside wing flap crosslinking apparatus of the tangential single-degree-of-freedom actuator of wing flap, can play reduction failure aerofoil over-tilting and carry
For the effect of aerofoil auxiliary constraint, and then ensures after the system failure that aircraft still has and continue safe flight and throwing power.
However, the inside and outside wing flap crosslinking apparatus general structure of the prior art is complex, and installation maintenance is inconvenient.
Invention content
It is an object of the present invention to overcome the defect of existing inside and outside wing flap crosslinking apparatus, provide a kind of new inside and outside
Wing flap crosslinking apparatus can realize overtravel forward direction pooling feature, and simple in structure, and installation maintenance is 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 packet
It includes：
Piston cartridge module；
Piston rod assembly, the piston rod assembly are set in the piston cartridge module, and relative to the piston cylinder group
Part is radially fixed, is axially moveable；
Arc wedge piece, the arc wedge piece are fixed on the outside of the piston cartridge module, the arc wedge piece
Including the first wedge-shaped compressive plane；
Recessed circle, the recessed circle are 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 second wedge shaped squeeze face, it is positive slow to realize to generate axial force
Punching.
According to above-mentioned technical proposal, inside and outside wing flap crosslinking apparatus of the invention can play following advantageous effects：It can be real
Existing overtravel forward direction pooling feature, and it is simple in structure, and installation maintenance is easy.
It is preferred that the piston cartridge module is equipped with piston cylinder sawtooth in its middle inside, the piston rod assembly is at it
Outside both ends are equipped with piston rod sawtooth, wherein when the described first wedge-shaped compressive plane is contacted with second wedge shaped squeeze face, also
Radial load is generated, 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：It 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 further includes：
Axial stroke retainer, the axial stroke retainer are fixed on the outside of the piston cartridge module；
Detection sensor, the detection sensor are fixed on the axial stroke retainer；
Target, the target are 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 out electric signal to realize that overtravel detects.
According to above-mentioned technical proposal, inside and outside wing flap crosslinking apparatus of the invention can play following advantageous effects：It can be real
Existing overtravel detecting function.
It is preferred that the axial stroke retainer further includes first axis stop shock surface；
The recessed circle further includes the second axial retention shock surface；
When the first axis stop shock surface and the second axial retention shock surface contact, 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：It can be real
Existing overtravel forward direction locking function.
It is preferred that the inside and outside wing flap crosslinking apparatus further includes being set to the arc wedge piece and the piston cylinder group
Radial gasket between part, to realize that arc wedge piece compressive plane outer diameter is adjusted.
It is preferred that the inside and outside wing flap crosslinking apparatus further includes being set between the recessed circle and the piston rod assembly
Axial gasket, with realize free travel adjust.
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
1, piston rod assembly
2, piston cartridge module
3, arc wedge piece
4, recessed circle
5, detection sensor
6, target
7, the first wedge-shaped compressive plane
8, the second wedge shaped squeeze face
9, first axis stop shock surface
10, the second axial retention shock surface
11, piston cylinder sawtooth
12, piston rod sawtooth
13, axial stroke retainer
Specific implementation mode
The specific implementation mode of the present invention explained below, it should be pointed out that in the specific descriptions of these embodiments
In the process, in order to carry out brief and concise description, this specification can not possibly make in detail all features of actual embodiment
Most description.It is to be understood that during the actual implementation 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 is relevant or quotient
The relevant limitation of industry can usually make various specific decisions, and this can also be implemented from a kind of embodiment to another kind
It changes between mode.Moreover, it is to be understood that although effort made in this development process may be complicated
And it is interminable, however for for the relevant those skilled in the art of 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 as 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 technical field.Present patent application specification and power
" first ", " second " and the similar word used in sharp claim is not offered as any sequence, quantity or importance, and
It is used only to distinguish different component parts.The similar word such as "one" or " one " is not offered as quantity limitation, but indicates
There are at least one.Either the similar word such as "comprising" means to appear in the element before " comprising " or "comprising" " comprising "
Either object covers the element for appearing in " comprising " or "comprising" presented hereinafter or object and its equivalent element, it is not excluded that
Other elements or object." connection " either the similar word such as " connected " is not limited to physics or mechanical 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 Figs. 1-2, according to an exemplary rather than exclusive embodiment of the invention, inside and outside wing flap crosslinking apparatus packet
It includes：
Piston cartridge module 2；
Piston rod assembly 1, piston rod assembly 1 are set in piston cartridge module 2, and radial solid relative to piston cartridge module 2
Determine, be axially moveable；
Arc wedge piece 3, arc wedge piece 3 are fixed on the outside of piston cartridge module 2, and arc wedge piece 3 includes first
Wedge shaped squeeze face 7；
Recessed circle 4, recessed circle 4 are fixed on the outside of piston rod assembly 1, and recessed circle 4 includes the second wedge shaped squeeze face 8；
When the first 7 and second wedge shaped squeeze face 8 of wedge-shaped compressive plane contacts, axial force is generated to realize positive buffering.
In this way, the inside and outside wing flap crosslinking apparatus of the present invention can realize overtravel forward direction pooling feature, and simple in structure, peace
Dress, which is safeguarded, to be 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, two difference of inside and outside wing flap crosslinking apparatus
It is fixed on the variation that the distance between the installation point of inside and outside wing flap end rib will elongate or shorten, so as to cause piston rod assembly
1 stretches or compression movement in the axial direction relative to piston cartridge module 2.
It is preferred that inside and outside wing flap crosslinking apparatus further includes：
Axial stroke retainer 13, axial stroke retainer 13 are fixed on the outside of piston cartridge module 2；
Detection sensor 5, detection sensor 5 are fixed on axial stroke retainer 13；
Target 6, target 6 are 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 out telecommunications
It number is detected with the overtravel of two installation point distance of wing flap crosslinking apparatus inside and outside realization.
It is preferred that axial stroke retainer 13 further includes first axis stop shock surface 9；
Recessed circle 4 further includes the second axial retention shock surface 10；
When first axis stop shock surface 9 and the second axial retention shock surface 10 contact, positive stop is realized.
Specifically, when piston rod assembly 1 moves overtravel, detection sensing relative to piston cartridge module 2 along any direction
When the distance between device 5 and target 6 are less than predetermined threshold, detection sensor 5 will send out electric signal to realize that overtravel detects.It connects
It, the first wedge-shaped compressive plane 7 of arc wedge piece 3 is contacted with the second wedge shaped squeeze face 8 of recessed circle 4, axial force is generated, to realize
Positive (axial direction) buffering.Finally, the first axis stop shock surface 9 of axial stroke retainer 13 axially stops with the second of recessed circle 4
Dynamic shock surface 10 contacts, and realizes positive (axial direction) stop.
It is preferred that the inside and outside wing flap crosslinking apparatus axis of the present invention is substantially tangential along wing flap, rear end is installed on interior wing flap
End rib, front end are installed on outer wing flap end rib.Free movement travel limit in an axial direction needs to combine total travel many-body dynamics and have
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 range
The variation of distance between two installation points of inside and outside wing flap crosslinking apparatus caused by different gentle dynamic load effect, and inside and outside wing flap is crosslinked
Device must not interfere the normal use of wing flap.
It is preferred that piston cartridge module 2 is equipped with piston cylinder sawtooth 11 in its middle inside, piston rod assembly 1 is on the outside
Both ends are equipped 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 piece 3
When face 8 contacts, radial load is also generated, piston cylinder sawtooth 11 and piston rod sawtooth 12 are held tightly, realized reverse locked.
That is, the above preferred embodiment according to the present invention, inside and outside wing flap crosslinking apparatus is in addition to that can provide overtravel
The reverse locking function of overtravel can also be provided close to other than detection and positive buffering locking function in target.
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.
In this way, piston cylinder sawtooth 11 and piston rod sawtooth 12 can preferably be realized under radial load and be held tightly.
It is preferred that piston cartridge module 2 is the piston cartridge module of middle part evagination predeformation.
In this way, piston cartridge module 2 at middle part with certain convex shape and/or with certain predeformation, therefore, when
When the wedge-shaped compressive plane 7 of the first of arc wedge piece 3 and the second wedge shaped squeeze face 8 of recessed circle 4 contact, radial load is also generated, it 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 of high-strength metal material, such as by Ti-6Al-4V material systems
At.
It is preferred that piston cylinder sawtooth 11 and piston rod sawtooth 12 are made 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 other suitable materials can also be used, 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 further includes the diameter being set between arc wedge piece 3 and piston cartridge module 2
To gasket (such as metal strippable gasket), to realize that arc wedge piece compressive plane outer diameter is adjusted.
In this way, by installing (setting) radial gasket additional between arc wedge piece and piston cartridge module, arc wedge can be changed
The outer diameter of the wedge-shaped compressive plane of the first of shape part can preferably realize the outer field control of cushion performance.
It is preferred that inside and outside wing flap crosslinking apparatus further includes the axial gasket being set between recessed circle 4 and piston rod assembly 1
(such as metal gasket), to realize that free travel is adjusted.
In this way, by installing (setting) axial gasket additional between recessed circle and piston rod assembly, freedom can be preferably 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 substituted or supplemented by other component or its equivalent in different ways, then may be implemented suitably to tie
Fruit.Correspondingly, other embodiment is also fallen into scope of the claims.
Claims (6)
1. a kind of inside and outside wing flap crosslinking apparatus, including：
Piston cartridge module；
Piston rod assembly, the piston rod assembly are set in the piston cartridge module, and relative to the piston cartridge module diameter
To fixation, it is axially moveable；
Arc wedge piece, the arc wedge piece are fixed on the outside of the piston cartridge module, and the arc wedge piece includes
First wedge-shaped compressive plane；
Recessed circle, the recessed circle are 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 second wedge shaped squeeze face, axial force is generated to realize positive buffering；
Wherein, the piston cartridge module is equipped with piston cylinder sawtooth, piston rod assembly both ends on the outside in its middle inside
Equipped with piston rod sawtooth, wherein when the described first wedge-shaped compressive plane is contacted with second wedge shaped squeeze face, also generate radial
Power holds the piston cylinder sawtooth and the piston rod sawtooth tightly, realizes reverse locked.
2. inside and outside wing flap crosslinking apparatus as described in claim 1, which is characterized in that the piston cartridge module is three pieces of separate types
The piston cartridge module of middle part evagination, the piston cartridge module have elastomeric radial ability.
3. the inside and outside wing flap crosslinking apparatus as described in any one in claim 1-2, which is characterized in that the inside and outside wing flap
Crosslinking apparatus further includes：
Axial stroke retainer, the axial stroke retainer are fixed on the outside of the piston cartridge module；
Detection sensor, the detection sensor are fixed on the axial stroke retainer；
Target, the target are 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 detects.
4. inside and outside wing flap crosslinking apparatus as claimed in claim 3, which is characterized in that
The axial stroke retainer further includes first axis stop shock surface；
The recessed circle further includes the second axial retention shock surface；
When the first axis stop shock surface and the second axial retention shock surface contact, positive stop is realized.
5. the inside and outside wing flap crosslinking apparatus as described in any one in claim 1-2, which is characterized in that the inside and outside wing flap
Crosslinking apparatus further includes the radial gasket being set between the arc wedge piece and the piston cartridge module, to realize arc wedge
Shape part compressive plane outer diameter is adjusted.
6. the inside and outside wing flap crosslinking apparatus as described in any one in claim 1-2, which is characterized in that the inside and outside wing flap
Crosslinking apparatus further includes the axial gasket being set between the recessed circle and the piston rod assembly, to realize free travel tune
Section.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710643247.9A CN107161325B (en) | 2017-07-31 | 2017-07-31 | Inner and outer flap cross-linking device |
| 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 | Inner and outer flap cross-linking device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107161325A CN107161325A (en) | 2017-09-15 |
| CN107161325B true 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 | Inner and outer flap cross-linking device |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN107161325B (en) |
| WO (1) | WO2019024398A1 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107161325B (en) * | 2017-07-31 | 2018-09-11 | 中国商用飞机有限责任公司 | Inner and outer flap cross-linking device |
| 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 |
| CN113291458B (en) * | 2021-06-25 | 2024-07-19 | 庆安集团有限公司 | Inner and outer flap crosslinking device for high lift system of airplane |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4336868A (en) * | 1978-05-10 | 1982-06-29 | Textron, Inc. | Composite fibrous tube energy absorber |
| 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 |
| DE102006020554B4 (en) * | 2006-05-03 | 2011-06-16 | Airbus Operations Gmbh | Connecting strut for arrangement between adjacent flaps of an aircraft |
| DE102009051983A1 (en) * | 2009-11-05 | 2011-05-12 | Airbus Operations Gmbh | Wing of an airplane |
| CN107161325B (en) * | 2017-07-31 | 2018-09-11 | 中国商用飞机有限责任公司 | Inner and outer flap cross-linking device |
-
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
Also Published As
| Publication number | Publication date |
|---|---|
| CN107161325A (en) | 2017-09-15 |
| WO2019024398A1 (en) | 2019-02-07 |
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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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