CN111003152B - Airplane control surface front edge sealing device - Google Patents
Airplane control surface front edge sealing device Download PDFInfo
- Publication number
- CN111003152B CN111003152B CN201911358802.9A CN201911358802A CN111003152B CN 111003152 B CN111003152 B CN 111003152B CN 201911358802 A CN201911358802 A CN 201911358802A CN 111003152 B CN111003152 B CN 111003152B
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- plate
- edge
- sealing
- control surface
- movable flange
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Sealing Devices (AREA)
Abstract
The embodiment of the application discloses a front edge sealing device of an aircraft control surface, which comprises the following components: a bi-directional sealing platen, a support platen and a fastener; the bidirectional sealing pressing plate comprises a fixed edge plate, an outer movable edge plate and an inner movable edge plate, and the fixed edge plate is arranged on the rear edge skin of the fixed airfoil surface through a supporting pressing plate and a fastener; the cross sections of the fixed flange plate, the external movable flange plate and the internal movable flange plate are of a herringbone structure; the outer movable flange plate is positioned at the outer side of the front edge of the aircraft control surface, the inner movable flange plate is positioned at the front part of the front edge of the aircraft control surface, and at least one of the outer movable flange plate and the inner movable flange plate is in sealing contact with the front edge of the control surface in the two-way sealing pressing plate. The embodiment of the application solves the pneumatic sealing problem of the gap between the rear edge of the fixed airfoil surface and the front edge of the movable airfoil surface of the existing aircraft structure.
Description
Technical Field
The application relates to the technical field of aircraft structures, in particular to a front edge sealing device of an aircraft rudder surface.
Background
For the airfoil structure of the aircraft, a certain gap is required to be reserved between the rear edge of the fixed airfoil and the front edge of the movable airfoil due to the requirements of movement clearance, deformation coordination and the like. In most cases, these gaps can adversely affect aerodynamics and structural loading of the airfoil structure, and proper sealing of the gaps can be considered. At present, the above-mentioned area sealing structure design is not yet in good design scheme.
Disclosure of Invention
In order to solve the technical problems, the embodiment of the application provides an aircraft control surface front edge sealing device which is used for solving the pneumatic sealing problem of a gap between the rear edge of a fixed airfoil and the front edge of a movable airfoil of the existing aircraft structure.
The embodiment of the application provides a front edge sealing device of an aircraft rudder surface, which comprises the following components: a bi-directional sealing platen, a support platen and a fastener;
the bidirectional sealing pressing plate comprises a fixed edge plate, an outer movable edge plate and an inner movable edge plate, and the fixed edge plate is arranged on the rear edge skin of the fixed airfoil surface through a supporting pressing plate and a fastener; the cross sections of the fixed flange plate, the external movable flange plate and the internal movable flange plate are of a herringbone structure;
the outer movable flange plate is positioned at the outer side of the front edge of the control surface of the aircraft, the inner movable flange plate is positioned at the front position of the front edge of the control surface of the aircraft, and at least one of the outer movable flange plate and the inner movable flange plate is in sealing contact with the front edge of the control surface in the two-way sealing pressing plate.
Optionally, in the aircraft control surface front edge sealing device as described above, the bidirectional sealing pressure plate further includes an internal bracket disposed between the fixed edge plate and the external movable edge plate, and having a trapezoid cross section, and the internal bracket is of a cavity structure.
Optionally, in the aircraft control surface leading edge sealing device described above, ends of the outer movable flange plate and the inner movable flange plate are provided in a bent structure.
Optionally, in the aircraft rudder surface edge sealing device as described above, the support platen includes: the fixed pressing plate is used for installing the fixed edge plate on the trailing edge skin of the fixed airfoil surface, and the cavity inner wall pressing plate is used for fixing the inner bracket.
Optionally, in the aircraft rudder surface edge sealing device as described above, the device further includes: the end baffles are arranged at two sides of the inner support in one-to-one correspondence, and the end baffles are provided with air leakage damping holes.
Optionally, in the aircraft control surface front edge sealing device as described above, the fixed edge plate of the bidirectional sealing pressure plate is bonded with the fixed pressure plate of the supporting pressure plate through colloid sealing.
Optionally, in the aircraft control surface leading edge sealing device, as described above, the outer surface of the bidirectional sealing pressing plate is paved with reinforcing fibers.
Optionally, in the aircraft control surface leading edge sealing device as described above, the aircraft control surface leading edge sealing device is configured to seal the control surface leading edge by the outer movable flange when the outer movable flange is subjected to pressure, and is further configured to seal the control surface leading edge by the inner movable flange when the inner movable flange is subjected to suction.
According to the airplane control surface front edge sealing device provided by the embodiment of the application, a sealing structure in a bidirectional aerodynamic bearing mode is adopted, a bidirectional sealing pressing plate is designed on one side of the control surface front edge, an external movable edge plate mainly bears pneumatic pressure, an internal movable edge plate mainly bears pneumatic suction, and a good pneumatic sealing effect is achieved through the sealing structure; the structure details of preventing the sealing element from reversely bending caused by the rotation of the control surface are adopted, an outward inflection structure is arranged at the end head of each sealing edge plate, the sealing edge plates can be well attached to the control surface in the forward direction, and the pressing plates can be restrained from curling due to friction in the reverse direction; the special trapezoid cavity sealing structure is adopted, so that the self rigidity of the sealing piece is improved, mutual support between two-way sealing pressing plates is established through the trapezoid cavity structure form, and the integrity of the sealing structure is improved; the sealing element is installed by adopting a sealing element installation mode of local bidirectional displacement limitation and the like, and the sealing element is installed by adopting low-viscosity glue and a contact type limiting pressing plate, so that a better supporting effect of a sealing structure is obtained. The sealing device provided by the embodiment of the application has the advantages of simple structural member manufacturing and assembling scheme, easiness in operation and good maintainability.
Drawings
The accompanying drawings are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate and do not limit the application.
Fig. 1 is a schematic structural diagram of a sealing device for the front edge of an aircraft control surface according to an embodiment of the present application;
FIG. 2 is a cross-sectional view of the aircraft rudder surface edge sealing device shown in FIG. 1;
fig. 3 is a schematic view of a use state of an aircraft control surface leading edge sealing device according to an embodiment of the present application.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present application more apparent, embodiments of the present application will be described in detail hereinafter with reference to the accompanying drawings. It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be arbitrarily combined with each other.
In the prior art, a sealing mode of a gap between the rear edge of a fixed airfoil surface and the front edge of a movable airfoil surface of an aircraft structure is usually a one-way sealing pressing plate, and most of the sealing modes are an external sealing pressing plate mode, and mainly bear pneumatic pressure load.
In addition, in the general scheme, the end head of the sealing pressing plate does not adopt inflection design or adopts inward inflection scheme, so that the control surface is easy to cause reverse curling when rotating, and the sealing structure is damaged accidentally and the like.
The following specific embodiments may be combined with each other, and some embodiments may not be repeated for the same or similar concepts or processes.
Fig. 1 is a schematic structural diagram of a sealing device for the front edge of an aircraft control surface according to an embodiment of the present application. The aircraft rudder surface edge sealing device provided in this embodiment may include: a bi-directional sealing pressure plate 1, a supporting pressure plate 2 and a fastener.
In the structure of the aircraft rudder surface front edge sealing device shown in fig. 1, a bidirectional sealing pressure plate 1 comprises a fixed edge plate 11, an outer movable edge plate 12 and an inner movable edge plate 13, wherein the fixed edge plate is arranged on a rear edge skin 3 of a fixed airfoil surface through a supporting pressure plate 2 and a fastener; wherein the cross sections of the fixed flange plate 11, the external movable flange plate 12 and the internal movable flange plate 13 are in a herringbone structure; as shown in fig. 2, which is a cross-sectional view of the aircraft rudder surface sealing device shown in fig. 1, a cross-section of the chevron configuration is illustrated in fig. 2.
In the sealing device for the front edge of the aircraft control surface, the outer movable flange plate 12 is positioned at the outer side of the front edge of the aircraft control surface, the inner movable flange plate 13 is positioned at the front position of the front edge of the aircraft control surface, and at least one of the outer movable flange plate 12 and the inner movable flange plate 13 is in sealing contact with the front edge of the control surface in the bidirectional sealing pressing plate 1.
Optionally, in the sealing device provided by the embodiment of the present application, the bidirectional sealing pressing plate 1 further includes an inner support 14 disposed between the fixed edge plate 11, the outer movable edge plate 12 and the inner movable edge plate 13, and the cross section of the inner support is trapezoidal, and the inner support may be configured as a cavity structure, such as a trapezoidal cavity 14 shown in fig. 2.
Alternatively, the ends of the outer and inner movable flanges 12, 13 in the embodiment of the present application may be provided in a bent structure.
Optionally, as shown in fig. 2, the support platen 2 in the embodiment of the present application may include: a fixing pressure plate 21 for mounting the fixing rim plate 11 on the trailing edge skin 3 of the fixing airfoil, and a cavity inner wall pressure plate 22 for fixing the inner bracket 14.
Optionally, in the sealing device provided by the embodiment of the present application, the sealing device may further include: the end baffles are arranged at two sides of the internal support 14 in a one-to-one correspondence manner, and the end baffles are provided with air leakage damping holes.
Optionally, the fixing edge plate 11 of the bidirectional sealing pressing plate 1 and the fixing pressing plate 21 of the supporting pressing plate 2 are adhered by glue sealing in the embodiment of the application.
Optionally, the outer surface of the bi-directional sealing platen in the inventive embodiment is laid with reinforcing fibers.
Optionally, the sealing device provided in the embodiment of the present application is used in a manner that when the outer movable flange 12 bears pressure, the front edge of the control surface is sealed by the outer movable flange 12, and when the inner movable flange 13 bears suction, the front edge of the control surface is sealed by the inner movable flange 13. Fig. 3 is a schematic view of a use state of the aircraft rudder surface edge sealing device according to the embodiment of the application.
The embodiment of the application provides a sealing device for the front edge of an aircraft control surface, in particular to a sealing structure, which comprises a herringbone bidirectional sealing pressing plate 1 with a cavity, a supporting pressing plate 2 and a fixed airfoil surface trailing edge skin 3. The double-sided sealing pressing plate 1 with the cavity is composed of the three edge plates, one cavity, end baffles with air leakage damping holes on two sides and the like, wherein the three edge plates are respectively a fixed edge plate 11 connected by fasteners, an external movable edge plate 12 with inflection and an internal movable edge plate 13 with inflection, the end baffles on two sides can be bonded on a main sealing element in a back bonding mode, in order to ensure that the edge plates have enough rigidity, reinforcing fiber materials can be paved on the outer surfaces of the sealing elements, and friction resistance reduction surface treatment can be carried out on a motion friction surface in order to reduce friction loss of the sealing elements.
The support pressure plate 2 in the embodiment of the application provides internal support for the sealing element and comprises a fixed pressure plate 21 and a cavity inner wall pressure plate 22; the stationary airfoil trailing edge skin 3 provides external support for the seal, including support for the stationary portion and the outer wall of the cavity.
According to the airplane control surface front edge sealing device provided by the embodiment of the application, the two movable edge plates of the inverted V-shaped bidirectional sealing pressing plate 1 with the cavity are contacted with the control surface front edge skin 3, so that bidirectional pneumatic sealing of the control surface front edge is realized; the installation and the support of the inverted-Y-shaped bidirectional sealing pressing plate 1 with the cavity are realized through the supporting pressing plate 2 and the fixed airfoil surface trailing edge skin 3.
According to the airplane control surface front edge sealing device provided by the embodiment of the application, when the airplane control surface front edge sealing device is installed, the bidirectional sealing pressing plate 1 and the supporting pressing plate 2 are adhered through low-viscosity glue according to the figure 2, then the assembly of the bidirectional sealing pressing plate 1 and the supporting pressing plate 2 is positioned strictly according to the design position, the assembly is adhered under the fixed airfoil surface rear edge skin 3 through the low-viscosity glue, finally a fastener hole is formed, a fastener is installed, the supporting pressing plate 2 and the fixed airfoil surface rear edge skin 3 are required to be pressed when the fastener hole is formed, and glue opening or structural damage is prevented.
When the sealing structure (namely the airplane control surface front edge sealing device) in the embodiment of the application is used, as shown in fig. 3, the control surface front edge skin extrudes two movable pressing plates (an outer movable edge plate 12 with inflection and an inner movable edge plate 13 with inflection) of the herringbone bidirectional sealing pressing plate 1, the outer tension of the movable pressing plates is in a compression state, the state (1) in fig. 3 is a control surface neutral position, the state (2) is a control surface upward deviation position, and the state (3) is a control surface downward deviation position; when the double-side pneumatic seal is adopted, the effect is better, when the sealing position is pneumatic suction, the outer movable flange plate 12 is subjected to partial load and then outwards generates displacement, partial aerodynamic force is transferred to the inner movable flange plate 13, and the inner movable flange plate 13 is tightly pressed on the front edge skin 3 of the control surface; when the sealing position is pneumatic pressure, the external movable flange plate 12 bears all the load, the external movable flange plate 12 is pressed on the front edge skin 3 of the control surface, and the phenomenon that the end head is separated from the front edge skin of the control surface is not required to occur when the movable pressing plate bears pneumatic pressure; however, when a single-sided pneumatic seal is used, the load of each movable platen under pneumatic pressure will be superimposed, requiring a stiffer seal.
When the sealing structure is required to be disassembled, all the fasteners are disassembled firstly, then the glue joint of the bidirectional sealing pressing plate 1 and the fixed airfoil surface trailing edge skin 3 is torn, and finally the glue joint of the bidirectional sealing pressing plate 1 and the supporting pressing plate 2 is torn off, and the adoption of the low-viscosity glue is used for providing enough support for the sealing element and also ensuring the requirements of easy installation and disassembly.
It should be noted that, for the aerodynamic gap between the front edge of the aircraft control surface and the rear edge of the fixed airfoil, the aerodynamic gap can locally reduce the aerodynamic efficiency of the control surface due to the motion requirement and structural design characteristics of the control surface, and meanwhile, turbulence can be generated, so that the structural vibration at the position is caused, fatigue cracks and other defects are generated, and the service life of the structure is reduced. Most airplanes adopt the reinforcing structure, improve fatigue resistance, and part of airplanes are subjected to pneumatic caulking seal design, and the main design scheme is that a single seal pressing plate is adopted and fixed on the rear edge of a fixed airfoil, and a sealing piece is elastically pressed outside the skin of the front edge of a control surface.
According to the airplane control surface front edge sealing device provided by the embodiment of the application, a sealing structure in a bidirectional aerodynamic bearing mode is adopted, a bidirectional sealing pressing plate is designed on one side of the control surface front edge, an external movable edge plate mainly bears pneumatic pressure, an internal movable edge plate mainly bears pneumatic suction, and a good pneumatic sealing effect is achieved through the sealing structure; in addition, the embodiment of the application adopts structural details for preventing the sealing element from reversely bending caused by the rotation of the control surface, an outward inflection structure is arranged at the end head of each sealing edge plate, the sealing edge plates can be well attached to the control surface in the forward direction, and the pressing plate can be restrained from curling due to friction in the reverse direction.
Furthermore, the embodiment of the application adopts a special trapezoid cavity sealing structure, so that the self rigidity of the sealing element is improved, the mutual support between the two-way sealing pressing plates is established through the trapezoid cavity structure form, and the integrity of the sealing structure is improved; furthermore, the embodiment of the application adopts a sealing element installation mode of partial bidirectional displacement limitation and the like, and adopts low-viscosity glue and a contact type limiting pressing plate to install the sealing element, so that a better supporting effect of the sealing structure is obtained.
The sealing device provided by the embodiment of the application has the advantages of simple structural part manufacturing and assembling scheme, easy operation and good maintainability; the sealing structure is suitable for sealing the gap between the rear edge of the fixed airfoil surface and the front edge of the movable airfoil surface of the aircraft structure.
The sealing device provided by the embodiment of the application can effectively solve the pneumatic sealing problem of the rear edge structure of the fixed airfoil and the front edge of the control surface structure, improve the pneumatic performance of the whole airfoil, effectively improve the air flow disturbance environment of the rear edge cabin of the fixed airfoil and the front edge cabin of the control surface, reduce the structural vibration fatigue load and the like. By the scheme of the embodiment of the application, the bidirectional pneumatic load bearing capacity of the sealing structure can be realized; providing more reliable sealing structure connection and support; avoiding accidental damage during the use process as much as possible; maintaining a seal structure of sufficient overall rigidity, etc.
Although the embodiments of the present application are described above, the embodiments are only used for facilitating understanding of the present application, and are not intended to limit the present application. Any person skilled in the art can make any modification and variation in form and detail without departing from the spirit and scope of the present disclosure, but the scope of the present disclosure is to be determined by the appended claims.
Claims (4)
1. An aircraft rudder surface leading edge sealing device, comprising: a bi-directional sealing platen, a support platen and a fastener;
the bidirectional sealing pressing plate comprises a fixed edge plate, an outer movable edge plate and an inner movable edge plate, and the fixed edge plate is arranged on the rear edge skin of the fixed airfoil surface through a supporting pressing plate and a fastener; the cross sections of the fixed flange plate, the external movable flange plate and the internal movable flange plate are of a herringbone structure; the bidirectional sealing pressing plate is arranged on one side of the front edge of the control surface, mainly bears pneumatic pressure through the outer movable flange plate, and mainly bears pneumatic suction through the inner movable flange plate;
the outer movable flange plate is positioned at the outer side of the front edge of the control surface of the aircraft, the inner movable flange plate is positioned at the front part of the front edge of the control surface of the aircraft, and at least one of the outer movable flange plate and the inner movable flange plate is in sealing contact with the front edge of the control surface in the two-way sealing pressing plate;
when the sealing position is pneumatic suction, the outer movable flange plate is subjected to partial load and then outwards generates displacement, partial aerodynamic force is transferred to the inner movable flange plate, and the inner movable flange plate is pressed on the front edge skin of the control surface; when the sealing position is pneumatic pressure, the external movable flange plate bears all the load, and the external movable flange plate is tightly pressed on the skin at the front edge of the control surface;
the ends of the outer movable flange plate and the inner movable flange plate are provided with bending structures, the outer movable flange plate and the inner movable flange plate can be well attached to a control surface in the forward direction, and the pressing plate can be restrained from being curled due to friction in the reverse direction;
the bidirectional sealing pressing plate further comprises an inner support which is arranged between the fixed edge plate and the outer movable edge plate and has a trapezoid cross section, and the inner support is of a cavity structure;
the support platen includes: a fixed pressure plate for mounting the fixed edge plate on the trailing edge skin of the fixed airfoil, and a cavity inner wall pressure plate for fixing the inner bracket;
the fixed edge plate of the two-way sealing pressing plate is bonded with the fixed pressing plate of the supporting pressing plate through colloid sealing.
2. The aircraft control surface leading edge sealing device of claim 1, further comprising: the end baffles are arranged at two sides of the inner support in one-to-one correspondence, and the end baffles are provided with air leakage damping holes.
3. The aircraft control surface leading edge sealing device of claim 1, wherein the outer surface of the bi-directional sealing platen is laid with reinforcing fibers.
4. The aircraft control surface leading edge sealing device of any of claims 1-3, wherein the aircraft control surface leading edge sealing device is configured to seal the control surface leading edge with an outer moving blade when the outer moving blade is subjected to pressure, and is further configured to seal the control surface leading edge with an inner moving blade when the inner moving blade is subjected to suction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911358802.9A CN111003152B (en) | 2019-12-25 | 2019-12-25 | Airplane control surface front edge sealing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911358802.9A CN111003152B (en) | 2019-12-25 | 2019-12-25 | Airplane control surface front edge sealing device |
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| Publication Number | Publication Date |
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| CN111003152A CN111003152A (en) | 2020-04-14 |
| CN111003152B true CN111003152B (en) | 2023-10-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911358802.9A Active CN111003152B (en) | 2019-12-25 | 2019-12-25 | Airplane control surface front edge sealing device |
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| CN (1) | CN111003152B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114993599B (en) * | 2022-05-31 | 2023-02-24 | 上海交通大学 | Wind tunnel test model for verifying influence of wing trailing edge cabin gap on vibration characteristic of wing trailing edge cabin gap |
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| US4042191A (en) * | 1976-05-03 | 1977-08-16 | The Boeing Company | Slot seal for leading edge flap |
| CN102137792A (en) * | 2008-09-01 | 2011-07-27 | 空中客车操作有限公司 | Seal for sealing a gap between a first and a second component of an aircraft flight surface |
| GB2545431A (en) * | 2015-12-15 | 2017-06-21 | Airbus Operations Ltd | Seal |
| CN108146616A (en) * | 2016-12-02 | 2018-06-12 | 中国航空工业集团公司成都飞机设计研究所 | A kind of rudder face seal structure of all-metal Varying-thickness |
| CN108454826A (en) * | 2017-02-22 | 2018-08-28 | 空中客车运营简化股份公司 | Flexible seals for aircraft |
| CN108609158A (en) * | 2016-12-12 | 2018-10-02 | 中国航空工业集团公司成都飞机设计研究所 | A kind of passive servo-actuated seal structure |
| CN110001925A (en) * | 2017-12-21 | 2019-07-12 | 空中客车营运有限公司 | Sealing plate for aerodynamic surface |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2827028B1 (en) * | 2001-07-06 | 2003-09-26 | Airbus France | AIRCRAFT WITH VENTRAL CARENAGE AND JOINT FOR SUCH AN AIRCRAFT |
| ES2277715B1 (en) * | 2004-12-31 | 2008-05-16 | Airbus España, S.L. | REINFORCED COVER FOR SCOTS IN AN AERODYNAMIC CONTOUR. |
| DE102007020870A1 (en) * | 2007-05-04 | 2008-11-13 | Airbus Deutschland Gmbh | High-lift system on the wing of an aircraft |
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Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4042191A (en) * | 1976-05-03 | 1977-08-16 | The Boeing Company | Slot seal for leading edge flap |
| CN102137792A (en) * | 2008-09-01 | 2011-07-27 | 空中客车操作有限公司 | Seal for sealing a gap between a first and a second component of an aircraft flight surface |
| GB2545431A (en) * | 2015-12-15 | 2017-06-21 | Airbus Operations Ltd | Seal |
| CN108146616A (en) * | 2016-12-02 | 2018-06-12 | 中国航空工业集团公司成都飞机设计研究所 | A kind of rudder face seal structure of all-metal Varying-thickness |
| CN108609158A (en) * | 2016-12-12 | 2018-10-02 | 中国航空工业集团公司成都飞机设计研究所 | A kind of passive servo-actuated seal structure |
| CN108454826A (en) * | 2017-02-22 | 2018-08-28 | 空中客车运营简化股份公司 | Flexible seals for aircraft |
| CN110001925A (en) * | 2017-12-21 | 2019-07-12 | 空中客车营运有限公司 | Sealing plate for aerodynamic surface |
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| Publication number | Publication date |
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| CN111003152A (en) | 2020-04-14 |
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