CN112238933A - Sliding device for guiding movement of trailing edge flap of airplane - Google Patents
Sliding device for guiding movement of trailing edge flap of airplane Download PDFInfo
- Publication number
- CN112238933A CN112238933A CN202011102697.5A CN202011102697A CN112238933A CN 112238933 A CN112238933 A CN 112238933A CN 202011102697 A CN202011102697 A CN 202011102697A CN 112238933 A CN112238933 A CN 112238933A
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- roller set
- rollers
- longitudinal direction
- slide rail
- aircraft
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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
- B64C9/14—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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Automation & Control Theory (AREA)
- Bearings For Parts Moving Linearly (AREA)
Abstract
The invention relates to a sliding device for guiding the movement of a trailing edge flap of an aircraft, which is laid in the longitudinal direction of the aircraft fuselage and comprises: a slide and sheave bracket assembly having a pi cross-sectional shape, the slide comprising: a strip-shaped top plate extending along the longitudinal direction of the slide rail; two side plates spaced apart from each other and extending vertically downward from a bottom surface of the top plate; and two bottom plates respectively extending from the bottom ends of the two side plates and the top plate in parallel towards mutually opposite directions, wherein the top plate and the corresponding bottom plates and side plates respectively form a groove which is opened towards the outer side of the slide rail along the transverse direction of the slide rail, the pulley frame assembly can move on the slide rail along the longitudinal direction of the slide rail and comprises a first roller set and a second roller set which are installed on the pulley frame assembly, rollers in the first roller set can respectively roll in the groove along at least one surface of the groove, rollers in the second roller set can respectively roll along two side edges of the top plate which extend in the longitudinal direction, and the rollers of the first roller set and the second roller set are at least partially exposed.
Description
Technical Field
The invention relates to the field of aircraft manufacturing, in particular to a sliding device suitable for guiding the movement of a trailing edge flap of an aircraft.
Background
The sliding device used for the trailing edge flap of the aircraft of the C919 aircraft comprises a pulley frame assembly and a sliding track. The slide rail comprises a substantially rectangular top plate and two L-shaped supporting webs, which are connected to the underside of the top plate at the free ends of the L-shaped vertical limbs, respectively, on the underside of the top plate, so that a slide rail with a pi-shaped cross section is formed, which can be connected at one end in the longitudinal direction to a slide rail support device, while the pulley carrier assembly is connected to the flap torsion tube. The sheave frame assembly comprises two middle rollers 100 and four side rollers 200 by means of which the sheave frame assembly can slide on the slide rail in the longitudinal direction of the pi-shaped slide rail. In this regard, the sheave bracket assembly transfers the load from the flap to the slide and then to the aircraft via the slide support. Wherein the middle roller 100 transmits a lateral component of the load and the side rollers 200 transmit a vertical component of the load. In this prior art, when a rail having a pi-shaped cross section is mounted with a sheave frame assembly, the idler 100 is located between two support webs of the pi-shaped rail and is thus hidden inside the rail, which makes maintenance and inspection of the idler difficult. Whereby the post-maintenance costs are high. Wherein figure 6 illustrates the arrangement of the center and side rollers of a prior art sheave frame assembly.
Disclosure of Invention
In view of the sliding device for guiding the motion of the flap at the trailing edge of the airplane in the prior art, the invention aims to provide an improved sliding device for guiding the motion of the flap at the trailing edge of the airplane, which improves the arrangement mode of the roller, can effectively reduce the maintenance difficulty of the roller, improves the wear resistance of the roller, and effectively transmits the load of the flap of the airplane to the sliding rail and further to the airplane. In addition, the sliding device is simple in structural form, compact in arrangement and capable of saving installation space.
This object is achieved by the invention of a slider for guiding the movement of a trailing edge flap of an aircraft, which slider runs in the longitudinal direction of the aircraft fuselage and comprises:
a slide rail having a pi cross-sectional shape, the slide rail comprising:
the long-strip-shaped top plate extends along the longitudinal direction of the slide rail;
two side plates spaced apart from each other and extending vertically downward from a bottom surface of the top plate; and
two bottom plates respectively extending from bottom ends of the two side plates in parallel with the top plate in opposite directions to each other,
wherein the top plate and the corresponding bottom plate and side plate respectively form a groove which is opened towards the outer side of the slide rail along the transverse direction of the slide rail,
a sheave frame assembly configured to be movable on the slide rail in a longitudinal direction of the slide rail, wherein the sheave frame assembly includes a first roller set and a second roller set mounted thereon,
the rollers of the first roller set are arranged to be capable of rolling in the groove along at least one surface of the groove, respectively, and the rollers of the second roller set are arranged to be capable of rolling along two side edges of the top plate extending in the longitudinal direction, respectively, and the rollers of the first roller set and the second roller set are at least partially exposed.
Compared with the arrangement mode of hiding the middle roller in the slide rail in the prior art, the sliding device at least partially exposes the rollers of the first roller group and the second roller group, so that all the rollers are arranged in the area easy to check, the maintenance difficulty of the rollers is effectively reduced, and the cost for part manufacturing and maintenance is saved.
According to a preferred embodiment of the invention, the rollers of the first roller group roll in the groove on the lower surface of the top plate and/or the upper surface of the bottom plate.
According to the slider for guiding the movement of an aircraft trailing edge flap according to the invention, the lateral component of the load of the aircraft flap is transferred to the slide rail by rolling the rollers of the first roller group in the groove on the lower surface of the top plate and/or on the upper surface of the bottom plate when the slider is in operation, thereby transferring the vertical component of the load of the aircraft flap to the slide rail and rolling the rollers of the second roller group along the two side edges of the longitudinal extension of the top plate, whereby the load of the aircraft flap can be efficiently transferred to the slide rail and via the slide rail to the slide rail support device onto the aircraft.
According to a preferred embodiment of the present invention, the first roller group and the second roller group are respectively provided with four rollers, the rollers of the first roller group disposed on both sides of the slide rail in the longitudinal direction are respectively symmetrically provided, and the rollers of the second roller group disposed on both sides of the slide rail in the longitudinal direction are respectively symmetrically provided. Therefore, the pulley frame assembly can particularly stably move on the sliding rail along the longitudinal direction of the sliding rail, and the pulley frame assembly is prevented from tilting. Furthermore, in this case a stable guidance can be provided while maintaining a low construction weight.
According to a preferred embodiment of the present invention, the plurality of rollers of the first and second roller groups, which are arranged on the same lateral side of the slide rail in the longitudinal direction, are spaced apart from each other, respectively. This makes it possible to better expose the roller at least partially. In addition, the movement of the pulley yoke assembly on the slide rail along the longitudinal direction of the slide rail can be further stabilized.
According to a preferred embodiment of the present invention, the rollers of the second roller set are respectively disposed on opposite sides of the rollers of the first roller set in a longitudinal direction of the slide rail. This results in the rollers being arranged offset in the longitudinal direction, as a result of which the pulley holder can be guided better on the running rail.
According to a preferred embodiment of the invention, the rail is connected with its one end in the longitudinal direction to the aircraft wing via a rail support device.
According to a preferred embodiment of the invention, the pulley yoke assembly further comprises a pulley bracket, on the side of the pulley bracket opposite to the side on which the sliding rail is mounted, a connection interface for mounting an aircraft flap is provided, and the aircraft flap is mounted on the pulley bracket in an articulated manner by means of the connection interface. Thereby, the flap of the aircraft is made more flexible.
According to a preferred embodiment of the present invention, the rollers of the second roller set are mounted on the pulley bracket by means of a two-lug plate connection structure.
According to a preferred embodiment of the present invention, two tabs of the two-tab connection structure extend from the pulley bracket in the longitudinal direction of the slide rail parallel to each other and spaced apart in the height direction of the slide rail, through holes are formed in the two tabs, respectively, and the through holes are aligned in the height direction of the slide rail, and the rollers of the second roller set can be mounted between the two tabs by means of a mounting member. This allows the rollers of the second roller set to be better exposed and provides a simple mounting method.
On the basis of the common general knowledge in the field, the preferred embodiments can be combined randomly to obtain the preferred examples of the invention.
Drawings
For a better understanding of the above and other objects, features, advantages and functions of the present invention, reference should be made to the preferred embodiments illustrated in the accompanying drawings. Like reference numerals in the drawings refer to like parts. It will be appreciated by persons skilled in the art that the drawings are intended to illustrate preferred embodiments of the invention without any limiting effect on the scope of the invention, and that the various components in the drawings are not drawn to scale.
Fig. 1 shows a perspective view of a sliding device for guiding the movement of a trailing edge flap of an aircraft according to the invention, wherein the sliding device comprises a sliding rail and a pulley yoke assembly.
Fig. 2 shows a perspective view of the slide rail of the sliding device in fig. 1.
Fig. 3 shows a cross section of the slide rail in fig. 2.
Fig. 4 shows a perspective view of the sheave bracket assembly of the sliding apparatus.
Fig. 5 shows a perspective view of the slide rail and sheave bracket assembly in an assembled state and after a distance of movement.
Fig. 6 shows the arrangement of the center and side rollers of a prior art sheave assembly.
Description of reference numerals:
sliding device 1
Pulley yoke assembly 3
Top board 4
First rolling surface 4.1
Second rolling surface 6.1
Third rolling surface 4.2
Pulley bracket 8
First roller set 7.1
First roller 7.11 of the first roller set
Second roller 7.12 of the first roller set
Third roller 7.13 of the first roller set
Fourth roller 7.14 of the first roller group
Second roller set 7.2
First roller 7.21 of second roller group
Second roller 7.22 of the second roller group
Third roller 7.23 of the second roller group
Fourth roller 7.24 of the second roller group
Detailed Description
The inventive concept of the present invention will be described in detail below with reference to the accompanying drawings. What has been described herein is merely a preferred embodiment in accordance with the present invention and other ways of practicing the invention will occur to those skilled in the art and are within the scope of the invention. In the following detailed description, directional terms, such as "upper", "lower", "inner", "outer", and the like, are used with reference to the orientation depicted in the accompanying drawings. Components of embodiments of the present invention can be positioned in a number of different orientations and the directional terminology is used for purposes of illustration and is in no way limiting.
The "longitudinal direction" in the present invention refers to the direction in which the length of the slide rail extends, i.e., the direction parallel to the longitudinal direction of the aircraft fuselage, and the "transverse direction" is the width direction of the slide rail, wherein the transverse direction and the longitudinal direction are perpendicular to each other. The vertical direction is the height direction of the slide rail, and the vertical direction is respectively vertical to the transverse direction and the longitudinal direction.
Fig. 1 shows a perspective view of a sliding device 1 according to the invention for guiding the movement of a trailing edge flap of an aircraft. The sliding device 1 has a running rail 2 and a carriage assembly 3 mounted on the running rail 2 so as to be movable in its longitudinal direction.
Fig. 2 shows a perspective view of the sliding rail 2 of the sliding device 1 from fig. 1. Fig. 3 shows a cross section of the slide rail 2 in fig. 2. The sliding device 1 is laid in the longitudinal direction of the aircraft fuselage. The slide rail 2 includes an elongated top plate 4, two side plates 5 spaced apart from each other and extending vertically downward from a bottom surface of the top plate 4, and two bottom plates 6 extending from bottom ends of the two side plates 5 in parallel with the top plate 4 in opposite directions to each other, respectively. Thereby the cross section of the slide rail 2 is substantially formed in a pi shape. The skid 2 can be connected at its one end in the longitudinal direction to a skid support (not shown) of the aircraft wing.
The top plate 4 and the side plates 5 and the bottom plate 6, respectively, are connected to each other, for example by welding or by means of fixing elements, such as screws or the like. It is also conceivable for the sliding rail 2 to be produced as one piece. In addition, the top panel 4 is configured longer in its longitudinal direction than the side panels 5 and the bottom panel 6.
The top plate 4 of the slide rail 2 forms with the corresponding bottom plate 6 and side plate 5, respectively, a groove 11 which is open towards the outside of the slide rail in the transverse direction of the slide rail. When the sheave frame assembly 3 and the sliding rail 2 are mounted, the rollers of the first roller set 7.1 can roll in the groove 11 along at least one surface of the groove 11 and the rollers of the second roller set 7.2 can roll along two side edges of the top plate 4 extending in the longitudinal direction.
Specifically, lower surfaces of the top plate 4 facing the two bottom plates 6 form first rolling surfaces 4.1, respectively, and upper surfaces of the two bottom plates 6 facing the top plate 4 form second rolling surfaces 6.1, respectively, while two side edges of the top plate 4 connecting the upper and lower surfaces thereof extending in the longitudinal direction form third rolling surfaces 4.2, respectively. The rollers on the pulley carriage assembly 3 can roll on the above-mentioned rolling surfaces, respectively, so that the pulley carriage assembly 3 can move in a guided manner on the slideway 2 in the longitudinal direction of the slideway 2, as will be described in detail below.
Fig. 4 shows a perspective view of the sheave frame assembly 3 of the sliding device 1. The sheave bracket assembly 3 includes a sheave bracket 8 and a plurality of rollers. Two roller sets, namely a first roller set 7.1 and a second roller set 7.2, are provided.
In the embodiment of fig. 4, the first roller set 7.1 may comprise at least two rollers, such that at least one roller of the first roller set 7.1 is arranged in a groove 11 of the skid 2 when the sheave bracket assembly 3 is mounted on the skid 2. The first roller set 7.1 is arranged such that the rollers of the first roller set 7.1 can roll on the first rolling surface 4.1 or the second rolling surface 6.1, respectively, in the longitudinal direction of the skid 2 when the skid frame assembly 3 is mounted on the skid 2.
As can be seen in fig. 4, the first roller group 7.1 comprises four rollers. Wherein the first 7.11 and the second 7.12 roller of the first roller set are arranged aligned with and spaced apart from each other along the longitudinal direction of the slide rail 2 and the third 7.13 and the fourth 7.14 roller of the first roller set are arranged aligned with and spaced apart from each other along the longitudinal direction of the slide rail 2. Furthermore, the first roller 7.11 and the third roller 7.13 of the first roller set are arranged aligned with and spaced apart from each other along the transverse direction of the rail 2 and the second roller 7.12 and the fourth roller 7.14 of the first roller set are arranged aligned with and spaced apart from each other along the transverse direction of the rail 2, so that in the assembled state of the rail 2 and the pulley carrier assembly 3, the first roller 7.11 and the second roller 7.12 of the first roller set are arranged in one groove of the rail 2 and the third roller 7.13 and the fourth roller 7.14 of the first roller set are arranged in another groove of the rail 2. This can be seen in fig. 1 and fig. 5 which shows the slide rail 2 and the pulley yoke assembly 3 in an assembled state. The rollers of the first roller set roll on the first rolling surface 4.1 and/or the second rolling surface 6.1.
Of course, the first roller set 7.1 can also be provided with more than four rollers. Preferably, the first roller set 7.1 is provided with an even number of rollers. Preferably, the rollers of the first roller set 7.1, which are arranged on the same side of the slide rail 2 in the longitudinal direction, are spaced apart from one another. Preferably, the rollers of the first roller group 7.1 arranged on both sides of the sliding rail 2 in the longitudinal direction are respectively symmetrically arranged.
The second roller set 7.2 may likewise comprise at least two rollers, so that at least one roller of the second roller set 7.2 can roll on the third rolling surface 4.2 in the longitudinal direction of the rail 2 when the sheave frame assembly 3 is mounted on the rail 2.
As can be seen from fig. 4, the second roller set 7.2 also comprises four rollers. In fig. 4, the first roller 7.21 and the second roller 7.22 of the second roller set 7.2 are arranged on opposite sides of the first roller 7.11 and the second roller 7.12, respectively, of the first roller set in the longitudinal direction of the rail 2, while the third roller 7.23 and the fourth roller 7.24 of the second roller set 7.2 are arranged on opposite sides of the third roller 7.13 and the fourth roller 7.14, respectively, of the first roller set in the longitudinal direction of the rail 2, so that in the assembled state of the rail 2 and the sheave frame assembly 3, the respective rollers of the second roller set 7.2 can roll on a third rolling surface, respectively, in the longitudinal direction of the rail 2.
Of course, the second roller set 7.2 can also be provided with more than four rollers. Preferably, the second roller set 7.2 is provided with an even number of rollers. Preferably, the first roller set 7.1 and the second roller set 7.2 have the same number of rollers. Preferably, the rollers of the second roller set 7.2 arranged on both sides of the sliding rail 2 in the longitudinal direction are respectively symmetrically arranged.
In addition, a mounting interface for mounting the roller of the first roller group 7.1 and the roller of the second roller group 7.2 is provided on the pulley bracket 8, and the mounting interface can be configured as a single-lug or double-lug connecting structure. As can be seen in particular from fig. 4, the rollers of the second roller group 7.2 are mounted on the roller carrier 8 by means of such a lug connection. The two lugs of the two lug connection project from the pulley holder 8 in the longitudinal direction of the rail parallel to one another and spaced apart in the vertical direction of the rail. Through holes are respectively formed in the two lugs, and the through holes in the two lugs are arranged in alignment in the vertical direction of the slide rail, so that the corresponding rollers of the second roller set 7.2 can be mounted between the two lugs by means of the through holes in the two lugs. In fig. 4, a mounting in the form of a pin or bolt for mounting the rollers of the second roller set 7.2 is shown.
Of course, the rollers of the first roller set 7.1 and the second roller set 7.2 can be mounted on the pulley holder 8 in any conceivable manner, as long as the rollers of the first roller set 7.1 and the rollers of the second roller set 7.2 can be at least partially exposed and are allowed to roll along the respective rolling surfaces.
On the side of the pulley carrier 8 opposite to the mounting rail 2, a connection interface 12 for mounting an aircraft flap is provided. The aircraft flap can be mounted, for example, via a joint bearing on a connection interface 12 on the pulley carrier 8, wherein a double lug connection for mounting the joint bearing can be provided. Of course, other hinge mounting arrangements are possible.
Compared with the prior art, the sliding device for guiding the movement of the trailing edge flap of the airplane has the following advantages:
1. by rolling the rollers of the first roller set on the first rolling surface and/or the second rolling surface when the sliding device is in operation, whereby the vertical component of the load of the aircraft flap is transferred to the slide rail and the rollers of the second roller set on the third rolling surface transfer the lateral component of the load of the aircraft flap to the slide rail, it is possible to efficiently transfer the load of the aircraft flap to the slide rail and, via the slide rail, to the slide rail support as far as the aircraft.
2. Since all the rollers are arranged on the side of the slide rail and are at least partially exposed, in particular the rollers of the second roller group are arranged to roll on both sides of the top plate of the slide rail forming the third rolling surface and are mounted on the roller carrier by means of the two-lug connection, so that all the rollers are arranged in an easily accessible region, the maintenance difficulty of the rollers is effectively reduced, and the costs for the manufacture of parts and for maintenance are saved.
3. Because the roller is adopted in the application, the friction force is reduced compared with the common sliding operation mode, the wear-resisting property is improved, and the service life of the part is prolonged.
The scope of the invention is limited only by the claims. Persons of ordinary skill in the art, having benefit of the teachings of the present invention, will readily appreciate that alternative structures to the structures disclosed herein are possible alternative embodiments, and that combinations of the disclosed embodiments may be made to create new embodiments, which also fall within the scope of the appended claims.
Claims (9)
1. A slider (1) for guiding the movement of a trailing edge flap of an aircraft, the slider (1) lying in the longitudinal direction of the fuselage of the aircraft and comprising:
a slide rail (2) having a pi-shaped cross-sectional shape, the slide rail comprising:
a strip-shaped top plate (4) extending along the longitudinal direction of the slide rail;
two side plates (5) spaced apart from each other and extending vertically downward from a bottom surface of the top plate (4); and
two bottom plates (6) extending from the bottom ends of the two side plates (5) in parallel with the top plate in opposite directions to each other,
wherein the top plate (4) and the corresponding bottom plate (6) and side plate (5) respectively form a groove which is opened towards the outer side of the slide rail along the transverse direction of the slide rail,
a sheave frame assembly (3), the sheave frame assembly (3) being configured to be movable on the skid (2) in a longitudinal direction of the skid, wherein the sheave frame assembly (3) comprises a first and a second roller set mounted thereon,
characterized in that the rollers of a first roller set (7.1) are arranged to be able to roll in the groove along at least one surface of the groove, respectively, and the rollers of a second roller set (7.2) are arranged to be able to roll along two side edges of the longitudinal extension of the top plate (4), respectively, and such that the rollers of the first roller set (7.1) and the second roller set (7.2) are at least partially exposed.
2. Slider (1) for guiding the movement of trailing edge flaps of aircraft according to claim 1, characterised in that the rollers of the first roller group (7.1) roll in the groove on the lower surface of the top plate (4) and/or on the upper surface of the bottom plate (6).
3. The sliding apparatus (1) for guiding a movement of a trailing edge flap of an aircraft according to claim 1 or 2, characterized in that the first roller set (7.1) and the second roller set (7.2) are provided with four rollers, respectively, in that the rollers of the first roller set (7.1) which are arranged on both sides of the sliding rail (2) in the longitudinal direction are symmetrically arranged, respectively, and in that the rollers of the second roller set (7.2) which are arranged on both sides of the sliding rail (2) in the longitudinal direction are symmetrically arranged, respectively.
4. The sliding device (1) for guiding a movement of a trailing edge flap of an aircraft according to claim 1 or 2, characterized in that the rollers of the first roller set (7.1) and of the second roller set (7.2) which are arranged on the same transverse side of the sliding rail (2) in the longitudinal direction are each spaced apart from one another.
5. Sliding device (1) for guiding a movement of a trailing edge flap of an aircraft according to claim 1 or 2, characterized in that the rollers of the second roller set (7.2) are respectively arranged on opposite sides of the rollers of the first roller set (7.1) in the longitudinal direction of the sliding rail (2).
6. Sliding device (1) for guiding the movement of trailing edge flaps of aircraft according to claim 1 or 2, characterized in that the sliding rail (2) is connected with its end in the longitudinal direction to the aircraft wing via a sliding rail support device.
7. The sliding device (1) for guiding the movement of aircraft trailing edge flaps according to claim 1 or 2, characterized in that the pulley frame assembly (3) further comprises a pulley bracket (8), on the side of the pulley bracket (8) opposite to the mounting of the sliding rail (2) there being provided a connection interface (12) for mounting aircraft flaps, by means of which the aircraft flaps are mounted on the pulley bracket (8) in an articulated manner.
8. Slider (1) for guiding the movement of aircraft trailing edge flaps according to claim 7, characterized in that the rollers of the second roller set (7.2) are mounted on the pulley bracket (8) by means of a two-lug connection.
9. Sliding device (1) for guiding a movement of a trailing edge flap of an aircraft according to claim 8, characterized in that the two tabs of the double-tab connection, between which the rollers of the second roller set (7.2) can be mounted by means of a mounting, extend from the pulley bracket (8) parallel to one another and spaced apart in the height direction of the sliding rail (2) in the longitudinal direction of the sliding rail, and through-holes are formed in each case in the two tabs, which are arranged aligned in the height direction of the sliding rail (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011102697.5A CN112238933A (en) | 2020-10-15 | 2020-10-15 | Sliding device for guiding movement of trailing edge flap of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011102697.5A CN112238933A (en) | 2020-10-15 | 2020-10-15 | Sliding device for guiding movement of trailing edge flap of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112238933A true CN112238933A (en) | 2021-01-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011102697.5A Pending CN112238933A (en) | 2020-10-15 | 2020-10-15 | Sliding device for guiding movement of trailing edge flap of airplane |
Country Status (1)
| Country | Link |
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| CN (1) | CN112238933A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113501126A (en) * | 2021-05-26 | 2021-10-15 | 中国商用飞机有限责任公司 | Flap support device for aircraft |
| CN114537643A (en) * | 2022-03-23 | 2022-05-27 | 中国商用飞机有限责任公司 | Sliding device for trailing edge flaps of aircraft |
| CN115520405A (en) * | 2022-11-29 | 2022-12-27 | 四川腾盾科技有限公司 | Design method and structure of trailing edge fullerene flap sliding device |
| EP4137401A1 (en) * | 2021-08-18 | 2023-02-22 | Airbus Operations GmbH | High-lift device connection assembly as well as wing and aircraft equipped therewith |
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| CN202213714U (en) * | 2011-09-02 | 2012-05-09 | 北京航空航天大学 | Supporting mechanism for trailing edge flap high lift device |
| DE102011082888A1 (en) * | 2011-09-16 | 2013-03-21 | Airbus Operations Gmbh | Buoyancy flap bearing device, buoyancy flap assembly, hydrofoil and aircraft |
| US20150083853A1 (en) * | 2013-09-24 | 2015-03-26 | The Boeing Company | Adaptive trailing edge actuator system and method |
| CN109415116A (en) * | 2016-06-30 | 2019-03-01 | 庞巴迪公司 | For the component and method of the trailing edge flap of aircraft to be unfolded |
| CN110271660A (en) * | 2018-03-15 | 2019-09-24 | 波音公司 | The auxiliary shoring system of wing flap for aircraft wing |
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| CN202213714U (en) * | 2011-09-02 | 2012-05-09 | 北京航空航天大学 | Supporting mechanism for trailing edge flap high lift device |
| DE102011082888A1 (en) * | 2011-09-16 | 2013-03-21 | Airbus Operations Gmbh | Buoyancy flap bearing device, buoyancy flap assembly, hydrofoil and aircraft |
| US20150083853A1 (en) * | 2013-09-24 | 2015-03-26 | The Boeing Company | Adaptive trailing edge actuator system and method |
| CN109415116A (en) * | 2016-06-30 | 2019-03-01 | 庞巴迪公司 | For the component and method of the trailing edge flap of aircraft to be unfolded |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113501126A (en) * | 2021-05-26 | 2021-10-15 | 中国商用飞机有限责任公司 | Flap support device for aircraft |
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| EP4137401A1 (en) * | 2021-08-18 | 2023-02-22 | Airbus Operations GmbH | High-lift device connection assembly as well as wing and aircraft equipped therewith |
| CN114537643A (en) * | 2022-03-23 | 2022-05-27 | 中国商用飞机有限责任公司 | Sliding device for trailing edge flaps of aircraft |
| CN114537643B (en) * | 2022-03-23 | 2024-01-30 | 中国商用飞机有限责任公司 | Sliding device for a trailing edge flap of an aircraft |
| CN115520405A (en) * | 2022-11-29 | 2022-12-27 | 四川腾盾科技有限公司 | Design method and structure of trailing edge fullerene flap sliding device |
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Application publication date: 20210119 |