CN117302507A - Flap support assembly for a wing comprising a flap and wing comprising a flap - Google Patents
Flap support assembly for a wing comprising a flap and wing comprising a flap Download PDFInfo
- Publication number
- CN117302507A CN117302507A CN202311200284.4A CN202311200284A CN117302507A CN 117302507 A CN117302507 A CN 117302507A CN 202311200284 A CN202311200284 A CN 202311200284A CN 117302507 A CN117302507 A CN 117302507A
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- CN
- China
- Prior art keywords
- flap
- support
- wing
- frame
- support body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 17
- 210000005069 ears Anatomy 0.000 claims description 5
- 239000013585 weight reducing agent Substances 0.000 claims description 3
- 230000008878 coupling Effects 0.000 abstract description 3
- 238000010168 coupling process Methods 0.000 abstract description 3
- 238000005859 coupling reaction Methods 0.000 abstract description 3
- 238000006073 displacement reaction Methods 0.000 description 4
- 125000006850 spacer group Chemical group 0.000 description 4
- 238000009434 installation Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000037396 body weight Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007789 sealing Methods 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
- B64C9/02—Mounting or supporting thereof
-
- 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
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/34—Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to a flap support assembly for a wing comprising a flap and a wing comprising a flap. The flap support assembly includes: a flap support body having a track on a first side for slidably coupling a flap to the flap support body; a first support, a first end of the first support rotatably coupled to a first end of the flap support body, and a second end of the first support rotatably coupled to a first location of a frame of the wing; and a second support, a first end of the second support rotatably coupled to a second end of the flap support body, and a second end of the second support rotatably coupled to a second location of the frame; wherein the flap support body and the first support, the second support and the frame are formed in a four bar mechanism such that the guide rail on the flap support body is movable relative to the frame under the constraint of the first support and the second support.
Description
Technical Field
The present invention relates to a flap support assembly for a wing including a flap that can provide support for the flap and limit displacement or vibration in a non-moving direction during the full travel of the flap retraction. The invention also relates to a wing comprising a flap. The invention belongs to the field of aircraft wing structural design.
Background
The wing flap of the airplane is a movable wing attached to the trailing edge of the wing, and is integrated with the wing at ordinary times, and when the airplane needs to adjust the posture, the wing flap can be operated to be put down. The flap can increase the area of the wing, change the radian of the wing section of the wing, increase the lift force which the wing can provide, and is most commonly used in low-speed take-off and landing. The flap is connected with the wing by two groups of moving mechanisms which are respectively arranged at specific positions on two sides of the flap in the extending direction.
The flaps are typically mounted on the trailing edge of a fixed wing aircraft and are capable of deflecting downwardly and sliding rearwardly in use. When the flap is put down, the two ends of the flap are suspended, and when the airflow passes through the flap, the two ends of the flap vibrate obviously, which occurs particularly on a large-sized airplane. If the end of the air flow is not restrained, the vibration effect caused by the air flow is more remarkable, passengers and units are uncomfortable, even the structure is possibly damaged, and other vibration problems are induced.
In the prior art, a patent of auxiliary supporting system of a flap for an airplane wing is a flap slide rail sealing device. The device is in the form of a roller and an I-shaped sliding rail, the sliding rail is connected with the flap through a joint bearing, the sliding rail is in an S-shaped and non-parallel shape, and the tail part of the sliding rail has a stop function. However, flap support systems employing rollers, i-shaped tracks are suitable for flaps that move in two dimensions. This form is no longer applicable when the flap is moved in three dimensions.
Therefore, it is desirable to provide a support device that can suppress the vibration of the flap end without affecting the flap motion, providing a technical reserve for model development.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provide a flap supporting mechanism which has the characteristics of simple form, high motion reliability and the like, and can provide support for flaps in the full stroke of the retraction of the flaps and limit the displacement or vibration of the flaps in the non-motion direction.
In a first example of the flap support assembly, the flap support assembly includes: a flap support body having a track on a first side for slidably coupling a flap to the flap support body; a first support, a first end of the first support rotatably coupled to a first end of the flap support body, and a second end of the first support rotatably coupled to a first location of a frame of the wing; and a second support, a first end of the second support rotatably coupled to a second end of the flap support body, and a second end of the second support rotatably coupled to a second location of the frame; wherein the flap support body and the first support, the second support and the frame are formed in a four bar mechanism such that the guide rail on the flap support body is movable relative to the frame under the constraint of the first support and the second support.
In a second example of the flap support assembly, optionally comprising a first example, the first end of the first support is connected to the first end of the flap support body by a pair of ears and a pin, and only the first support is allowed to rotate in a first rotational direction relative to the flap support body, and the second end of the first support is connected to the frame of the wing by a pair of ears and a pin, and only the first support is allowed to rotate in the first rotational direction relative to the frame, so that the flap support body can provide support for the flap in a non-moving direction, and thus can withstand moments in other directions.
In a third example of the flap support assembly, optionally including one or more of the first example and the second example, the first end of the second support is connected to the second end of the flap support body by a knuckle bearing, and the second end of the second support is connected to the frame of the wing by a knuckle bearing.
In a fourth example of the flap support assembly, optionally including one or more of the first to third examples, the second support is in the form of a lever set and is capable of adjusting the overall length of the second support and maintaining the overall length. The overall movement of the flap support assembly 1 can thus be adjusted during ground installation to meet the actual requirements of the flap 3 during operation of the aircraft.
In a fifth example of the flap support assembly, optionally including one or more of the first to fourth examples, the flap support body and/or the first support and/or the second support is provided with a body weight reduction or support weight reduction thereon that does not affect the overall structural strength. The shape and location of these body weight-reducing portions and support weight-reducing portions are designed so as not to affect their overall structural strength.
In a sixth example of the flap support assembly, optionally including one or more of the first to fifth examples, the first and/or second supports are connected to a second side of the flap support body opposite the first side. The appropriate dimensions of the quadrangle in the form of a four-bar mechanism allowing the movement stroke of the flap can be satisfied in the case where the length dimension of the flap supporting body 20 is allowed to satisfy the length dimension of the guide rail 21.
In a seventh example of the flap support assembly, optionally including one or more of the first to sixth examples, the frame includes a bulkhead of the wing and includes a spar of the wing. Because of the closer distance from the spacer, the length of the first and second supports may be shorter when secured to the spacer, reducing weight as a whole.
The present invention also provides a wing comprising a flap, wherein the wing comprises the flap support assembly of any of the preceding examples.
The flap supporting assembly has the characteristics of simple form, high motion reliability and the like, and can provide support for the flap in the full stroke of the retraction of the flap and limit the displacement or vibration of the flap in the non-motion direction.
Drawings
In order to describe the above-mentioned and other characteristic embodiments of the invention, a more particular description of the invention briefly described above will be rendered by reference to exemplary embodiments thereof which are illustrated in the appended drawings. Understanding that these drawings depict only exemplary embodiments of the invention and are not therefore to be considered to be limiting of its scope, the invention will be described and explained with additional specificity and detail through the use of the accompanying drawings. In the drawings:
FIG. 1 is a perspective view of a flap support assembly in an installed state according to an embodiment of the invention;
FIG. 2 is a perspective view of a flap support body of a flap support assembly according to an embodiment of the invention;
FIG. 3 is a perspective view of a flap support assembly according to an embodiment of the invention viewed in another direction; and
FIG. 4 is an exploded view of a flap support assembly according to an embodiment of the invention.
Fig. 1-4 are generally drawn to scale, however, the dimensions in the drawings are merely schematic and are not necessarily drawn to scale, but are intended to be more clearly illustrated. In other embodiments, other relative dimensions may be used.
The same reference numbers are used herein and throughout the following description to refer to the same or like features appearing in different drawings.
List of reference numerals:
1. flap support assembly
2. Frame
3. Flap
20. Flap support body
20a first end of the flap support body
Second end of 20b flap support body
21. Guide rail
22. Main body weight-reducing part
30. First support piece
31. Support weight-reducing portion
40. Second support piece
Detailed Description
The present invention will be further described with reference to specific embodiments and drawings, in which more details are set forth in the following description in order to provide a thorough understanding of the present invention, it will be apparent that the present invention can be embodied in many other forms than described herein, and that those skilled in the art may make similar generalizations and deductions depending on the actual application without departing from the spirit of the present invention, and therefore should not be taken as limiting the scope of the present invention in its context.
In the present invention, directional terms, such as "vertical", "horizontal", "top", "bottom", "upper", "lower", "inner", "inward", "outer" and "outward", are used to assist in describing the invention in terms of the orientation of the embodiments shown in the drawings, and are not to be construed as absolute upper, lower, horizontal, vertical, etc., but are not to be construed as limiting the invention to any particular orientation.
In the present invention, unless explicitly stated to the contrary, the terms "first," "second," and the like, are not intended to denote any order, location, quantity, or importance, but rather are merely used as labels to distinguish one element from another.
In the present invention, the term "knuckle bearing" refers to a joint that can perform universal rotation within a certain range, not limited to a bearing, but any joint structure that can provide omnidirectional rotation for preventing a mechanism to which it is connected from seizing up during movement.
In the prior art, most of the flap supports are directly fixed to the spar of the wing. Since the support point is at a large distance from the rear spar, it is necessary to make the flap support long enough and therefore a large weight.
The flap support assembly of the present application may not be fixed to the rear spar, but may alternatively be fixed to the side spacer. Because of the closer distance from the spacer, the length of the connector, and in particular the first 30 and second 40 supports, can be shorter, reducing weight overall.
Fig. 1 schematically shows a perspective view of a flap support assembly 1 according to a preferred embodiment of the invention in an installed state. The flap support assembly 1 mainly comprises a flap support body 20, a first support 30 and a second support 40 connecting the flap support body 20 to the frame 2 of the wing.
Fig. 2 is a perspective view of the flap support body 20 schematically showing the flap support assembly 1 of the preferred embodiment of the invention, wherein the rail 21 on the first side of the flap support body 20 is shown. The track 21 is shaped so that the flap 3 (shown in fig. 1) is slidably connected to the flap support body 20 during the full stroke of retraction of the flap 3 and thus allows the flap 3 to be slidably connected to the flap support body 20 and thus to the frame 2 of the wing.
When the flap 3 has a tendency to vibrate or deform in a non-moving direction, it is restricted by the side walls of the track 21 on the flap support body 20, so that vibrations or deformations of the flap are avoided.
The specific guiding direction and shape of the rail 21 is not limited and is determined according to the specific movement requirements of the flap 3. During the full stroke of retraction of the flap 3, the movement of the flap 3 will produce a relative movement with the flap support body 20. The relative movement track of which conforms to the shape of the rail 21 of the flap support body 20 so as to facilitate movement of the flap 3 without jamming.
The flap 3 has support bars on both sides, which are in contact with the rail 21, so that the rail 21 provides guidance and support for the flap 3 during the full travel of the flap 3 in the retracted position.
Preferably, the flap support main body 20 may be provided with a main body weight-reducing portion 22, the shape and location of the main body weight-reducing portion 22 being designed so as not to affect its overall structural strength. In order to reduce the weight of the parts, through holes or blind holes can be reduced according to actual conditions.
Turning now to fig. 3, there is schematically shown a perspective view of the flap support assembly 1 of the preferred embodiment of the invention, seen in another direction.
A first end of the first support 30 is rotatably connected to the first end 20a of the flap support body 20 and a second end of the first support 30 is rotatably connected to a first position of the frame 2 of the wing. Further, a first end of the second support 40 is rotatably connected to the second end 20b of the flap support main 20, and a second end of the second support 40 is rotatably connected to the second position of the frame 2.
The flap support body 20 is formed as a four bar mechanism with the first support 30, the second support 40 and the frame 2 as shown in fig. 1. The four-bar linkage may be a parallelogram mechanism, but the shape is not limited thereto, and may be a scalene quadrilateral mechanism as long as the flap support body 20 can move within a range such that the rail 21 on the flap support body 20 can move relative to the frame 2 under the constraint of the first support 30 and the second support 40.
The motion track of the flap 3 is space motion rather than plane motion, and the flap support assembly 1 can move along with the flap 3 in the direction of the aircraft extension along with the motion of the flap 3 through a four-bar mechanism formed by the flap support assembly and the frame 2, so that the space motion requirement of the flap 3 can be met in the full stroke of retraction and extension of the flap 3. By means of the four-bar mechanism, the spanwise motion constraint of the flap 3 can be released, the motion of the flap 3 can be matched, and the whole mechanism cannot be blocked and locked.
Fig. 4 schematically shows an exploded view of a flap support assembly 1 according to an embodiment of the invention.
Referring to fig. 3 and 4, in a preferred embodiment, a first end of the first support 30 is connected to the first end 20a of the flap support body 20 by a double ear having a predetermined span and a pin, and only the first support 30 is allowed to rotate in a first rotational direction with respect to the flap support body 20. Furthermore, the second end of the first support 30 is connected to the frame 2 of the wing by means of ears and pins, and only allows the first support 30 to rotate in a first rotational direction with respect to the frame 2.
Since the first support 30 is connected by means of a double tab with a predetermined span, the movement of the first support 30 is constrained such that the first support 30 can only rotate relative to the frame 2 or the flap support body 20, in particular the form of construction ensures that the flap support body 20 can only rotate relative to the first support 30 about double tabs and pins, so that the flap support body 20 can provide support for the flap 3 in a non-moving direction and can thus withstand moments in other directions.
Therefore, when the flap 3 has a tendency to vibrate or deform in the vertical direction, it is restrained by the side walls of the rail 21 of the flap support body 20, thereby avoiding the vibration or deformation of the flap.
In contrast, the second support 40 is intended to provide a predetermined length and is not designed to withstand moments in other directions. The second support 40 will be described in detail below.
It will be appreciated that the structural form of the first support 30 is not limited to the frame rocker arm form shown, but may be in the form of a ribbed beam.
Preferably, the first support 30 may be provided with a support weight-reducing portion 31, the support weight-reducing portion 31 being shaped and positioned so as not to affect its overall structural strength. In order to reduce the weight of the parts, lightening holes or lightening blind holes can be arranged according to actual conditions.
Preferably, a connection lug may be provided on a second side of the flap support main 20 opposite to the first side, and the first support 30 may be connected to the connection lug. The provision on the second side can satisfy a suitable size of a quadrangle in the form of a four-bar mechanism allowing a movement stroke of the flap in a case where the length size of the flap support main 20 is allowed to satisfy the length size of the guide rail 21, as compared with the case where the connection structure is provided at both ends of the flap support main 20.
Referring to fig. 3 and 4, the first end of the second support 40 is connected to the second end 20b of the flap support body 20 by means of a knuckle bearing. Furthermore, the second end of the second support 40 is connected to the frame 2 of the wing by means of a knuckle bearing. The term "knuckle bearing" as used herein provides sufficient rotational freedom to prevent rotational joint binding.
The knuckle bearings at the two ends of the second support piece 40 are used for reducing the friction force of the mechanism and ensuring the smooth movement of the flap support assembly 1; in addition, the use of the knuckle bearing reduces the requirement on the machining precision of the mechanism parts, so that the cost can be reduced.
In the case of sufficient machining precision of the parts and sufficient rigidity of the coupling parts, bushings can also be used instead of the knuckle bearings.
The use of bushings or knuckle bearings herein protects the primary parts from wear in addition to reducing the friction of the mechanism.
The second support 40 is shaped in the form of a loop bar which allows the overall length of the second support 40 to be adjusted and maintained during operation of the aircraft. The overall movement of the flap support assembly 1 can thus be adjusted during ground installation to meet the actual requirements of the flap 3 during operation of the aircraft.
Preferably, the second support 40 may be provided on a second side of the flap support body 20.
The flap supporting assembly has the characteristics of simple form, high motion reliability and the like, and can provide support for the flap in the full folding and unfolding stroke of the flap and limit the displacement or vibration of the flap in the non-motion direction.
In the foregoing, in order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the present invention are clearly and completely described with reference to the specific embodiments of the present invention and the accompanying drawings.
While various embodiments have been described above, it should be understood that the embodiments described are some, but not all, of the embodiments of the present invention, which are presented by way of example and not limitation. It will be apparent to those skilled in the relevant art that the disclosed subject matter may be embodied in other specific forms without departing from the spirit or essential characteristics thereof.
The above-described embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, and not as subject of any limitation of the invention.
All other embodiments, based on the embodiments of the invention, which are apparent to those of ordinary skill in the art without undue burden are within the scope of the invention. The present disclosure also includes various modifications and modifications within the equivalent scope. In addition, various combinations and modes, including only one element, more than one or less than one other combinations and modes, are also within the scope and spirit of the present disclosure.
Claims (8)
1. A flap support assembly for a wing comprising a flap, characterized in that the flap support assembly (1) comprises:
a flap support body (20), the flap support body (20) having on a first side a track (21) for slidably connecting a flap (3) to the flap support body (20);
a first support (30), a first end of the first support (30) being rotatably connected to a first end of the flap support body (20), and a second end of the first support (30) being rotatably connected to a first position of the frame of the wing; and
a second support (40), a first end of the second support (40) being rotatably connected to a second end of the flap support body (20), and a second end of the second support (40) being rotatably connected to a second position of the frame;
wherein the flap support body (20) and the first support (30), the second support (40) and the frame (2) are formed in a four bar mechanism such that the guide rail (21) on the flap support body (20) is movable relative to the frame (2) under the constraint of the first support (30) and the second support (40).
2. The flap support assembly of claim 1 wherein,
the first end of the first support (30) is connected to the first end of the flap support body (20) by means of ears and pins and allows rotation of the first support (30) relative to the flap support body (20) only in a first rotational direction, and
the second end of the first support (30) is connected to the frame (2) of the wing by means of ears and pins and allows only the first support (30) to rotate in the first rotational direction relative to the frame (2).
3. The flap support assembly of claim 1 wherein,
the first end of the second support (40) is connected to the second end of the flap support body (20) by means of a knuckle bearing, and
the second end of the second support (40) is connected to the frame (2) of the wing by means of a knuckle bearing.
4. The flap support assembly of claim 1 wherein,
the second support (40) is in the form of a set of bars and is capable of adjusting the overall length of the second support (40) and maintaining the overall length.
5. The flap support assembly of claim 1 wherein,
the flap support body (20) is provided with a body weight-reducing portion, and/or
The first support (30) and/or the second support (40) are provided with a support weight reduction.
6. The flap support assembly of claim 1 wherein,
the first support (30) and/or the second support (40) are connected to a second side of the flap support body (20) opposite the first side.
7. The flap support assembly of claim 1 wherein,
the frame (2) comprises a bulkhead of the wing and comprises a back spar of the wing.
8. A wing comprising a flap, characterized in that it comprises a flap support assembly according to any of claims 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311200284.4A CN117302507A (en) | 2023-09-15 | 2023-09-15 | Flap support assembly for a wing comprising a flap and wing comprising a flap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311200284.4A CN117302507A (en) | 2023-09-15 | 2023-09-15 | Flap support assembly for a wing comprising a flap and wing comprising a flap |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117302507A true CN117302507A (en) | 2023-12-29 |
Family
ID=89254607
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311200284.4A Pending CN117302507A (en) | 2023-09-15 | 2023-09-15 | Flap support assembly for a wing comprising a flap and wing comprising a flap |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117302507A (en) |
-
2023
- 2023-09-15 CN CN202311200284.4A patent/CN117302507A/en active Pending
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