CN114348235A - Integrated wing aileron driving device and installation method - Google Patents
Integrated wing aileron driving device and installation method Download PDFInfo
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- CN114348235A CN114348235A CN202210054480.4A CN202210054480A CN114348235A CN 114348235 A CN114348235 A CN 114348235A CN 202210054480 A CN202210054480 A CN 202210054480A CN 114348235 A CN114348235 A CN 114348235A
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Abstract
The invention discloses an integral wing aileron driving device and an installation method, wherein the integral wing aileron driving device comprises a driving piece, a transmission assembly and a transmission accommodating cylinder, wherein the transmission accommodating cylinder is pre-embedded in a wing main body which is integrally manufactured with a wing box with an opening, is positioned between the installation position of an aileron in the wing main body and the wing box, and is coaxially arranged with a rotating shaft of the aileron; the transmission assembly is movably arranged in the transmission accommodating barrel in a penetrating way and can move along the axial direction when not connected with the driving piece, and one end of the transmission assembly is connected with or separated from the aileron positioned at the mounting position; the driving piece is placed into the wing box from the opening and connected with the other end of the transmission assembly and limits the axial movement of the transmission assembly, and the transmission assembly is driven to rotate. The driving device has the advantages of simple structure, reasonable layout, capability of being installed from a small opening, suitability for the wing profiles without process separating surfaces and with the ailerons positioned at the far ends or the middle parts of the wing main bodies, and the like, and the installation method also has the advantages of simple steps, convenient operation, extremely small space required by operation, and the like.
Description
Technical Field
The invention relates to the technical field of high-speed unmanned aerial vehicle equipment, in particular to an integral wing aileron driving device and an installation method.
Background
The high-speed unmanned aerial vehicle wing usually needs to adopt the thin wing section that relative thickness is less, just can reduce air resistance, obtains good aerodynamic performance. However, because the wings are thin, aileron driving pieces such as steering engines and the like cannot be arranged in the wing body. The existing better solution is to place the aileron drive in the central wing box and then transmit the drive to the aileron through a set of transmission mechanisms.
However, the existing transmission mechanism is only suitable for the layout structure that the ailerons are located at the wing root of the wing main body, namely, the end surfaces of the ailerons are directly exposed at the driving part of the wing box and directly transmitted from the end surfaces, but the wing rudder efficiency applicable to the transmission mode is low, and the transmission mechanism cannot be used for a high-speed unmanned aerial vehicle. Some airfoils with ailerons arranged at the far end or the middle part of the wing main body can be used, but the installation and the disassembly of the transmission mechanism can be completed only by disassembling the wing main body, and the transmission mechanism can only be used for the wings with process separation surfaces on the wing main body and cannot be installed and connected inside the integrated wings without the process separation surfaces.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, provides an integral wing aileron driving device which has a simple structure and reasonable layout, can be installed from a small opening, is suitable for a wing type without a process separating surface and has ailerons positioned at the far end or the middle part of a wing main body, and also provides an installation method of the driving device which has simple steps, convenient operation and extremely small space required by operation.
In order to solve the technical problems, the technical scheme provided by the invention is as follows:
an integral wing aileron driving device comprises a driving piece, a transmission assembly and a transmission accommodating cylinder, wherein the transmission accommodating cylinder is pre-embedded in a wing main body which is integrally manufactured with a wing box with an opening, is positioned between the installation position of an aileron in the wing main body and the wing box, and is coaxially arranged with a rotating shaft of the aileron; the transmission assembly is movably arranged in the transmission accommodating barrel in a penetrating way and can move along the axial direction when not connected with the driving piece, and one end of the transmission assembly is connected with or separated from the aileron positioned at the mounting position; the driving piece is placed into the wing box from the opening, connected with the other end of the transmission assembly and limited in axial movement of the transmission assembly, and drives the transmission assembly to rotate.
As a further improvement of the above-described integrated wing aileron drive:
the width of the hollow area of the wing box in the axial direction of the transmission containing cylinder is not less than the connecting length of the transmission assembly and the ailerons, and the transmission assembly is contained in the wing box and the transmission containing cylinder in the preparation of the wings.
The transmission assembly comprises a transmission rod, the transmission rod comprises a connecting rod section, the connecting rod section is a straight rod with a non-circular section, and the ailerons are provided with connecting holes which are connected with the connecting rod section in an adaptive mode and have non-circular sections.
The transmission rod also comprises a conical rod section connected with the connecting rod section, the diameter of the conical rod section is larger than that of the connecting rod section, and the conical rod section is connected with the connecting rod section through a small-diameter end; the inner hole of the transmission accommodating cylinder is a taper hole with the taper consistent with the taper rod section, and the taper rod section is arranged in the transmission accommodating cylinder in a penetrating mode with a gap.
The transmission containing barrel comprises a first bearing and a barrel body used for containing the conical rod section, the first bearing is arranged at the end part, close to the aileron, of the barrel body, and the inner diameter and the outer diameter of the first bearing are respectively in adaptive connection with the conical rod section and the barrel body.
The transmission rod further comprises a cylindrical section connected with the large-diameter end of the conical rod section, a limiting plate is arranged at the intersection position of the wing box and the wing main body, a limiting hole is formed in the limiting plate, and the cylindrical section is located on one side, facing the wing box, of the limiting plate and is larger than the aperture of the limiting hole in diameter; the conical rod section is positioned on one side of the limiting plate, which faces the wing main body, and the diameter of the large-diameter end is smaller than the aperture of the limiting hole.
The transmission assembly further comprises a bearing seat and a second bearing, the end face of the bearing seat is attached to the surface, facing the wing box, of the limiting plate, and the inner diameter and the outer diameter of the second bearing are respectively in adaptive connection with the cylindrical section and the bearing seat; the bearing block connected with the second bearing is placed into the wing box through the opening and is connected with the wing box through a fastener penetrating the surface of the wing box and fastened on the bearing block.
The transmission assembly further comprises a third bearing, the third bearing is arranged at one end, far away from the transmission accommodating barrel, of the connecting hole, and the connecting rod section penetrates through the connecting hole and then is connected with the third bearing in an adaptive mode.
The driving piece is connected with an adapter plate parallel to the surface of the wing box, and the driving piece is connected with the wing box through a fastener penetrating through the surface of the wing box and fastened on the adapter plate; the end face of the cylindrical section is provided with an inserting piece, the driving end of the driving piece is provided with a slot, and the inserting piece is inserted into the slot and is connected with the slot through a screw which vertically penetrates through a through hole formed in the inserting piece and the through hole.
The invention also provides an installation method of the integrated wing aileron driving device, which comprises the following steps:
s1: embedding a transmission accommodating cylinder at a set position in a material for preparing the wing, so that the transmission accommodating cylinder is positioned between the installation position of the aileron in the wing main body and the wing box and is coaxial with a rotating shaft of the aileron;
s2: accommodating the transmission assembly in the hollow areas of the transmission accommodating barrel and the wing box;
s3: after the wing is prepared, the aileron is placed at the installation position of the wing main body, the transmission assembly is rotated to be aligned to the aileron, the transmission assembly is axially moved, and the aileron is connected by using viscose glue;
s4: placing the driving piece into the wing box through the opening, and connecting the driving end of the driving piece with the transmission assembly;
s5: and continuing axially moving the transmission assembly until the driving piece reaches the installation position, and connecting the driving piece and the wing box to finish installation.
Compared with the prior art, the invention has the advantages that:
the integral wing aileron driving device is used for an integral wing type high-speed unmanned aerial vehicle, namely, a wing main body and a wing box of the unmanned aerial vehicle adopt an integral forming processing mode, so that the integral wing aileron driving device has no splitting performance and no process separation surface, and the smoothness of lines is ensured. The transmission accommodating cylinder is embedded in the wing main body, is positioned between the installation position of the aileron in the wing main body and the wing box and is coaxially arranged with a rotating shaft of the aileron, and the embedded transmission accommodating cylinder constructs a channel connected between a driving piece in the wing box and the aileron in the preparation process of the wing, so that a movable space is provided for a transmission assembly, direct sealing or glue permeation during the forming of the wing main body is avoided, and the transmission capacity of the transmission assembly is ensured.
The transmission assembly is movably arranged in the transmission accommodating barrel in a penetrating mode and can move along the axial direction when not connected with the driving piece, so that the end portion extends out of the transmission accommodating barrel and reaches the installation position of the aileron, and connection can be completed when the aileron is located at the installation position. The driving piece is placed into the wing box from the opening and connected to the other end of the transmission assembly, the axial movement of the transmission assembly is limited after the connection is completed, and the transmission assembly is driven to rotate to drive the aileron to swing. The whole connection process of the transmission assembly and the driving piece does not need to operate the structure inside the wing main body, and the connection can be realized only by operating the installation position of the aileron and the opening of the wing box, so that the integral wing box is suitable for integral wings which cannot be detached. And the transmission assembly can be completed only by axial movement in the connection process, has axial extensibility, and can be completely realized even if the ailerons are positioned at the far ends or the middle parts of the wings and the like, so that the structure disclosed by the invention can be used for the integral high-speed unmanned aerial vehicle. In addition, the device is completely arranged inside the wing, so that the aerodynamic appearance of the wing and the aerodynamic performance of the unmanned aerial vehicle are not influenced.
The installation method of the integrated wing aileron driving device is used for installing the integrated wing aileron driving device, has the advantages, and has simple installation steps, convenient operation and extremely small required space, thereby reducing the capability dependence on workers, reducing the production cost, improving the production efficiency and facilitating the overhaul and maintenance.
Drawings
FIG. 1 is a schematic structural view of an integrated wing aileron drive of the present invention;
FIG. 2 is a schematic exploded view of the integrated wing aileron drive of the present invention;
FIG. 3 is a schematic view of the construction of the actuator rod in the integrated wing aileron drive of the present invention;
FIG. 4 is a schematic view of the connection of the drive rod and aileron of the integrated wing aileron drive of the present invention;
FIG. 5 is a plan view of the drive link and the drive member of the integrated wing aileron drive of the present invention;
FIG. 6 is a perspective view of the drive link and the drive member of the integrated wing aileron drive of the present invention;
FIG. 7 is a schematic view of the structure of an aileron in the integrated wing aileron drive of the present invention.
Illustration of the drawings: 1. a drive member; 11. a patch; 12. a slot; 2. a transmission assembly; 21. connecting rod segments; 22. a tapered rod section; 23. a cylindrical section; 231. inserting sheets; 232. a screw; 24. a bearing seat; 25. a second bearing; 26. a third bearing; 3. a transmission accommodating cylinder; 31. a first bearing; 32. a barrel; 4. a wing body; 5. a wing box; 51. an opening; 52. a limiting plate; 521. a limiting hole; 6. an aileron; 61. and connecting the holes.
Detailed Description
In order to facilitate understanding of the invention, the invention will be described more fully and in detail with reference to the accompanying drawings and preferred embodiments, but the scope of the invention is not limited to the specific embodiments below.
Example (b):
as shown in fig. 1 and 2, the integral wing aileron driving device of the embodiment is used for the integral wing type high-speed unmanned aerial vehicle, namely, the wing main body 4 and the wing box 5 of the unmanned aerial vehicle adopt an integral forming and processing mode, so that the splitting performance does not exist, the process separation surface does not exist, and the fluency of lines is ensured.
The wing comprises a driving piece 1, a transmission assembly 2 and a transmission accommodating barrel 3, wherein the transmission accommodating barrel 3 is pre-embedded in a wing main body 4 integrally manufactured with a wing box 5 with an opening 51, is positioned between the installation position of an aileron 6 in the wing main body 4 and the wing box 5, and is coaxially arranged with a rotating shaft of the aileron 6. The embedded transmission containing cylinder 3 constructs a channel connected between the driving piece 1 and the aileron 6 in the wing box 5 in the wing preparation process, provides a movable space for the transmission component 2, avoids direct sealing or glue permeation when the wing main body 4 is formed, and ensures the transmission capacity of the transmission component 2. Meanwhile, the transmission accommodating barrel 3 can also reduce the friction resistance of the transmission assembly 2 in rotation when the wing main body 4 deforms. The wing main part 4 of this embodiment is carbon-fibre composite foam sandwich structure, and a transmission holding section of thick bamboo 3 is the carbon fiber pipe, and is pre-buried in the foam core, and the outside parcel of foam core has the combined material covering, and concrete material be the conventional covering material of unmanned aerial vehicle can, do not do here and describe repeatedly.
The transmission assembly 2 is movably arranged in the transmission accommodating barrel 3 in a penetrating way and can move along the axial direction when not connected with the driving piece 1, so that the end part extends out of the transmission accommodating barrel 3 and reaches the installation position of the aileron 6, and when the aileron 6 is located at the installation position, the connection can be completed; or the transmission containing barrel 3 is retracted, so that the ailerons 6 can be conveniently placed at the installation position. The driving piece 1 is arranged in the wing box 5 from the opening 51 and connected with the other end of the transmission component 2, the axial movement of the transmission component 2 is limited after the connection is finished, the transmission component 2 and the aileron 6 are ensured to be in a connection state, and the transmission component 2 is driven to rotate to drive the aileron 6 to swing.
The whole connection process of the transmission assembly 2 and the driving member 1 of the embodiment does not need to operate the internal structure of the wing main body 4, and can be realized only by operating the installation position of the aileron 6 and the opening 51 of the wing box 5, so that the wing box is suitable for an integral wing which cannot be detached. And transmission assembly 2 just can accomplish through axial displacement at the in-process of connecting, has axial extensibility, even if aileron 6 is located wing distal end or positions such as middle part, also can realize completely, therefore the structure of this embodiment can be used for integral high-speed unmanned aerial vehicle.
In this embodiment, the inner space of the wing box 5 is surrounded by the upper box and the lower box before preparation, the two parts are connected into a whole by screws, and the upper box and the lower box are also pre-embedded in the wing and prepared together. The width of the hollow area of the wing box 5 in the axial direction of the drive receiving cylinder 3 is not less than the connection length of the drive assembly 2 and the aileron 6. That is, when the transmission unit 2 moves axially and retreats into the wing box 5, the retreat space allowed for the transmission unit 2 in the wing box 5 is larger than the connection length between the transmission unit 2 and the aileron 6, and the transmission unit 2 can be completely detached from the aileron 6 before completely retreating into the wing box 5, thereby avoiding the installation position of the aileron 6 and ensuring that the aileron 6 can be freely installed. And because this kind of setting up structure, drive assembly 2 can be held in wing box 5 and drive holding section of thick bamboo 3 in the wing preparation, consequently drive assembly 2 also can be like drive holding section of thick bamboo 3, places in the wing inside and prepare together with wing main part 4 and wing box 5 and accomplish, avoids follow-up installation, has not only guaranteed drive assembly 2's axial extensibility, still need not adopt a plurality of member to carry out operations such as later stage concatenation.
In this embodiment, as shown in fig. 3 and 4, the transmission assembly 2 includes a transmission rod, the transmission rod includes a connection rod section 21, the connection rod section 21 is a straight rod with a non-circular cross section, and the flap 6 is provided with a connection hole 61 with a non-circular cross section, which is connected to the connection rod section 21 in a fitting manner. The non-circular rod pieces and the holes can ensure axial penetration connection, and relative rotation of the rod pieces and the holes is avoided as the rod pieces with the circular cross sections. In this embodiment, the cross-section of the connecting rod segment 21 and the connecting hole 61 is a waist-round structure, as shown in fig. 7. In this embodiment, the transfer line is metal material such as stainless steel, ensures structural strength. Before installing aileron 6, can pour into the viscose in to connecting hole 61, can guarantee the glue when later being connected with connecting rod section 21 and even, further strengthened joint strength.
In this embodiment, the transmission rod further includes a tapered rod section 22 connected to the connecting rod section 21, the tapered rod section 22 has a diameter larger than that of the connecting rod section 21 and is connected to the connecting rod section 21 through a small-diameter end; the inner hole of the transmission accommodating barrel 3 is a taper hole with the taper consistent with that of the taper rod section 22, and the taper rod section 22 penetrates through the transmission accommodating barrel 3 with a gap. Lubricating grease can be filled in the gap between the transmission accommodating cylinder 3 and the conical rod section 22, and the conical rod section 22 can freely rotate.
In this embodiment, the transmission accommodating cylinder 3 includes a first bearing 31 and a cylinder 32 for accommodating the tapered rod section 22, the first bearing 31 is disposed at an end of the cylinder 32 close to the aileron 6, and the inner diameter and the outer diameter are respectively in adaptive connection with the tapered rod section 22 and the cylinder 32. The first bearing 31 supports the end of the tapered rod section 22, not only ensuring free rotation, but also ensuring coaxiality with the cylinder 32 and avoiding contact friction.
In this embodiment, as shown in fig. 5 and 6, the transmission rod further includes a cylindrical section 23 connected to the large-diameter end of the tapered rod section 22, a position where the wing box 5 and the wing main body 4 intersect is provided with a limit plate 52, the limit plate 52 is provided with a limit hole 521, the cylindrical section 23 is located on one side of the limit plate 52 facing the wing box 5, and the diameter of the cylindrical section is larger than the aperture of the limit hole 521; the tapered rod segment 22 is located on the side of the limiting plate 52 facing the wing body 4, and the diameter of the large-diameter end is smaller than the aperture of the limiting hole 521. The limiting hole 521 is arranged to realize one-way limiting of axial movement of the transmission rod, namely, the transmission rod is not limited to move towards the wing box 5, when the transmission rod moves towards the wing main body 4, after the transmission rod reaches a set position, the step surface between the conical rod section 22 and the cylindrical section 23 is clamped at the limiting hole 521, excessive entering into the wing main body 4 is avoided, the cylindrical section 23 is ensured to be always positioned in the wing box 5, and an end head for connecting with the driving piece 1 is reserved.
In this embodiment, the transmission assembly 2 further includes a bearing seat 24 and a second bearing 25, the end face of the bearing seat 24 is attached to the surface of the limiting plate 52 facing the wing box 5, and the inner diameter and the outer diameter of the second bearing 25 are respectively in adaptive connection with the cylindrical section 23 and the bearing seat 24, so as to ensure the rotation flexibility of the transmission rod. When the wing box is installed, the bearing seat 24 and the second bearing 25 are connected firstly, then the bearing seat 24 connected with the second bearing 25 is placed into the wing box 5 through the opening 51 and penetrates through the cylindrical section 23, the end face of the bearing seat 24 is attached to the limiting plate 52, and the limiting plate 52 serves as a positioning foundation to enable a worker to sense whether the bearing seat 24 is installed in place or not, so that the wing box is suitable for blind operation inside the wing box 5. Once in position, the bearing block 24 is attached to the wing box 5 by fasteners which penetrate the surface of the wing box 5 and are fastened to the bearing block 24.
In this embodiment, the transmission assembly 2 further includes a third bearing 26, the third bearing 26 is disposed at an end of the connection hole 61 far from the transmission accommodating cylinder 3, and may be embedded in the wing or bonded to the aileron 6, and the connection rod section 21 passes through the connection hole 61 and then is in adaptive connection with the third bearing 26, so as to prevent the connection rod section 21 from rubbing against the wing when the wing deforms.
In this embodiment, as shown in fig. 6, an adapter sheet 11 parallel to the surface of the wing box 5 is connected to the driving member 1, and the driving member 1 is connected to the wing box 5 by a fastener penetrating the surface of the wing box 5 and fastened to the adapter sheet 11; the end face of the cylindrical section 23 is provided with an inserting piece 231, the driving end of the driving piece 1 is provided with a slot 12, the inserting piece 231 is inserted into the slot 12 and is connected with a screw 232 penetrating into a through hole formed in the slot 12 vertically, and the transmission rod can be ensured to rotate synchronously with the driving end of the driving piece 1. In this embodiment, driving piece 1 is the steering wheel, and the whole bending of switching piece 11 is the C shape, and the middle part surface is equipped with the through-hole that allows the drive end to pass, avoids interfering, and both sides are parallel with the top surface, the bottom surface of wing box 5, are convenient for connect.
The installation method of the integrated wing aileron driving device of the embodiment comprises the following steps:
s1: the transmission accommodating cylinder 3 is pre-embedded at a set position in a material for preparing the wing, is positioned between the installation position of the aileron 6 in the wing main body 4 and the wing box 5, and is coaxial with a rotating shaft of the aileron 6;
s2: the transmission assembly 2 is accommodated in the hollow area of the transmission accommodating barrel 3 and the wing box 5;
s3: after the preparation of the wing is finished, injecting adhesive into the connecting hole 61 of the aileron 6, placing the aileron 6 at the installation position of the wing main body 4, rotating the transmission assembly 2 to enable the section of the connecting rod section 21 to be aligned with the section of the connecting hole 61 of the aileron 6, axially moving the transmission assembly 2, and enabling the two to be connected through the adhesive; then installing a bearing seat 24 and a second bearing 25, placing the bearing seat 24 into the wing box 5 through an opening 51, penetrating through the cylindrical section 23 until the bearing seat is attached to the limiting plate 52, and connecting the bearing seat 24 and the wing box 5 through a fastener;
s4: the driving piece 1 is arranged in the wing box 5 through the opening 51, is connected with the slot 12 at the driving end and the inserting piece 231 of the transmission component 2, and is fixed through the screw 232;
s5: and connecting the adapter plate 11 and the wing box 5 through a fastener to complete installation.
The installation method of the integrated wing aileron driving device is used for installing the integrated wing aileron driving device, has the advantages, and is simple in installation steps, convenient to operate and small in required space, so that the dependence on the capability of workers is reduced, the production cost is reduced, the production efficiency is improved, and the maintenance and the repair are convenient.
The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above-described embodiments. It should be apparent to those skilled in the art that modifications and variations can be made without departing from the technical spirit of the present invention.
Claims (10)
1. An integral wing aileron drive, characterized in that: the wing comprises a driving piece (1), a transmission assembly (2) and a transmission accommodating barrel (3), wherein the transmission accommodating barrel (3) is pre-embedded in a wing main body (4) which is integrally formed with a wing box (5) with an opening (51), is positioned between the installation position of an aileron (6) in the wing main body (4) and the wing box (5), and is coaxially arranged with a rotating shaft of the aileron (6); the transmission assembly (2) is movably arranged in the transmission accommodating barrel (3) in a penetrating way, can move along the axial direction when not connected with the driving piece (1), and one end of the transmission assembly is connected with or separated from the aileron (6) positioned at the mounting position; the driving piece (1) is arranged into the wing box (5) from the opening (51), is connected with the other end of the transmission assembly (2) and limits the axial movement of the transmission assembly (2), and drives the transmission assembly (2) to rotate.
2. The integrated-wing aileron drive of claim 1, wherein: the width of the hollow area of the wing box (5) in the axial direction of the transmission containing barrel (3) is not less than the connection length of the transmission assembly (2) and the ailerons (6), and the transmission assembly (2) is contained in the wing box (5) and the transmission containing barrel (3) during wing preparation.
3. The integrated-wing aileron drive of claim 1, wherein: the transmission assembly (2) comprises a transmission rod, the transmission rod comprises a connecting rod section (21), the connecting rod section (21) is a straight rod with a non-circular section, and a connecting hole (61) with a non-circular section, which is connected with the connecting rod section (21) in an adaptive manner, is formed in the aileron (6).
4. The integrated-wing aileron drive of claim 3, wherein: the transmission rod also comprises a conical rod section (22) connected with the connecting rod section (21), the diameter of the conical rod section (22) is larger than that of the connecting rod section (21), and the conical rod section is connected with the connecting rod section (21) through a small-diameter end; the inner hole of the transmission accommodating barrel (3) is a taper hole with the taper consistent with the taper rod section (22), and the taper rod section (22) penetrates through the transmission accommodating barrel (3) with a gap.
5. The integrated-wing aileron drive of claim 4, wherein: the transmission accommodating barrel (3) comprises a first bearing (31) and a barrel body (32) used for accommodating the conical rod section (22), the first bearing (31) is arranged at the end part, close to the aileron (6), of the barrel body (32), and the inner diameter and the outer diameter of the first bearing are respectively in adaptive connection with the conical rod section (22) and the barrel body (32).
6. The integrated-wing aileron drive of claim 4, wherein: the transmission rod further comprises a cylindrical section (23) connected with the large-diameter end of the conical rod section (22), a limiting plate (52) is arranged at the intersection position of the wing box (5) and the wing main body (4), a limiting hole (521) is formed in the limiting plate (52), the cylindrical section (23) is located on one side, facing the wing box (5), of the limiting plate (52), and the diameter of the cylindrical section is larger than the aperture of the limiting hole (521); the conical rod section (22) is positioned on one side of the limiting plate (52) facing the wing main body (4), and the diameter of the large-diameter end is smaller than the aperture of the limiting hole (521).
7. The integrated-wing aileron drive of claim 6, wherein: the transmission assembly (2) further comprises a bearing seat (24) and a second bearing (25), the end face of the bearing seat (24) is attached to the surface, facing the wing box (5), of the limiting plate (52), and the inner diameter and the outer diameter of the second bearing (25) are respectively in adaptive connection with the cylindrical section (23) and the bearing seat (24); the bearing block (24) connected with the second bearing (25) is placed into the wing box (5) through the opening (51) and is connected with the wing box (5) through a fastener penetrating the surface of the wing box (5) and fastened on the bearing block (24).
8. The integrated-wing aileron drive of claim 3, wherein: the transmission assembly (2) further comprises a third bearing (26), the third bearing (26) is arranged at one end, far away from the transmission accommodating barrel (3), of the connecting hole (61), and the connecting rod section (21) penetrates through the connecting hole (61) and then is in adaptive connection with the third bearing (26).
9. The integrated-wing aileron drive of claim 6, wherein: the driving piece (1) is connected with an adapter sheet (11) parallel to the surface of the wing box (5), and the driving piece (1) is connected with the wing box (5) through a fastener penetrating through the surface of the wing box (5) and fastened on the adapter sheet (11); the end face of the cylindrical section (23) is provided with an inserting piece (231), the driving end of the driving piece (1) is provided with a slot (12), and the inserting piece (231) is inserted into the slot (12) and is connected through a screw (232) which vertically penetrates through a through hole formed in the inserting piece and the slot.
10. A method of installing an integral wing aileron drive comprising the steps of:
s1: the transmission accommodating cylinder (3) is pre-embedded at a set position in a material for preparing the wing, is positioned between the installation position of an aileron (6) in a wing main body (4) and a wing box (5), and is coaxial with a rotating shaft of the aileron (6);
s2: the transmission assembly (2) is accommodated in the hollow area of the transmission accommodating barrel (3) and the wing box (5);
s3: after the preparation of the wing is finished, the aileron (6) is placed at the installation position of the wing main body (4), the transmission component (2) is rotated to be aligned to the aileron (6), the transmission component (2) is axially moved, and the aileron (6) is connected by using viscose glue;
s4: placing the driving piece (1) into the wing box (5) through the opening (51), and connecting the driving end of the driving piece with the transmission assembly (2);
s5: and continuing to axially move the transmission assembly (2) until the driving piece (1) reaches the installation position, and connecting the driving piece (1) and the wing box (5) to finish installation.
Priority Applications (1)
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| CN202210054480.4A CN114348235A (en) | 2022-01-18 | 2022-01-18 | Integrated wing aileron driving device and installation method |
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Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB357585A (en) * | 1930-03-20 | 1931-09-25 | Aircraft Improvement Corp | Improvements in aircraft controls |
| GB619169A (en) * | 1946-11-23 | 1949-03-04 | David Williams | Improvements relating to the control of aircraft |
| GB753423A (en) * | 1954-08-30 | 1956-07-25 | Ministerio Da Aeronautica | Improvements in flying machines for horizontal and vertical flight |
| CN101909992A (en) * | 2007-12-30 | 2010-12-08 | 空中客车营运有限公司 | System for actuating at least one regulating flap of an aircraft and a method for checking the system. |
| CN102458995A (en) * | 2009-05-26 | 2012-05-16 | 空中客车营运有限公司 | Aircraft having vertical lift system |
| CN103153791A (en) * | 2010-10-05 | 2013-06-12 | 空中客车德国运营有限责任公司 | High lift system for an aircraft with a separate drive unit for each wing half |
| CN104712692A (en) * | 2013-12-12 | 2015-06-17 | 波音公司 | Motion-damping systems and methods including the same |
| CN104760684A (en) * | 2015-05-08 | 2015-07-08 | 佛山市神风航空科技有限公司 | Airplane provided with wind-ball-driving wind wheels on main lift force front edges |
| CN105151278A (en) * | 2015-08-27 | 2015-12-16 | 中国运载火箭技术研究院 | Control surface differential drive mechanism suitable for unmanned aerial vehicle |
| CN105711830A (en) * | 2016-05-10 | 2016-06-29 | 左建章 | Rotor-wing craft with two tilting flaps with balanced axial vector |
| RU2709976C1 (en) * | 2019-03-22 | 2019-12-23 | Публичное акционерное общество "Авиационный комплекс им. С.В. Ильюшина" | Aircraft wing, aircraft wings caisson, center wing, spar (versions) |
| RU195308U1 (en) * | 2019-09-10 | 2020-01-22 | федеральное государственное бюджетное образовательное учреждение высшего образования "Тольяттинский государственный университет" | ELERON REJECTION DEVICE |
| US20200023952A1 (en) * | 2018-06-21 | 2020-01-23 | Thomas Norman Hesse | Propelling System with Variable Aerodynamic Controls |
| WO2021232753A1 (en) * | 2020-05-22 | 2021-11-25 | 深圳市大疆创新科技有限公司 | Aircraft and aircraft control system |
-
2022
- 2022-01-18 CN CN202210054480.4A patent/CN114348235A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB357585A (en) * | 1930-03-20 | 1931-09-25 | Aircraft Improvement Corp | Improvements in aircraft controls |
| GB619169A (en) * | 1946-11-23 | 1949-03-04 | David Williams | Improvements relating to the control of aircraft |
| GB753423A (en) * | 1954-08-30 | 1956-07-25 | Ministerio Da Aeronautica | Improvements in flying machines for horizontal and vertical flight |
| CN101909992A (en) * | 2007-12-30 | 2010-12-08 | 空中客车营运有限公司 | System for actuating at least one regulating flap of an aircraft and a method for checking the system. |
| CN102458995A (en) * | 2009-05-26 | 2012-05-16 | 空中客车营运有限公司 | Aircraft having vertical lift system |
| CN103153791A (en) * | 2010-10-05 | 2013-06-12 | 空中客车德国运营有限责任公司 | High lift system for an aircraft with a separate drive unit for each wing half |
| CN104712692A (en) * | 2013-12-12 | 2015-06-17 | 波音公司 | Motion-damping systems and methods including the same |
| CN104760684A (en) * | 2015-05-08 | 2015-07-08 | 佛山市神风航空科技有限公司 | Airplane provided with wind-ball-driving wind wheels on main lift force front edges |
| CN105151278A (en) * | 2015-08-27 | 2015-12-16 | 中国运载火箭技术研究院 | Control surface differential drive mechanism suitable for unmanned aerial vehicle |
| CN105711830A (en) * | 2016-05-10 | 2016-06-29 | 左建章 | Rotor-wing craft with two tilting flaps with balanced axial vector |
| US20200023952A1 (en) * | 2018-06-21 | 2020-01-23 | Thomas Norman Hesse | Propelling System with Variable Aerodynamic Controls |
| RU2709976C1 (en) * | 2019-03-22 | 2019-12-23 | Публичное акционерное общество "Авиационный комплекс им. С.В. Ильюшина" | Aircraft wing, aircraft wings caisson, center wing, spar (versions) |
| RU195308U1 (en) * | 2019-09-10 | 2020-01-22 | федеральное государственное бюджетное образовательное учреждение высшего образования "Тольяттинский государственный университет" | ELERON REJECTION DEVICE |
| WO2021232753A1 (en) * | 2020-05-22 | 2021-11-25 | 深圳市大疆创新科技有限公司 | Aircraft and aircraft control system |
Non-Patent Citations (1)
| Title |
|---|
| 张仲桢;: "机翼盒段结构优化分析", 民用飞机设计与研究, no. 01, 31 March 2013 (2013-03-31), pages 42 - 47 * |
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