CN210364374U - Duct and duct aircraft - Google Patents
Duct and duct aircraft Download PDFInfo
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- CN210364374U CN210364374U CN201921180708.4U CN201921180708U CN210364374U CN 210364374 U CN210364374 U CN 210364374U CN 201921180708 U CN201921180708 U CN 201921180708U CN 210364374 U CN210364374 U CN 210364374U
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- culvert
- duct
- ring
- central shaft
- inclined surface
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Abstract
The utility model relates to an aircraft technical field, in particular to duct structural design. A duct, its technical scheme is: the inner end of the culvert beam is inclined downwards, and the culvert beam can form a conical space by rotating for a circle by taking the central shaft as an axis; the propeller and the motor are both arranged on the central shaft and are positioned in the conical space. The culvert beam is arranged in a downward inclined mode, so that component force acting on the culvert beam in the direction perpendicular to the length direction is reduced, and the inward acting force of the culvert ring along the culvert beam caused by deformation can be reduced. The contact surface of the culvert beam and the culvert ring is an inclined surface, so that a larger glue joint area is formed between the culvert beam and the culvert ring, the connection strength is increased, and when the culvert beam is stressed in a rising way, the lower end of the glue joint of the culvert beam is basically not subjected to shearing force, so that the connection is firmer. The utility model discloses avoided the screw in the duct circle relative duct roof beam the position too high, the focus is lower relatively, makes the whole of duct arrange more harmoniously. The utility model also discloses an aircraft including this duct.
Description
Technical Field
The utility model relates to an aircraft technical field, in particular to duct structural design.
Background
In the ducted aircraft, a plurality of ducted girders are located between the ducted ring and the central shaft for supporting the central shaft on which the propeller, the motor and other parts are mounted. The culvert beam is generally horizontally arranged, and the structure is relatively simple, so that the design and the installation are simplified, the length of the culvert beam is shorter, the weight is lighter, and the lightweight requirement is easily met. But the disadvantage is that the height of the ducted ring is increased due to the fact that the parts mounted on the central shaft are stacked layer by layer in the height direction and the whole arrangement is completed. Due to the increased height of the culvert ring, the connection strength of the culvert ring and the culvert beam needs to be enhanced, resulting in an increase in the overall weight of the culvert aircraft. Another disadvantage is that horizontally arranged culvert beams, as shown in figure 1, are flexible when the aircraft is forced up, and are susceptible to excessive stretching and failure at the lower end where they are glued to the culvert rings.
SUMMERY OF THE UTILITY MODEL
The utility model aims at: in order to overcome the defects of the prior art, a lightweight and structurally firm duct design scheme is provided, and an aircraft comprising the duct is provided.
The utility model discloses a technical scheme is: a culvert is provided, at least two culvert beams are arranged in a culvert ring, the outer ends of the culvert beams are connected to the inner wall of the culvert ring, and the inner ends of the culvert beams are connected to a central shaft; the inner end of the culvert beam is inclined downwards; the culvert beam rotates for a circle by taking the central shaft as an axis to form a conical space; the propeller, the motor and other parts are all arranged on the central shaft and are positioned in the conical space.
Because the culvert beam is obliquely arranged, the contact surface of the culvert beam and the culvert ring is an inclined surface, the inclined surface has a larger area compared with the cross section of the culvert beam body, and the inclined surface is used for being cemented with the culvert ring, so that the culvert beam and the culvert ring have a larger cementing area, and the connection strength is increased. In the conical space formed by the rotation of the propeller, the motor and other parts of the ducted beam, the propeller is lifted up at the center of the ducted beam by the design so as to avoid the rotating space of the propeller, and meanwhile, the relative positions and the azimuth relations of the ducted beam and the propeller are compact, so that the situation that the propeller is too high relative to the ducted beam in a ducted ring is avoided.
On the basis of the scheme, in order to ensure that the whole culvert has better stability, the outer end of the culvert beam is positioned in the middle position of the culvert ring in the height direction. Because the culvert ring and the culvert beam are both positioned at the outer side of the propeller, the culvert ring has better containment for the propeller, and the safety is improved.
On the basis of the scheme, the cross section area of the culvert beam is further gradually reduced from outside to inside, and the cross section area of any position of the culvert beam is in direct proportion to the distance from the cross section to the central shaft; the inner sides of the culvert beams are thin, the culvert beams can avoid propellers and other parts, the bending moment borne by the culvert beams is increased along with the increase of the distance from the central shaft, the outer sides of the culvert beams are thick, the connection strength and the bending resistance of the culvert beams and the culvert ring can be enhanced, and the culvert ring and the culvert beams are connected more firmly.
The other technical scheme of the invention is as follows: a ducted aircraft comprising a duct as described in the above scheme, and a fuselage of the aircraft;
the culvert is provided with a connecting beam; the machine body is provided with an installation interface; the connecting beam is connected with the mounting interface through a flange.
Furthermore, the connecting beam is obliquely arranged, and one end of the connecting beam, which is far away from the culvert, is inclined upwards; the mounting surface of the mounting interface is an inclined surface with an upward inclined surface; the mounting surface of the flange is an inclined surface with a downward inclined surface. The connecting beams are obliquely arranged, so that the connecting area of the connecting beams and the contact surface of the machine body is increased, the lateral bending resistance and the torsion resistance of the connecting part are increased, and the deflection of the duct to the interior of the machine body can be reduced due to the bending deformation. Meanwhile, due to the inclination of the contact surface, the interference with the ducted ring during assembly is avoided, and the assembly is easier. In addition, the connecting beams arranged in an inclined manner reduce the interval between the ducts on the two sides of the aircraft body and the aircraft body, so that the overall structure of the aircraft is compact; and the connecting beam is obliquely arranged, so that the length of the connecting beam is increased, and the course bending resistance of the connecting beam is improved. The connecting beam is connected with the machine body through the flange plate, so that the contact area of the connecting beam and the machine body is further increased, and the torsion resistance of the connecting part of the duct and the machine body is enhanced. The flange plate is adopted for connection, so that the culvert is convenient to be close to the machine body, the mounting positions at the two ends of the connecting beam are staggered, and the assembly is easy. The installation surface of the flange plate inclines downwards, so that the gravity of the whole culvert can partially act on the aircraft fuselage, and the overlarge shearing force between the flange plate and the aircraft fuselage is avoided.
In the above scheme, specifically, the connecting beam has two design forms: firstly, the outer end of the culvert beam penetrates out of the culvert ring, and a connecting beam is formed on the outer side of the culvert ring; and secondly, the outer wall of the culvert ring is provided with a connecting pipe, so that a connecting beam is formed.
Because the length of the connecting beam is very small, the culvert beam extension scheme is adopted, and the flange plate and the culvert beam can be integrally formed and manufactured; the scheme that the connecting pipe is arranged on the outer wall is adopted, the connecting pipe and the flange plate can be integrally formed to form the flange plate with the neck.
On the basis of the scheme, a connection reinforcing structure is arranged at the position, corresponding to the installation interface, of the inner side wall of the machine body, and the machine body is locally reinforced.
Has the advantages that: the utility model discloses the culvert roof beam in the culvert sets up to the decline, makes the component that is used in perpendicular to culvert roof beam length direction on reduce, can reduce the culvert circle and produce along the inward effort of culvert roof beam because of the deformation. The contact surface of the culvert beam and the culvert ring is an inclined surface, so that a larger glue joint area is formed between the culvert beam and the culvert ring, the connection strength is increased, and when the culvert beam is stressed in a rising way, the lower end of the glue joint of the culvert beam is basically not subjected to shearing force, so that the connection is firmer. The utility model discloses make the relative position and the position relation compactness of duct roof beam, screw, avoided the screw in the duct circle relative duct roof beam the position too high, the focus is lower relatively, makes the whole of duct arrange more harmoniously. The utility model discloses the scheme still discloses the aircraft based on this duct structure.
Drawings
Fig. 1 is a schematic view of a horizontal arrangement of culvert beams in the background art subjected to bending deformation;
fig. 2 is a schematic structural view of a middle duct of the present invention;
figure 3 is a side view of the central duct of the present invention;
FIG. 4 is a schematic structural view of the ducted aircraft of the present invention;
FIG. 5 is a schematic view of the fuselage structure of FIG. 4 with the hatch cover removed;
in the figure: 1-culvert beam, 2-culvert beam, 3-central shaft, 4-propeller, 5-motor, 6-connecting beam, 7-flange, 8-conical space, 9-culvert, 10-fuselage, 11-installation interface, 12-reinforced structure.
Detailed Description
Embodiment 1, refer to fig. 2 and 3, a culvert 9, the inside of a culvert ring 2 is provided with at least two culvert beams 1, the outer ends of the culvert beams 1 are connected on the inner wall of the culvert ring 2, the inner ends of the culvert beams 1 are connected on a central shaft 3; the inner end of the culvert beam 1 is inclined downwards; the culvert beam 1 rotates for a circle by taking the central shaft 3 as an axis to form a conical space 8; the propeller 4, the motor 5 and other parts are all arranged on the central shaft 3 and are positioned in the conical space 8. In this example, three ducted beams 1 are provided, the central shaft 3 is a tray, the motor 5 is clamped in the tray, and the propeller 4 is installed above the motor 5.
Because the contact surface of the culvert beam 1 and the culvert ring 2 is an inclined surface, the inclined surface has a larger area compared with the cross section of the culvert beam 1, and the inclined surface is used for cementing with the culvert ring, so that a larger cementing area is formed between the culvert beam 1 and the culvert ring 2, and the connection strength is increased. The propeller 4 and the motor 5 are located in the conical space 8, the propeller 4 is lifted up at the center of the culvert beam 1 due to the design so as to avoid the rotating space of the propeller 4, the culvert beam 1 and the propeller 4 are close to each other as much as possible, the overall arrangement is centralized, the overlarge height difference between the culvert beam 1 and the propeller 4 is avoided, the gravity center is relatively low, and the overall arrangement of the culvert is more coordinated.
Further, in order to give the whole culvert 9 better stability, the outer ends of the culvert beams 1 in this example are located in the middle position in the height direction of the culvert rings 2. Because the culvert ring 2 and the culvert beam 1 are both positioned at the outer side of the propeller, the culvert ring has better containment for the propeller, and the safety is improved.
Furthermore, in the embodiment, the cross-sectional area of the culvert beam 1 is gradually reduced from outside to inside, and the cross-sectional area of any position of the culvert beam 1 is in direct proportion to the distance from the cross section to the central shaft 3; the culvert beam 1 is thin towards the inner side and can avoid the propeller and other parts, the bending moment borne by the culvert beam 1 is increased along with the increase of the distance from the central shaft 3, the outer side of the culvert beam 1 is thick and can enhance the connection strength and the bending resistance of the culvert ring 2, and the culvert ring 2 is more firmly connected with the culvert beam 1.
Embodiment 2, see fig. 4 and 5, a ducted aircraft comprising a duct 9 as described in embodiment 1, and a fuselage 10 of the aircraft; the ducts 9 are arranged symmetrically on both sides of the fuselage 10, in this case 3 ducts per side of the fuselage 10.
The culvert 9 is provided with a connecting beam 6; the body 10 is provided with a mounting interface 11; the connecting beam 6 is connected with the mounting interface 11 through a flange 7.
Furthermore, the connecting beam 6 is obliquely arranged, and one end of the connecting beam 6, which is far away from the culvert 9, is obliquely upwards; the mounting surface of the mounting interface 11 is an inclined surface with an upward inclined surface; the mounting surface of the flange 7 is an inclined surface with a downward inclined surface. The connecting beams 6 are obliquely arranged, so that the connecting area of the contact surface of the connecting beams 6 and the fuselage 10 is increased, the lateral bending resistance and the torsion resistance of the connecting part are increased, and the deflection of the duct to the interior of the fuselage can be relieved by bending deformation. Meanwhile, due to the inclination of the contact surface, the interference with the ducted ring 2 during assembly is avoided, and the assembly is easier. In addition, the connecting beams 6 arranged obliquely reduce the interval between the ducts 9 at the two sides of the fuselage 10 and the fuselage 10, so that the overall structure of the aircraft is compact; and the connecting beam 6 is obliquely arranged, so that the length of the connecting beam 6 is increased, and the course bending resistance of the connecting beam 6 is improved. The connecting beam 6 is connected with the fuselage 10 by the flange 7, so that the contact area of the connecting beam 6 and the fuselage 10 is further increased, and the torsion resistance of the joint of the duct 9 and the fuselage 10 is enhanced. Compared with the traditional lug joint, the flange 7 is easier to assemble and has stronger torsion resistance and stronger lateral bending resistance; the flange 7 is adopted for connection, so that the duct 9 is convenient to be close to the machine body 10, the mounting positions of the two ends of the connecting beam 6 can be staggered, and the assembly is easy. The mounting surface of the flange 7 is inclined downwards, so that the gravity of the whole duct 9 can partially act on the aircraft fuselage 10, and excessive shearing force between the flange 7 and the aircraft fuselage 10 is avoided.
Example 3, on the basis of example 2, the culvert beam 6 is further defined:
the connecting beam 6 has two design modes: firstly, as shown in figure 3, the outer end of the culvert beam 1 penetrates out of the culvert ring 2, and a connecting beam 6 is formed on the outer side of the culvert ring 2; and secondly, connecting pipes are arranged on the outer wall of the culvert ring 2, so that a connecting beam 6 is formed. When the first mode is adopted, the wires in the culvert 9 are directly led out through the inside of the culvert beam 1; when the second mode is adopted, the wires in the culvert 9 sequentially pass through the through holes in the culvert beam 1 and the culvert 9, and the inside of the connecting pipe is led out.
Because the length of the connecting beam 6 is very small, the ducted beam 1 is extended, and the flange 7 and the ducted beam 1 can be integrally formed; the scheme that the connecting pipe is arranged on the outer wall is adopted, the connecting pipe and the flange plate 7 can be integrally formed to form the flange plate with the neck.
Embodiment 4, on the basis of embodiment 2 or 3, further, referring to fig. 5, a connection reinforcing structure 12 is provided at a position corresponding to the mounting interface 11 on the inner side wall of the body 10 for locally reinforcing the body 10. The reinforcing structure 12 includes: a wall plate attached to the inner side wall of the body 10, and a web plate connected to the wall plate and extending downward; the web extends downwards, the pulling force generated by taking off and landing the duct 9 is transmitted to the lower part of the machine body 10, the strength defect caused by opening a hatch and an equipment security inspection port on the upper part of the machine body 10 can be avoided, and meanwhile, the upper part of the machine body 10 is prevented from bearing larger load.
Although the invention has been described in detail with respect to the general description and the specific embodiments, it will be apparent to those skilled in the art that modifications and improvements can be made based on the invention. Therefore, such modifications and improvements are intended to be within the scope of the invention as claimed.
Claims (10)
1. The utility model provides a duct (9), duct roof beam (1) outer end is connected on the inner wall of duct circle (2), and the connection of duct roof beam (1) inner is on center pin (3), its characterized in that: the inner end of the culvert beam (1) is inclined downwards; the culvert beam (1) rotates for a circle by taking the central shaft (3) as an axis to form a conical space (8); the propeller (4) and the motor (5) are both arranged on the central shaft (3) and are positioned in the conical space (8).
2. A culvert according to claim 1, characterized in that the cross-sectional area of the culvert beams (1) is decreasing from the outside inwards.
3. A duct according to claim 1 or 2, wherein: the outer ends of the culvert beams (1) are positioned in the middle of the culvert ring (2) in the height direction.
4. A ducted aircraft, characterized in that: it includes:
the duct (9) according to any of claims 1 to 3, and a fuselage (10);
the culvert (9) is provided with a connecting beam (6); the machine body (10) is provided with a mounting interface (11); the connecting beam (6) is connected with the mounting interface (11) through a flange (7).
5. The ducted aircraft according to claim 4, wherein: the connecting beam (6) is obliquely arranged, and one end, far away from the culvert (9), of the connecting beam (6) is inclined upwards; the mounting surface of the mounting interface (11) is an inclined surface with an upward inclined surface; the mounting surface of the flange plate (7) is an inclined surface with a downward inclined surface.
6. The ducted aircraft according to claim 5, wherein: the outer end of the culvert beam (1) penetrates out of the culvert ring (2), and the connecting beam (6) is formed on the outer side of the culvert ring (2).
7. The ducted aircraft according to claim 6, wherein: the flange plate (7) and the culvert beam (1) are integrally formed.
8. The ducted aircraft according to claim 4 or 5, wherein: the connecting beam (6) is a connecting pipe connected between the outer wall of the culvert ring (2) and the machine body (10).
9. The ducted aircraft according to claim 8, wherein: the connecting pipe and the flange plate (7) are integrally formed to form a flange plate with a neck.
10. The ducted aircraft according to claim 4, wherein: and a connection reinforcing structure (12) is arranged on the inner side wall of the machine body (10) at a position corresponding to the mounting interface (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921180708.4U CN210364374U (en) | 2019-07-25 | 2019-07-25 | Duct and duct aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921180708.4U CN210364374U (en) | 2019-07-25 | 2019-07-25 | Duct and duct aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210364374U true CN210364374U (en) | 2020-04-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921180708.4U Active CN210364374U (en) | 2019-07-25 | 2019-07-25 | Duct and duct aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN210364374U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11472533B2 (en) * | 2019-12-31 | 2022-10-18 | Textron Innovations Inc. | Stators located aft of duct ring |
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2019
- 2019-07-25 CN CN201921180708.4U patent/CN210364374U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11472533B2 (en) * | 2019-12-31 | 2022-10-18 | Textron Innovations Inc. | Stators located aft of duct ring |
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