CN117566134A - Integrated unmanned aerial vehicle wing rotating mechanism and integrated unmanned aerial vehicle - Google Patents
Integrated unmanned aerial vehicle wing rotating mechanism and integrated unmanned aerial vehicle Download PDFInfo
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- CN117566134A CN117566134A CN202311538433.8A CN202311538433A CN117566134A CN 117566134 A CN117566134 A CN 117566134A CN 202311538433 A CN202311538433 A CN 202311538433A CN 117566134 A CN117566134 A CN 117566134A
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- aerial vehicle
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- 230000007246 mechanism Effects 0.000 title claims abstract description 37
- 230000000149 penetrating effect Effects 0.000 claims abstract description 4
- 230000008878 coupling Effects 0.000 claims 1
- 238000010168 coupling process Methods 0.000 claims 1
- 238000005859 coupling reaction Methods 0.000 claims 1
- 230000005540 biological transmission Effects 0.000 abstract description 8
- 230000032258 transport Effects 0.000 description 4
- 230000017105 transposition Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides an integrated unmanned aerial vehicle wing rotating mechanism and an integrated unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, wherein the rotating mechanism comprises: the shell is used for being arranged in the unmanned aerial vehicle body, the top end of the shell is provided with a mounting opening, and an annular concave surface is arranged at the inner top end of the shell and positioned at the periphery of the mounting opening; the top end circumference side of the rotating center piece is provided with an annular convex surface, the rotating center piece is rotationally connected in the shell, and the annular convex surface is rotationally connected in the annular concave surface; the bottom end of the rotary connecting piece penetrates through the mounting opening and is connected with the top end of the rotary center piece, the top end of the rotary connecting piece is used for penetrating through the top of the machine body and is connected with the wing of the unmanned aerial vehicle, and the wing can rotate relative to the machine body; the rotary mechanism is simple in form and compact in assembly mode, and can simultaneously realize rotation of the wing and transmission of wing load to the fuselage.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an integrated unmanned aerial vehicle wing rotating mechanism and an integrated unmanned aerial vehicle.
Background
For unmanned aerial vehicle with larger wingspan, the projection area of the unmanned aerial vehicle is larger in the wing unfolding state, and a larger storage space is needed. For the convenience of unmanned aerial vehicle's storage and transportation, traditional unmanned aerial vehicle that span is great is often designed into detachable wing, stores and transports unmanned aerial vehicle after will dismantling, assembles when having work task again. The traditional unmanned aerial vehicle with the detachable wings occupies larger storage and transportation space due to scattered parts, and the disassembly of the wings can increase extra workload, so that the unmanned aerial vehicle with large formation is unfavorable for storage, transportation and quick unfolding.
Disclosure of Invention
The invention aims to provide an integrated unmanned aerial vehicle wing rotating mechanism and an integrated unmanned aerial vehicle aiming at the defects of the prior art, so as to solve the problems that the traditional unmanned aerial vehicle with detachable wings, which is proposed in the background art, occupies larger storage and transportation space due to scattered parts, and the disassembly of the wings can increase extra workload, and is unfavorable for storage, transportation and quick expansion of unmanned aerial vehicles for large formation.
In order to achieve the above object, the present invention provides an integrated unmanned aerial vehicle wing rotation mechanism, comprising:
the shell is used for being arranged in the body of the unmanned aerial vehicle, the top end of the shell is provided with a mounting opening, and an annular concave surface is arranged at the inner top end of the shell and positioned at the periphery of the mounting opening;
the top end circumference side of the rotating center piece is provided with an annular convex surface, the rotating center piece is rotationally connected in the shell, and the annular convex surface is rotationally connected in the annular concave surface;
the bottom end of the rotary connecting piece penetrates through the mounting opening and is connected with the top end of the rotary center piece, the top end of the rotary connecting piece is used for penetrating through the top of the fuselage and is connected with the wing of the unmanned aerial vehicle, and the wing can rotate relative to the fuselage;
the indexing adjusting piece is arranged in the machine body, and the output end of the indexing adjusting piece is connected with the rotation center piece.
Preferably, the integrated unmanned aerial vehicle wing rotating mechanism comprises a bearing, the bearing is arranged in the shell and sleeved on the rotating center piece, an outer shell of the bearing is connected with the inner side wall of the shell in an interference fit manner, and an inner shell of the bearing is connected with the rotating center piece in an interference fit manner.
Preferably, the bearing is a tapered roller bearing.
Preferably, the annular convex surface and the annular concave surface are mutually matched conical surfaces.
Preferably, the rotary connecting piece comprises a rotary connecting body, a rotary upper connecting flange plate is arranged at the top end of the rotary connecting body, and a rotary lower connecting flange plate is arranged at the bottom end of the rotary connecting body.
Preferably, the rotating center piece comprises a rotating center body, a positioning groove is formed in the middle of the top end of the rotating center body, and a plurality of first connecting holes are distributed in the positioning groove.
Preferably, the shell comprises a shell body and a mounting plate, a plurality of mounting grooves are distributed on the periphery of the shell body, the top ends of the mounting grooves extend out of the top end of the shell body, at least one second connecting hole is formed in the bottom end of the mounting groove, a plurality of third connecting holes are distributed on the periphery of the plate surface of the mounting plate, and the second connecting holes are used for being connected with the third connecting holes.
An integrated unmanned aerial vehicle, comprising:
an integrated unmanned aerial vehicle wing rotating mechanism;
a wing;
the top of fuselage is equipped with the opening, and the casing sets up in the opening, the top of swivelling joint spare runs through the opening, and with the wing is connected.
Preferably, the body comprises a body skin, a body front connecting frame and a body rear connecting frame, the body skin is connected to the body front connecting frame and the body rear connecting frame, and the bottom end of the shell is connected to the top of the body front connecting frame and the body rear connecting frame.
Preferably, the wing comprises a wing skin, a wing front beam, a wing rear beam and a wing flange, wherein the wing skin is connected to the wing front beam and the wing rear beam, the wing flange is connected to the bottoms of the wing front beam and the wing rear beam, and the wing flange is connected with the top end of the rotary connecting piece.
The invention provides an integrated unmanned aerial vehicle wing rotating mechanism and an integrated unmanned aerial vehicle, which have the beneficial effects that: the rotating center piece of the rotating mechanism is rotationally connected in the shell, the annular convex surface is rotationally connected in the annular concave surface, when the unmanned aerial vehicle stops flying, the wing is pushed, the wing can rotate around the axis of the rotating center piece, the wing is in a parallel state with the machine body after rotating, the projection area of the unmanned aerial vehicle can be reduced, and the unmanned aerial vehicle is convenient to store and transport;
when a work task exists, the wing can be rotated, so that the wing and the fuselage are in a vertical state, and the unmanned aerial vehicle can be rapidly unfolded;
when unmanned aerial vehicle flight state, the lift of wing will upwards stimulate the rotation center piece, and annular convex surface and annular concave surface contact will realize the transmission of wing lift to the fuselage, simultaneously, annular convex surface and annular concave surface also will be in the state of compressing tightly, can guarantee that the axis position of rotation center piece does not move.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The foregoing and other objects, features and advantages of the invention will be apparent from the following more particular descriptions of exemplary embodiments of the invention as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the invention.
FIG. 1 illustrates a schematic cross-sectional structural view of an integrated unmanned aircraft wing rotation mechanism according to an embodiment of the present invention;
FIG. 2 shows an enlarged schematic view of the structure of FIG. 1 at A;
FIG. 3 illustrates a schematic diagram of the fuselage structure of an integrated unmanned aerial vehicle according to an embodiment of the present invention;
FIG. 4 shows a schematic diagram of the wing structure of an integrated unmanned aerial vehicle according to an embodiment of the present invention;
FIG. 5 shows a schematic structural view of an integrated unmanned aircraft wing in a vertical position with respect to the aircraft fuselage, according to an embodiment of the present invention;
FIG. 6 shows a schematic structural view of an integrated unmanned aircraft wing in parallel with the fuselage, according to an embodiment of the present invention;
FIG. 7 illustrates a schematic structural view of a rotary connection of an integrated unmanned aerial vehicle wing rotary mechanism, according to an embodiment of the present invention;
FIG. 8 illustrates a structural schematic diagram of a rotational center piece of an integrated unmanned aerial vehicle wing rotation mechanism, according to an embodiment of the present invention;
FIG. 9 illustrates a schematic structural view of an inner housing of an integrated unmanned aircraft wing rotation mechanism according to an embodiment of the present invention;
FIG. 10 illustrates a schematic structural view of a bearing needle of an integrated unmanned aircraft wing rotation mechanism in accordance with an embodiment of the present invention;
FIG. 11 illustrates a schematic structural view of an outer housing of an integrated unmanned aircraft wing rotation mechanism according to an embodiment of the present invention;
FIG. 12 illustrates a schematic structural view of a mounting plate of an integrated unmanned aircraft wing rotation mechanism according to an embodiment of the present invention;
fig. 13 shows a schematic structural view of a housing of an integrated unmanned aerial vehicle wing rotation mechanism according to an embodiment of the present invention.
Reference numerals illustrate:
1. a body; 101. a fuselage skin; 102. a front frame of the machine body; 103. a frame is connected to the rear of the machine body; 2. a wing; 201. a wing skin; 202. a wing front beam; 203. a wing back beam; 204. a wing flange; 3. a rotary connector; 301. rotating the upper connecting flange plate; 302. rotating the lower connecting flange plate; 4. a rotation center; 401. a first connection hole; 5. a housing; 501. a shell body; 502. a mounting plate; 503. a second connection hole; 504. a third connection hole; 6. a convex surface; 7. a concave surface; 8. a bearing; 801. an outer housing; 802. an inner housing; 803. bearing needle rollers.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the preferred embodiments of the present invention are described below, it should be understood that the present invention may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
As shown in fig. 1 and 2, the present invention provides an integrated unmanned aerial vehicle wing rotation mechanism, which includes:
the shell 5 is arranged in the unmanned aerial vehicle body 1, the top end of the shell 5 is provided with a mounting opening, and an annular concave surface 7 is arranged at the inner top end of the shell 5 and positioned at the periphery of the mounting opening;
the rotating center piece 4, the top end circumference side of the rotating center piece 4 is provided with an annular convex surface 6, the rotating center piece 4 is rotationally connected in the shell 5, and the annular convex surface 6 is rotationally connected in the annular concave surface 7;
the bottom end of the rotary connecting piece 3 penetrates through the mounting opening and is connected with the top end of the rotary center piece 4, the top end of the rotary connecting piece 3 is used for penetrating through the top of the fuselage 1 and is connected with the wing 2 of the unmanned aerial vehicle, and the wing 2 can rotate relative to the fuselage 1;
the transposition adjusting piece is arranged in the machine body 1, and the output end of the transposition adjusting piece is connected with the rotation center piece 4.
Specifically, in order to solve the problems that the traditional detachable unmanned aerial vehicle occupies larger storage and transportation space due to scattered parts, and the disassembly of the wing increases extra workload, and for large-formation unmanned aerial vehicle, the storage, transportation and quick unfolding are not facilitated, the invention provides an integrated unmanned aerial vehicle wing rotating mechanism and an integrated unmanned aerial vehicle, wherein a rotating center piece 4 of the rotating mechanism is rotationally connected in a shell 5, an annular convex surface 6 is rotationally connected in an annular concave surface 7, when the unmanned aerial vehicle stops flying, the wing 2 is pushed, the wing 2 can rotate around the axis of the rotating center piece 4, the wing 2 is in a parallel state with a machine body 1 after rotating, the projection area of the unmanned aerial vehicle can be reduced, and the unmanned aerial vehicle is convenient to store and transport; when a work task exists, the wing 2 can be rotated, so that the wing 2 and the fuselage 1 are in a vertical state, and the unmanned aerial vehicle can be rapidly unfolded; when unmanned aerial vehicle flight state, the lift of wing 2 will upwards stimulate rotation center piece 4, and annular convex surface 6 and annular concave surface 7 contact will realize the transmission of wing 2 lift to fuselage 1, and simultaneously, annular convex surface 6 also will be in the state of compressing tightly with annular concave surface 7, can guarantee that the axis position of rotation center piece 4 does not move.
The rotating mechanism realizes the rotation of the wing 2, simultaneously realizes the transmission of the load of the wing 2 to the fuselage 1, and is simpler and more compact in structure.
The transposition adjusting piece can be a steering engine, the steering engine can control the transposition of the rotary center piece 4, and a worker can operate the steering engine to realize the rotation of the wing 2.
Preferably, the integrated unmanned aerial vehicle wing rotary mechanism comprises a bearing 8, wherein the bearing 8 is arranged in the shell 5 and sleeved on the rotary center piece 4, an outer shell 801 of the bearing 8 is connected with the inner side wall of the shell 5 in an interference fit manner, and an inner shell 802 of the bearing 8 is connected with the rotary center piece 4 in an interference fit manner.
As shown in fig. 2, 8-10, the bearing 8 is preferably a tapered roller bearing.
Specifically, an inclined annular groove is formed between the inner side of the outer housing 801 of the bearing 8 and the surface opposite to the inner housing 801 of the bearing 8, and a plurality of bearing needle rollers 803 of the bearing 8 are distributed in the annular groove to form a tapered roller bearing, wherein the bearing needle rollers 803 are obliquely arranged and have a centripetal effect, so that the rotation axis position of the wing 2 can be kept unchanged under the action of the dead weight load of the wing 2.
As shown in fig. 2, the annular convex surface 6 and the annular concave surface 7 are preferably conical surfaces that cooperate with each other.
Specifically, when unmanned aerial vehicle flight state, the lift of wing 2 will upwards stimulate rotatory central piece 4, and annular convex surface 6 and annular concave surface 7 contact will realize the transmission of wing 2 lift to fuselage 1, simultaneously, annular convex surface 6 and annular concave surface 7 will also be in the state of compressing tightly, because annular convex surface 6 and annular concave surface 7 are the conical surface of mutually supporting, can further guarantee that the axis position of rotatory central piece 4 does not remove.
As shown in fig. 7, preferably, the rotary connector 3 includes a rotary connector, a rotary upper connection flange 301 is provided at a top end of the rotary connector, and a rotary lower connection flange 302 is provided at a bottom end of the rotary connector.
As shown in fig. 8, the rotation center 4 preferably includes a rotation center body, and a positioning groove is provided in the middle of the top end of the rotation center body, and a plurality of first connection holes 401 are distributed in the positioning groove.
Specifically, the plurality of first connecting holes 401 are distributed with two circles of connecting holes, and the rotating lower connecting flange 302 is disposed in the positioning groove and is connected with the first connecting holes 401 through bolts.
As shown in fig. 12 and 13, preferably, the housing 5 includes a housing 501 and a mounting plate 502, wherein a plurality of mounting slots are distributed on the periphery of the housing 501, the top ends of the mounting slots extend out of the top end of the housing 501, at least one second connecting hole 503 is provided at the bottom end of the mounting slots, a plurality of third connecting holes 504 are distributed on the periphery of the plate surface of the mounting plate 502, and the second connecting holes 503 are used for being connected with the third connecting holes 504.
Specifically, the second connection hole 503 is used to be connected to the third connection hole 504 by a bolt.
As shown in fig. 3 to 6, an integrated unmanned aerial vehicle includes:
an integrated unmanned aerial vehicle wing rotating mechanism;
a wing 2;
the fuselage 1, the top of fuselage 1 is equipped with the opening, and casing 5 sets up in the opening, and the top of swivelling joint spare 3 runs through the opening to be connected with wing 2.
Preferably, the body 1 comprises a body skin 101, a body front connecting frame 102 and a body rear connecting frame 103, wherein the body skin 101 is connected to the body front connecting frame 102 and the body rear connecting frame 103, and the bottom end of the shell 5 is connected to the top of the body front connecting frame 102 and the body rear connecting frame 103.
Specifically, mounting panel 502 is connected with the top of connecting frame 102 behind the fuselage and the fuselage, and the load of casing 5 is finally transmitted to fuselage 1 to rotation center piece 4 transmission, is equipped with the through-hole on the mounting panel 502, and the steering wheel is connected on connecting frame 102 behind the fuselage or the fuselage 103, and the output of steering wheel runs through the through-hole and can be connected with rotation center piece 4.
Preferably, the wing 2 comprises a wing skin 201, a wing front beam 202, a wing rear beam 203 and a wing flange 204, wherein the wing skin 2 is connected to the wing front beam 202 and the wing rear beam 203, the wing flange 204 is connected to the bottoms of the wing front beam 202 and the wing rear beam 203, and the wing flange 204 is connected to the top end of the rotary connector 3.
Specifically, the wing 2 is a main bearing component of the wing 2 formed by a wing skin 201, a wing front beam 202, a wing rear beam 203 and a wing flange 204, the rotary connecting piece 3 is a connecting tie of the wing 2 and the rotary central core piece 4, the rotary upper connecting flange 301 is connected with the wing flange 204 through bolts, and the rotary lower connecting flange 302 is connected with the first connecting hole 401 through bolts.
In summary, when the integrated unmanned aerial vehicle wing rotating mechanism is implemented, when the unmanned aerial vehicle is in a stop-flight state, the wing 2 is pushed, so that the wing 2 can rotate around the axis of the rotating center piece 4, the wing 2 is in a parallel state with the machine body 1 after rotating, the projection area of the unmanned aerial vehicle can be reduced, and the unmanned aerial vehicle is convenient to store and transport; when a work task exists, the wing 2 can be rotated, so that the wing 2 and the fuselage 1 are in a vertical state, and the unmanned aerial vehicle can be rapidly unfolded; when the unmanned aerial vehicle is in a flight state, the lifting force of the wing 2 pulls the rotating center piece 4 upwards, the annular convex surface 6 is contacted with the annular concave surface 7 to realize the transmission of the lifting force of the wing 2 to the fuselage 1, and meanwhile, the annular convex surface 6 and the annular concave surface 7 are in a compression state, so that the axial position of the rotating center piece 4 can be ensured not to move; the rotating mechanism is simple in form and compact in assembly mode, and can simultaneously realize rotation of the wing 2 and transmission of load of the wing 2 to the fuselage 1.
The foregoing description of embodiments of the invention has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described.
Claims (9)
1. An integrated unmanned aerial vehicle wing rotary mechanism, characterized in that, this rotary mechanism includes:
the shell is used for being arranged in the body of the unmanned aerial vehicle, the top end of the shell is provided with a mounting opening, and an annular concave surface is arranged at the inner top end of the shell and positioned at the periphery of the mounting opening;
the top end circumference side of the rotating center piece is provided with an annular convex surface, the rotating center piece is rotationally connected in the shell, and the annular convex surface is rotationally connected in the annular concave surface;
the bottom end of the rotary connecting piece penetrates through the mounting opening and is connected with the top end of the rotary center piece, the top end of the rotary connecting piece is used for penetrating through the top of the fuselage and is connected with the wing of the unmanned aerial vehicle, and the wing can rotate relative to the fuselage;
the indexing adjusting piece is arranged in the machine body, and the output end of the indexing adjusting piece is connected with the rotation center piece.
2. The integrated unmanned aerial vehicle wing rotating mechanism according to claim 1, wherein the integrated unmanned aerial vehicle wing rotating mechanism comprises a bearing, the bearing is arranged in the shell and sleeved on the rotating center piece, an outer shell of the bearing is in interference fit connection with the inner side wall of the shell, and an inner shell of the bearing is in interference fit connection with the rotating center piece.
3. The integrated unmanned aerial vehicle wing rotation mechanism of claim 2, wherein the bearing is a tapered roller bearing.
4. The integrated unmanned aerial vehicle wing rotating mechanism according to claim 1, wherein the rotating connector comprises a rotating connector, a rotating upper connecting flange is arranged at the top end of the rotating connector, and a rotating lower connecting flange is arranged at the bottom end of the rotating connector.
5. The integrated unmanned aerial vehicle wing rotating mechanism according to claim 1, wherein the rotating center piece comprises a rotating center body, a positioning groove is formed in the middle of the top end of the rotating center body, and a plurality of first connecting holes are distributed in the positioning groove.
6. The integrated unmanned aerial vehicle wing rotating mechanism according to claim 1, wherein the shell comprises a shell body and a mounting plate, a plurality of mounting grooves are distributed on the periphery of the shell body, the top ends of the mounting grooves extend out of the top ends of the shell body, at least one second connecting hole is formed in the bottom ends of the mounting grooves, a plurality of third connecting holes are distributed on the periphery of the plate surface of the mounting plate, and the second connecting holes are used for being connected with the third connecting holes.
7. An integrated unmanned aerial vehicle, comprising:
an integrated unmanned aerial vehicle wing rotation mechanism according to any one of claims 1 to 6;
a wing;
the top of fuselage is equipped with the opening, and the casing sets up in the opening, the top of swivelling joint spare runs through the opening, and with the wing is connected.
8. The integrated unmanned aerial vehicle of claim 7, wherein the fuselage comprises a fuselage skin, a fuselage front connection frame, and a fuselage rear connection frame, the fuselage skin being connected to the fuselage front connection frame and the fuselage rear connection frame, the bottom end of the housing being connected to the tops of the fuselage front connection frame and the fuselage rear connection frame.
9. The integrated unmanned aerial vehicle of claim 7, wherein the wing comprises a wing skin, a wing front beam, a wing rear beam, and a wing flange, the wing skin being coupled to the wing front beam and the wing rear beam, the wing flange being coupled to the bottom of the wing front beam and the wing rear beam, the wing flange being coupled to the top end of the rotational coupling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311538433.8A CN117566134A (en) | 2023-11-17 | 2023-11-17 | Integrated unmanned aerial vehicle wing rotating mechanism and integrated unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311538433.8A CN117566134A (en) | 2023-11-17 | 2023-11-17 | Integrated unmanned aerial vehicle wing rotating mechanism and integrated unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117566134A true CN117566134A (en) | 2024-02-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311538433.8A Pending CN117566134A (en) | 2023-11-17 | 2023-11-17 | Integrated unmanned aerial vehicle wing rotating mechanism and integrated unmanned aerial vehicle |
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| Country | Link |
|---|---|
| CN (1) | CN117566134A (en) |
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2023
- 2023-11-17 CN CN202311538433.8A patent/CN117566134A/en active Pending
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