CN213800179U - Periodic variable-pitch rotor wing set device - Google Patents
Periodic variable-pitch rotor wing set device Download PDFInfo
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- CN213800179U CN213800179U CN202022646854.0U CN202022646854U CN213800179U CN 213800179 U CN213800179 U CN 213800179U CN 202022646854 U CN202022646854 U CN 202022646854U CN 213800179 U CN213800179 U CN 213800179U
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Abstract
The utility model relates to an unmanned aerial vehicle equipment technical field specifically is a periodic variable pitch rotor group device, include: the rotor is arranged on a driving mechanism of the unmanned aerial vehicle, a slot is formed in the upper end of the rotor, and the mounting block is movably mounted in the slot; the mounting block is hinged and movably mounted in a slot arranged at the upper end of the rotor through a hinge shaft; wing assemblies are arranged on two sides of the mounting block; when the unmanned aerial vehicle provided with the periodic variable-pitch rotor group device operates, the blade tip path plane of the wing assembly can be changed only by adjusting the driving torque of the driving mechanism, and the thrust loss is kept perpendicular to the tip road surface flat diameter and can point; through the cyclic variable-pitch rotor group device with the special structural design, the unmanned aerial vehicle can swing back and forth when keeping the body suspended.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle equipment technical field specifically is a periodic variable pitch rotor group device.
Background
An unmanned helicopter is a vertical take-off and landing (VTOL) unmanned aerial vehicle flying by radio ground remote control or autonomous control, belonging to a rotary wing vehicle in the structural form and a vertical take-off and landing vehicle in the function. In recent decades, along with the research progress of composite materials, power systems, sensors, especially flight control and other technologies, unmanned helicopters have been rapidly developed and are becoming the focus of people's attention.
When the unmanned helicopter in the prior art passes through a space track, the whole unmanned helicopter body cannot keep a perfect level due to unreasonable design of a propeller structure; in addition, the unmanned helicopter in the prior art cannot swing back and forth when the body is kept suspended, so that the unmanned helicopter is suitable for the shooting angle position of a camera mounted on the unmanned helicopter.
To the problem in the above-mentioned background art, the utility model aims at providing a periodic displacement rotor organizes device.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a periodic displacement rotor group device to solve the problem that proposes among the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
a cyclic pitch rotor-set apparatus, comprising: the rotor is arranged on a driving mechanism of the unmanned aerial vehicle, a slot is formed in the upper end of the rotor, and the mounting block is movably mounted in the slot; the mounting block is hinged and movably mounted in a slot arranged at the upper end of the rotor through a hinge shaft; wing assemblies are arranged on two sides of the mounting block.
As a further aspect of the present invention: the wing assembly comprises a mounting frame and blades, the mounting frame is in a U-shaped shape, the mounting frame is movably mounted on the mounting block through a shaft bolt, and the blades are movably mounted on one side of the mounting frame through the mounting shaft; the blades are made of carbon fiber materials.
As a further aspect of the present invention: the number of the mounting frames is two, namely a first mounting frame and a second mounting frame, and the number of the blades is two, namely a first blade and a second blade; the number of the mounting shafts is two, namely a first mounting shaft and a third mounting shaft; the number of the shaft bolts is two, namely a first shaft bolt and a second shaft bolt; the first mounting frame is movably mounted on the left side of the mounting block through a first shaft bolt, and the first blade is movably mounted on one side of the first mounting frame through a first mounting shaft; the second mounting frame is movably mounted on the mounting block through a second shaft bolt, and the second blade is movably mounted on one side of the second mounting frame through a third mounting shaft.
As a further aspect of the present invention: gaps exist at the position where the first blade is connected with the first mounting frame, the position where the first mounting frame is connected with the mounting block, the position where the mounting block is connected with the second mounting frame and the position where the second mounting frame is connected with the second blade; and the first blade, the first mounting frame, the mounting block, the second mounting frame and the second blade are oblique lines on the same plane.
Compared with the prior art, the beneficial effects of the utility model are that:
when the unmanned aerial vehicle provided with the periodic variable-pitch rotor group device operates, the blade tip path plane of the wing assembly can be changed only by adjusting the driving torque of the driving mechanism, and the thrust loss is kept perpendicular to the tip road surface flat diameter and can point; through the cyclic variable-pitch rotor group device with the special structural design, the unmanned aerial vehicle can swing back and forth when keeping the body suspended.
Drawings
In order to illustrate the technical solutions in the embodiments of the present invention more clearly, the drawings that are needed in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention.
Fig. 1 is a schematic structural diagram of a cyclic variable-pitch rotor group device according to an embodiment of the present invention.
In the figure: 1-a first blade, 2-a first mounting frame, 3-a first mounting shaft, 4-a first shaft bolt, 5-a mounting block, 6-a hinge shaft, 7-a rotor, 8-a second mounting frame, 9-a third mounting shaft, 10-a second blade and 11-a second shaft bolt.
Detailed Description
In order to make the technical problem, technical solution and advantageous effects to be solved by the present invention more clearly understood, the following description is given in conjunction with the accompanying drawings and embodiments to illustrate the present invention in further detail. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Examples
Referring to fig. 1, in an embodiment of the present invention, a cyclic variable-pitch rotor assembly device includes: the rotor 7 and the mounting block 5, the rotor 7 is arranged on a driving mechanism of the unmanned aerial vehicle, the driving mechanism is the prior art, and is not further explained here; the upper end of the rotor 7 is provided with a slot, and the inside of the slot is movably provided with an installation block 5; the mounting block 5 is hinged and movably mounted in a slot arranged at the upper end of the rotor 7 through a hinge shaft 6; wing components are arranged on two sides of the mounting block 5;
further, the wing assembly comprises a mounting frame and a blade, the mounting frame is in a U-shaped shape, the mounting frame is movably mounted on the mounting block 5 through a shaft bolt, and the blade is movably mounted on one side of the mounting frame through a mounting shaft; the blades are made of carbon fiber materials;
specifically, the number of the mounting brackets is two, namely a first mounting bracket 2 and a second mounting bracket 8, and the number of the blades is two, namely a first blade 1 and a second blade 10; the number of the mounting shafts is two, namely a first mounting shaft 3 and a third mounting shaft 9; the number of the shaft bolts is two, namely a first shaft bolt 4 and a second shaft bolt 11; the first mounting frame 2 is movably mounted on the left side of the mounting block 5 through a first shaft bolt 4, and the first blade 1 is movably mounted on one side of the first mounting frame 2 through a first mounting shaft 3; the second mounting frame 8 is movably mounted on the mounting block 5 through a second shaft bolt 11, and the second blade 10 is movably mounted on one side of the second mounting frame 8 through a third mounting shaft 9;
furthermore, gaps exist at the position where the first blade 1 is connected with the first mounting frame 2, the position where the first mounting frame 2 is connected with the mounting block 5, the position where the mounting block 5 is connected with the second mounting frame 8 and the position where the second mounting frame 8 is connected with the second blade 10; and the first blade 1, the first mounting frame 2, the mounting block 5, the second mounting frame 8 and the second blade 10 are inclined on the same plane.
The embodiment of the utility model provides a theory of operation is:
when the unmanned aerial vehicle provided with the periodic variable-pitch rotor group device operates, the blade tip path plane of the wing assembly can be changed only by adjusting the driving torque of the driving mechanism, and the thrust loss is kept perpendicular to the tip road surface flat diameter and can point; in different directions, the rotor 7 only needs one control input main driver, the mounting block 5 is passively shaken, the wing assembly movably mounted on the mounting block 5 passively swings up and down, the inclined hysteresis mounting block 5 is kinematically coupled with hysteresis motion excited by the driver, a motor of the energy supply mechanism enters periodic clearance pitch change, the pitch of blades of the wing assembly changes along with the change of the pitch, the coherent flapping response is pneumatically driven, and then lateral force is generated, so that the unmanned aerial vehicle can pass through a space track and keep perfect level; the periodically-variable-pitch rotor group device designed by the special structure enables the unmanned aerial vehicle to keep swinging back and forth when the body of the unmanned aerial vehicle hovers.
In the description of the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (4)
1. A cyclic pitch rotor-set apparatus, comprising: a rotor (7) and a mounting block (5); the method is characterized in that: the rotor (7) is arranged on a driving mechanism of the unmanned aerial vehicle; the upper end of the rotor (7) is provided with a slot, and the inside of the slot is movably provided with an installation block (5); the mounting block (5) is hinged and movably mounted in a slot arranged at the upper end of the rotor (7) through a hinge shaft (6); wing components are arranged on two sides of the mounting block (5).
2. The cyclic pitch rotor assembly apparatus of claim 1, wherein: the wing assembly comprises a mounting frame and blades, the mounting frame is in a U-shaped shape, the mounting frame is movably mounted on the mounting block (5) through a shaft bolt, and the blades are movably mounted on one side of the mounting frame through mounting shafts.
3. The cyclic pitch rotor assembly apparatus of claim 2, wherein: the number of the mounting frames is two, and the mounting frames are respectively a first mounting frame (2) and a second mounting frame (8); the number of the blades is two, namely a first blade (1) and a second blade (10); the number of the mounting shafts is two, namely a first mounting shaft (3) and a third mounting shaft (9); the number of the shaft bolts is two, namely a first shaft bolt (4) and a second shaft bolt (11); the first mounting frame (2) is movably mounted on the left side of the mounting block (5) through a first shaft bolt (4), and the first blade (1) is movably mounted on one side of the first mounting frame (2) through a first mounting shaft (3); the second mounting frame (8) is movably mounted on the mounting block (5) through a second shaft bolt (11), and the second blade (10) is movably mounted on one side of the second mounting frame (8) through a third mounting shaft (9).
4. The cyclic pitch rotor assembly apparatus of claim 3, wherein: gaps exist at the position where the first blade (1) is connected with the first mounting frame (2), the position where the first mounting frame (2) is connected with the mounting block (5), the position where the mounting block (5) is connected with the second mounting frame (8) and the position where the second mounting frame (8) is connected with the second blade (10); and the first blade (1), the first mounting frame (2), the mounting block (5), the second mounting frame (8) and the second blade (10) are oblique lines on the same plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022646854.0U CN213800179U (en) | 2020-11-16 | 2020-11-16 | Periodic variable-pitch rotor wing set device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022646854.0U CN213800179U (en) | 2020-11-16 | 2020-11-16 | Periodic variable-pitch rotor wing set device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213800179U true CN213800179U (en) | 2021-07-27 |
Family
ID=76933797
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022646854.0U Active CN213800179U (en) | 2020-11-16 | 2020-11-16 | Periodic variable-pitch rotor wing set device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213800179U (en) |
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2020
- 2020-11-16 CN CN202022646854.0U patent/CN213800179U/en active Active
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