CN216003056U - Rotor unmanned aerial vehicle - Google Patents
Rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN216003056U CN216003056U CN202122638418.3U CN202122638418U CN216003056U CN 216003056 U CN216003056 U CN 216003056U CN 202122638418 U CN202122638418 U CN 202122638418U CN 216003056 U CN216003056 U CN 216003056U
- Authority
- CN
- China
- Prior art keywords
- assembly
- plate
- unmanned aerial
- rotor
- aerial vehicle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a rotor unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles and comprises a shell; a first driving component; the rotor wing assembly is connected with the first driving assembly; a second driving component; the wing is connected with the second driving assembly; the control assembly is connected with the first driving assembly and the second driving assembly; the damping subassembly, the damping subassembly is including locating first board, second board and the telescopic link of casing bottom, is equipped with the board three that the telescopic link outside was located to the cover in the board two, locates the spring one in the telescopic link outside through the cover between board one and the board three and connects, and telescopic link one end and board one are connected, the telescopic link other end and two elastic connection of board. To the technical problem that rotor unmanned aerial vehicle easily produces the vibration, the utility model discloses a technological effect lies in that it can effectively reduce the vibration.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field, concretely relates to rotor unmanned aerial vehicle.
Background
Rotor unmanned aerial vehicle is an unmanned helicopter with rotor, and it rotates through every epaxial motor, drives the rotor to produce the thrust that rises, and through the relative speed who changes between the different rotors, change the size of unipolar propulsive force, thereby control rotor unmanned aerial vehicle's flight orbit.
Relevant rotor unmanned aerial vehicle need descend subaerially after the flight finishes, however, can produce the interact force between rotor unmanned aerial vehicle and the ground for rotor unmanned aerial vehicle produces the vibration, thereby produces the damage to rotor unmanned aerial vehicle's spare part, leads to rotor unmanned aerial vehicle's spare part to take place to drop even.
SUMMERY OF THE UTILITY MODEL
1. Technical problem to be solved by the utility model
To the technical problem that rotor unmanned aerial vehicle easily produces the vibration, the utility model provides a rotor unmanned aerial vehicle, it can effectively reduce the vibration.
2. Technical scheme
In order to solve the above problem, the utility model provides a technical scheme does:
a rotorcraft, comprising:
a housing;
a first driving component;
the rotor assembly is connected with the first driving assembly;
a second driving component;
the wing is connected with the second driving assembly;
the control assembly is connected with the first driving assembly and the second driving assembly;
the damping assembly comprises a first plate, a second plate and a telescopic rod, wherein the first plate, the second plate and the telescopic rod are arranged at the bottom of the shell, a third plate is arranged on the outer side of the telescopic rod and is provided with a sleeve, the first plate and the third plate are arranged between the first plate and the second plate through the sleeve, a first spring on the outer side of the telescopic rod is connected, one end of the telescopic rod is connected with the first plate, and the other end of the telescopic rod is elastically connected with the second plate.
Optionally, the vibration damping assembly further comprises a sliding block movably connected in the second plate, one end of the sliding block is hinged to one end, far away from the first plate, of the telescopic rod, and the other end of the sliding block is connected with the second plate through a second spring.
Optionally, the first driving assembly, the second driving assembly and the control assembly are located in the casing, and the rotor assembly and the wing are located outside the casing.
Optionally, the rotor assembly and the housing are connected by an arc-shaped connecting rod.
Optionally, the arc-shaped connecting rod is hollow, and holes one are formed in two sides of the arc-shaped connecting rod.
Optionally, the control assembly includes a controller and a remote controller connected to the controller, and the controller is connected to the first driving assembly and the second driving assembly.
Optionally, the power supply module is further included, and the power supply module is connected with the first driving module, the second driving module and the control module.
Optionally, the first driving assembly comprises a motor connected with the control assembly, and an output shaft of the motor is connected with the rotor assembly.
Optionally, the power module includes a photocell and a storage battery, the photocell is connected to the first driving module, the second driving module and the control module, and the storage battery is connected to the first driving module, the second driving module and the control module.
Optionally, the motor is a brushless motor.
3. Advantageous effects
Adopt the technical scheme provided by the utility model, compare with prior art, have following beneficial effect:
(1) the first spring is used for connecting the first plate and the third plate to reduce the interaction force between the first plate and the third plate, and the first plate is arranged at the bottom of the shell, so that the interaction force between the shell and the third plate is reduced, a certain buffering and vibration damping effect is achieved when the rotor unmanned aerial vehicle is in contact with the ground, and the vibration suffered by the rotor unmanned aerial vehicle is effectively reduced;
(2) the other end of the telescopic rod is elastically connected with the second plate, so that the interaction force between the telescopic rod and the second plate is favorably reduced, the first plate is arranged at the bottom of the shell, and one end of the telescopic rod is connected with the first plate, so that the interaction force between the shell and the second plate is reduced, the unmanned rotor wing aircraft has a certain buffering and vibration damping effect when contacting the ground, and the vibration borne by the unmanned rotor wing aircraft is further effectively reduced;
(3) the arc connecting rod of cavity form is favorable to reducing the quality of arc connecting rod to reduce rotor unmanned aerial vehicle's energy consumption, increase rotor unmanned aerial vehicle's duration.
Drawings
Fig. 1 is a schematic structural view of a rotor unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic structural view of an arc-shaped connecting rod according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a damping assembly according to an embodiment of the present invention;
in the figure: 1. a first driving component; 2. a rotor assembly; 3. a second driving component; 4. an airfoil; 5. a gyroscope sensor; 6. a controller; 7. an arc-shaped connecting rod; 71. a first hole; 72. a convex surface; 73. a concave surface; 8. a housing; 9. a vibration reduction assembly; 91. a first plate; 92. a second plate; 93. a third plate; 94. a telescopic rod; 95. a first spring; 96. a slider; 97. a second spring; 98. and a roller.
Detailed Description
For a further understanding of the present invention, reference will be made to the following detailed description taken in conjunction with the accompanying drawings and examples.
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and are not limiting of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings. The utility model discloses in words such as first, second, be for the description the utility model discloses a technical scheme is convenient and set up, and does not have specific limiting action, is general finger, right the technical scheme of the utility model does not constitute limiting action. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; 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 technical solutions in the same embodiment and between the technical solutions in different embodiments can be arranged and combined to form a new technical solution without contradiction or conflict, which is all within the scope of the present invention.
Example 1
With reference to fig. 1-3, the present embodiment provides a rotorcraft, including:
a housing 8;
a first driving assembly 1;
the rotor assembly 2 is connected with the driving assembly I1;
a second driving assembly 3;
the wing 4 is connected with the second driving assembly 3;
the control assembly is connected with the first driving assembly 1 and the second driving assembly 3;
damping subassembly 9, damping subassembly 9 is including locating first board 91, second board 92 and the telescopic link 94 of casing 8 bottom, is equipped with the third board 93 that the telescopic link 94 outside was located to the cover in the second board 92, connects through the first spring 95 that the telescopic link 94 outside was located to the cover between first board 91 and the third board 93, and telescopic link 94 one end is connected with first board 91, and the other end of telescopic link 94 and second board 92 elastic connection.
Specifically, the first plate 91 is used to connect the housing 8 and the telescoping rod 94; the second plate 92 is used for accommodating the third plate 93, the third plate 93 is used for accommodating the telescopic rod 94, and the third plate 93 is sleeved outside the telescopic rod 94, so that the third plate 93 can limit the telescopic direction of the telescopic rod 94, and the telescopic stability of the telescopic rod 94 is ensured; the first spring 95 is used for connecting the first plate 91 and the third plate 93 to reduce the interaction force between the first plate 91 and the third plate 93, and the first plate 91 is arranged at the bottom of the shell 8, so that the interaction force between the shell 8 and the third plate 93 is reduced, a certain buffering and vibration damping effect is achieved when the rotor unmanned aerial vehicle is in contact with the ground, and vibration borne by the rotor unmanned aerial vehicle is effectively reduced; because the telescopic link 94 other end and two 92 elastic connection of board, be favorable to reducing the interaction force between telescopic link 94 and two 92 boards, because casing 8 bottom is located to board 91, and telescopic link 94 one end and the connection of board 91 to reduce the interaction force between casing 8 and the two 92 boards, have certain buffering damping effect when making rotor unmanned aerial vehicle and ground contact, further effectively reduce the vibration that rotor unmanned aerial vehicle received.
When manual control rotor unmanned aerial vehicle, because control assembly and drive assembly 1 are connected, the opening and close and drive power size of manual remote control operation control assembly control drive assembly 1, thereby control opening and close and the rotational speed size of rotor assembly 2, wherein drive assembly 1 equals and unrestricted with the quantity of rotor assembly 2, can be according to rotor unmanned aerial vehicle's load, it is decided to make or factor such as manufacturing cost are synthesized, and simultaneously, because control assembly and drive assembly two 3 are connected, opening and close of manual remote control operation control assembly control drive assembly two 3, thereby control wing 4 is opened and close, wherein drive assembly two 3 equals and unrestricted with the quantity of wing 4, can be according to rotor unmanned aerial vehicle's load, the factors such as manufacturing or manufacturing cost are synthesized and are considered and decide.
Further, the vibration damping assembly 9 further comprises a sliding block 96 movably connected in the second plate 92, one end of the sliding block 96 is hinged to one end of the telescopic rod 94 far away from the first plate 91, and the other end of the sliding block 96 is connected with the second plate 92 through a second spring 97.
Specifically, the sliding direction of the sliding block 96 is limited through the second plate 92, the sliding stability of the sliding block 96 can be guaranteed, the roller 98 can be installed at the bottom of the sliding block 96, sliding friction is replaced by rolling friction between the sliding block 96 and the second plate 92, friction force is reduced beneficially, the sliding block 96 and the second plate 92 are prevented from being damaged mutually, the sliding block 96 is used for being connected with the telescopic rod 94 and the second spring 97, the second spring 97 is used for being connected with the sliding block 96 and the second plate 92, and certain vibration damping performance is achieved between the sliding block 96 and the second plate 92.
Further, the first driving assembly 1, the second driving assembly 3 and the control assembly are located in the housing 8, and the rotor assembly 2 and the wing 4 are located outside the housing 8.
Specifically, the casing 8 supports the first driving assembly 1, the second driving assembly 3, the control assembly, the rotor assembly 2 and the wing 4 to a certain extent, so that stability of the driving assemblies is guaranteed, meanwhile, the first driving assembly 1, the second driving assembly 3 and the control assembly which are located in the casing 8 are prevented from being damaged by substances such as external dust and moisture, and the rotor assembly 2 and the wing 4 which are located outside the casing 8 are enabled to play a role in flying.
Specifically, the material of the housing 8 is SE9547, and SE9547 not only increases the strength of the housing 8, but also increases the toughness of the housing 8.
Further, the rotor assembly 2 and the housing 8 are connected by an arc-shaped connecting rod 7.
Specifically, arc connecting rod 7 is used for connecting rotor subassembly 2 and casing 8, guarantee rotor subassembly 2's stability, and arc connecting rod 7 is protruding to rotor unmanned aerial vehicle rising direction, it is big to make the concave surface 73 of arc connecting rod 7 and the area of contact of air, thereby make more air to produce lift to arc connecting rod 7, make the air with arc connecting rod 7's convex surface 72 contact disperse to both sides, thereby reduce the resistance of air to arc connecting rod 7, thereby reduce the energy consumption, increase rotor unmanned aerial vehicle's time of endurance.
Further, the arc-shaped connecting rod 7 is hollow, and two sides of the arc-shaped connecting rod 7 are provided with first holes 71.
Specifically, the hollow arc-shaped connecting rod 7 is beneficial to reducing the quality of the arc-shaped connecting rod 7, so that the energy consumption of the rotor wing unmanned aerial vehicle is reduced, and the endurance time of the rotor wing unmanned aerial vehicle is prolonged; the first hole 71 is convenient for air circulation, so that the internal and external pressure difference of the arc-shaped connecting rod 7 is small, and the arc-shaped connecting rod 7 is prevented from being damaged due to the large internal and external pressure difference.
Further, the control assembly comprises a controller 6 and a remote controller connected with the controller 6, and the controller 6 is connected with the first driving assembly 1 and the second driving assembly 3.
Specifically, the remote controller is used for transmitting a control signal to the controller 6, and the controller 6 is used for controlling the opening and closing and the power of the driving assembly I1 and controlling the opening and closing and the power of the driving assembly II 3.
Furthermore, the power supply assembly is connected with the first driving assembly 1, the second driving assembly 3 and the control assembly.
Specifically, the power supply assembly supplies electric energy to the first driving assembly 1, the second driving assembly 3 and the control assembly.
Further, the driving assembly 1 comprises a motor connected with the control assembly, and an output shaft of the motor is connected with the rotor assembly 2.
Specifically, control assembly is used for opening and close and the rotational speed size of control motor, and the output shaft of motor rotates and drives rotor subassembly 2 and rotate to control opening and close and the rotational speed size of rotor subassembly 2.
Furthermore, the power supply assembly comprises a photocell and a storage battery, the photocell is connected with the first driving assembly 1, the second driving assembly 3 and the control assembly, and the storage battery is connected with the first driving assembly 1, the second driving assembly 3 and the control assembly.
Specifically, rotor unmanned aerial vehicle's drive assembly 1, drive assembly two 3 and control assembly can pass through the photocell power supply, can improve rotor unmanned aerial vehicle's time of endurance again through the battery power supply, especially under the condition that has the sunlight, and rotor unmanned aerial vehicle can fly the limit and charge, effectively improves rotor unmanned aerial vehicle's time of endurance.
Further, the motor is a brushless motor.
Specifically, brushless motor not only makes the energy consumption of motor low to increase rotor unmanned aerial vehicle's duration, make the noise of motor low moreover, thereby reduce rotor unmanned aerial vehicle's noise pollution.
When the rotor unmanned aerial vehicle is manually controlled, the control assembly is connected with the first driving assembly 1, the manual remote control operation control assembly controls the opening and closing of the first driving assembly 1 and the driving force, so as to control the opening and closing and the rotating speed of the rotor assembly 2, wherein the first driving assembly 1 and the rotor assembly 2 are equal in number and are not limited, and can be comprehensively considered according to the load of the rotor unmanned aerial vehicle, the processing and manufacturing or the production cost, and other factors, meanwhile, the control assembly is connected with the second driving assembly 3, the manual remote control operation control assembly controls the opening and closing of the second driving assembly 3, so as to control the rotation of the wing 4 by a certain angle, when the flight speed of the rotor unmanned aerial vehicle is higher, the wing 4 is controlled to keep a smaller attack angle, when the flight speed of the rotor unmanned aerial vehicle is lower, the wing 4 is controlled to keep a larger attack angle, so that the wing 4 keeps a proper attack angle at any time, so as to effectively improve the lift force of the rotor unmanned aerial vehicle, thereby offset rotor unmanned aerial vehicle's partial load, increase rotor unmanned aerial vehicle's duration, wherein the quantity of drive assembly two 3 and wing 4 equals and unrestricted, can be according to rotor unmanned aerial vehicle's load, manufacturing or manufacturing cost's such factors comprehensive consideration and decide.
When the automatic control of the rotor unmanned aerial vehicle is required, a gyroscope sensor 5 connected with the control assembly can be installed on the unmanned aerial vehicle, and the gyroscope sensor 5 is used for judging the motion state of the rotor unmanned aerial vehicle and transmitting a state signal to the control assembly; the control assembly controls the opening and closing of the driving assembly 1 and the driving force according to the state signal of the gyroscope sensor 5, and the control assembly is connected with the driving assembly 1, so as to control the opening and closing and the rotating speed of the rotor wing assembly 2, wherein the number of the driving assembly 1 and the number of the rotor wing assembly 2 are equal and are not limited, and can be determined according to the comprehensive consideration of the factors such as the load of the rotor wing unmanned aerial vehicle, the processing and manufacturing or the production cost, and the like, meanwhile, the control assembly controls the opening and closing of the driving assembly 3 due to the connection of the control assembly and the driving assembly II 3, so as to control the rotation of the wing 4 by a certain angle, so that the wing 4 keeps a proper attack angle, so as to effectively improve the lift force of the rotor wing unmanned aerial vehicle, thereby offsetting partial load of the rotor wing unmanned aerial vehicle, so as to increase the endurance time of the rotor wing unmanned aerial vehicle, wherein the number of the driving assembly II 3 and the wing 4 is equal and is not limited, can be decided according to the comprehensive consideration of the factors such as the load, the processing and manufacturing or the production cost of the rotor unmanned aerial vehicle.
The present invention and its embodiments have been described above schematically, and the description is not limited thereto, and what is shown in the drawings is only one of the embodiments of the present invention, and the actual structure is not limited thereto. Therefore, if the person skilled in the art receives the teaching of the present invention, without departing from the inventive spirit of the present invention, the person skilled in the art should also design the similar structural modes and embodiments without creativity to the technical solution, and all shall fall within the protection scope of the present invention.
Claims (10)
1. A rotorcraft, comprising:
a housing;
a first driving component;
the rotor assembly is connected with the first driving assembly;
a second driving component;
the wing is connected with the second driving assembly;
the control assembly is connected with the first driving assembly and the second driving assembly;
the damping assembly comprises a first plate, a second plate and a telescopic rod, wherein the first plate, the second plate and the telescopic rod are arranged at the bottom of the shell, a third plate is arranged on the outer side of the telescopic rod and is provided with a sleeve, the first plate and the third plate are arranged between the first plate and the second plate through the sleeve, a first spring on the outer side of the telescopic rod is connected, one end of the telescopic rod is connected with the first plate, and the other end of the telescopic rod is elastically connected with the second plate.
2. A rotary wing drone according to claim 1, wherein the damping assembly further comprises a slider movably connected within the second plate, one end of the slider being hinged to the end of the telescopic rod remote from the first plate, the other end of the slider being connected to the second plate via a second spring.
3. A rotary-wing drone according to claim 1, wherein the first drive assembly, the second drive assembly and the control assembly are located within the housing, and the rotor assembly and the wing are located outside the housing.
4. A rotary-wing drone according to claim 1, wherein the rotor assembly and the housing are connected by an arcuate connecting rod.
5. A rotary-wing unmanned aerial vehicle according to claim 4, wherein the curved connecting rod is hollow and has a first hole on each side.
6. A rotary-wing drone according to any one of claims 1 to 5, wherein the control assembly includes a controller and a remote control connected to the controller, the controller being connected to both the first and second drive assemblies.
7. A rotary-wing drone according to any one of claims 1 to 5, further comprising a power supply assembly, the power supply assembly being connected to the first drive assembly, the second drive assembly and the control assembly.
8. A rotary-wing drone according to any one of claims 1 to 5, characterised in that the drive assembly includes a motor connected to the control assembly, the output shaft of the motor being connected to the rotor assembly.
9. A rotary-wing drone according to claim 7, wherein the power supply assembly includes a photovoltaic cell and a battery, the photovoltaic cell being connected to the first drive assembly, the second drive assembly and the control assembly, the battery being connected to the first drive assembly, the second drive assembly and the control assembly.
10. A rotary-wing drone according to claim 8, wherein the motor is a brushless motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122638418.3U CN216003056U (en) | 2021-10-28 | 2021-10-28 | Rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122638418.3U CN216003056U (en) | 2021-10-28 | 2021-10-28 | Rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216003056U true CN216003056U (en) | 2022-03-11 |
Family
ID=80526759
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122638418.3U Active CN216003056U (en) | 2021-10-28 | 2021-10-28 | Rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216003056U (en) |
-
2021
- 2021-10-28 CN CN202122638418.3U patent/CN216003056U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8070090B2 (en) | Stop-rotor rotary wing aircraft | |
| CN105775120B (en) | A kind of multi-rotor unmanned aerial vehicle | |
| CN204223181U (en) | A kind of combined type vertically taking off and landing flyer | |
| CN210391552U (en) | Vertical take-off and landing fixed wing unmanned aerial vehicle | |
| CN108438215A (en) | It is a kind of to have the vector four-axle aircraft for keeping organism level ability | |
| CN105905291A (en) | Multi-rotor craft with tilting rotors | |
| CN205524969U (en) | Unmanned aerial vehicle with multiple rotor wings | |
| CN109229352A (en) | A kind of more rotor manned aircraft | |
| CN216003056U (en) | Rotor unmanned aerial vehicle | |
| CN100389048C (en) | Articulated type double-rotor flying robot | |
| CN110816827B (en) | Bionic butterfly flapping-wing aircraft | |
| CN208963310U (en) | It is a kind of can VTOL vert the fixed-wing unmanned plane of quadrotor | |
| CN218537100U (en) | Single power driven unmanned aerial vehicle that verts | |
| CN110712748A (en) | Novel eight-rotor aircraft | |
| CN205668640U (en) | Tilting rotor multi-rotor aerocraft | |
| CN201086823Y (en) | Rank double-oar minitype helicopter | |
| CN115367106A (en) | Tilt rotor unmanned aerial vehicle | |
| CN209581874U (en) | A kind of vertical take-off and landing drone | |
| CN208198817U (en) | A kind of twin-engined quadrotor drones | |
| CN208931639U (en) | A kind of novel culvert type vertical take-off and landing drone | |
| CN112644701A (en) | Transverse double-rotor unmanned aerial vehicle | |
| CN112340022A (en) | Double rotor unmanned plane | |
| CN109250095A (en) | A kind of VTOL fixed wing aircraft | |
| CN214190096U (en) | Many rotor crafts horn structure | |
| CN213800167U (en) | Unmanned helicopter of no swash plate formula |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |