CN220332979U - Can adjust centrobaric unmanned aerial vehicle support - Google Patents
Can adjust centrobaric unmanned aerial vehicle support Download PDFInfo
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- CN220332979U CN220332979U CN202321191658.6U CN202321191658U CN220332979U CN 220332979 U CN220332979 U CN 220332979U CN 202321191658 U CN202321191658 U CN 202321191658U CN 220332979 U CN220332979 U CN 220332979U
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- 238000012986 modification Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
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Abstract
The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle bracket capable of adjusting the gravity center, which comprises a main body bracket, wherein a bearing plate is arranged in the main body bracket, an angle sensor is fixed at the upper end of the bearing plate, a balancing weight is arranged at the lower end of the balancing weight, a gravity center adjusting part is assembled at the lower end of the bearing plate, and the gravity center adjusting part is connected with the balancing weight, wherein the angle sensor can monitor the inclination of the main body bracket and drive the gravity center adjusting part to adjust the position of the balancing weight. According to the utility model, when the unmanned aerial vehicle lands on the inclined ground, the first driving element and the second driving element are started according to the inclined angle, the direction of the guide rod and the position of the balancing weight are adjusted through the cooperation of the first driving element and the second driving element, the gravity center of the unmanned aerial vehicle in an inclined state is adjusted through the balancing weight, and the probability that the unmanned aerial vehicle lands unstably and turns on one's side when landing on the inclined ground is reduced.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle bracket capable of adjusting the gravity center.
Background
Unmanned aerial vehicles, abbreviated as "unmanned aerial vehicles" (UAVs), are unmanned aerial vehicles that are operated using a radio remote control device and a self-contained programmed control device. With the development of unmanned aerial vehicle technology, unmanned aerial vehicles have been widely used in a plurality of fields such as geological survey, traffic cruising, agricultural planting, military reconnaissance, aerospace photography, entertainment and leisure.
When unmanned aerial vehicle carries out outdoor operation and finishes landing, because the uncontrollable characteristic of geographical environment, the ground when it lands probably has the condition of slope, can lead to unmanned aerial vehicle focus slope when unmanned aerial vehicle drops in the ground of slope, when the slope exceeds certain angle, can cause unmanned aerial vehicle to land unstable, topple over, circumstances such as turn on one's side, even cause unmanned aerial vehicle damage's condition, it is through the mode of diminishing the air inlet like a many rotor unmanned aerial vehicle undercarriage that publication number is CN214824078U disclosed, reduce the recovery speed of spring, directly take place to strike with ground hard landing when reaching unmanned aerial vehicle landing easily, cause unmanned aerial vehicle to take place to topple over or damage and influence the problem of subsequent use easily, but, it can't solve the unmanned aerial vehicle that leads to because ground slope takes place the focus slope, cause unmanned aerial vehicle to topple over, turn on one's side, even the problem of damaging, based on above-mentioned problem, this application document has proposed an unmanned aerial vehicle support that can adjust focus in order to solve the problem of focus slope when unmanned aerial vehicle that leads to land because of ground slope.
Disclosure of Invention
The utility model aims to provide an unmanned aerial vehicle bracket capable of adjusting the gravity center, when an unmanned aerial vehicle lands on an inclined ground, a first driving element and a second driving element are started according to the inclined angle, the direction of a guide rod and the position of a balancing weight are adjusted through the cooperation of the first driving element and the second driving element, the gravity center of the unmanned aerial vehicle in an inclined state is adjusted through the balancing weight, and the probability of unstable landing and rollover of the unmanned aerial vehicle when the unmanned aerial vehicle lands on the inclined ground is reduced.
The technical scheme adopted by the utility model is as follows:
the utility model provides an unmanned aerial vehicle support that can adjust centrobaric, includes the main part support, the inside of main part support is provided with the loading board, the upper end of loading board is fixed with angle sensor, the lower extreme of main part support is provided with the balancing weight, the lower extreme of loading board is equipped with focus adjustment portion, just focus adjustment portion is connected with the balancing weight, wherein, angle sensor can monitor the gradient of main part support and drive focus adjustment portion adjustment balancing weight's position.
Further, the focus adjustment part includes first actuating element, U-shaped board, second actuating element, axostylus axostyle, guide bar and transmission bush and, first actuating element is fixed in the upper end of loading board, the U-shaped board is fixed in the output of loading board, second actuating element is fixed in the one end of U-shaped board, the axostylus axostyle is fixed in the output of second actuating element, just axostylus axostyle and U-shaped board rotate to be connected, the guide bar is fixed in the other end of U-shaped board, just the one end and the axostylus axostyle rotation connection of U-shaped board are kept away from to the guide bar, transmission bush threaded connection is in the outside of axostylus axostyle, be sliding connection between transmission bush and guide bar and balancing weight and the guide bar, balancing weight and transmission bush fixed connection.
Further, the four end corners of the bottom of the main body support are all fixed with the supporting legs, a plurality of supporting legs are annularly distributed at the lower end of the main body support, and the distance between two supporting legs positioned at opposite angles is larger than the rotating diameter of the guide rod.
Further, the outside of guide bar has offered the direction and has led to the groove, the outside of transmission bush is fixed with the guide pin pole, guide pin pole sliding connection is in the inside of leading to the groove, guide bar and transmission bush pass through guide pin pole and direction and lead to groove sliding connection.
Further, the sum of the weights of the weight block, the shaft rod, the guide rod and the transmission bushing is equal to the weight of the second driving element.
Further, the balancing weight is spherical or elliptic in shape.
The utility model has the technical effects that:
according to the utility model, when the unmanned aerial vehicle lands on the inclined ground, the first driving element and the second driving element are started according to the inclined angle, the direction of the guide rod and the position of the balancing weight are adjusted through the cooperation of the first driving element and the second driving element, the gravity center of the unmanned aerial vehicle in an inclined state is adjusted through the balancing weight, and the probability that the unmanned aerial vehicle lands unstably and turns on one's side when landing on the inclined ground is reduced.
According to the utility model, the inclination angle of the unmanned aerial vehicle in the landing state is monitored through the angle sensor, and the moving direction and the moving distance of the balancing weight are calculated through the matched program, so that the position of the balancing weight can be automatically adjusted, and further, the gravity center of the unmanned aerial vehicle landed on the inclined ground is adjusted, and manual intervention is not needed, so that the device is convenient to use.
Drawings
FIG. 1 is a schematic view of the overall structure of the present utility model;
FIG. 2 is a bottom view of the overall structure of the present utility model;
FIG. 3 is an enlarged view of a portion of the utility model at A in FIG. 2;
FIG. 4 is a schematic view of the gravity center adjusting portion according to the present utility model;
FIG. 5 is a cross-sectional view of the center of gravity adjusting portion of the present utility model;
fig. 6 is an exploded view of the structure of the center of gravity adjusting portion in the present utility model.
In the drawings, the list of components represented by the various numbers is as follows:
10. a main body bracket; 11. a carrying plate; 12. an angle sensor; 13. balancing weight; 14. a support leg; 20. a center of gravity adjusting section; 21. a first driving element; 22. a U-shaped plate; 23. a second driving element; 24. a shaft lever; 25. a guide rod; 26. and a transmission bushing.
Detailed Description
The present utility model will be specifically described with reference to examples below in order to make the objects and advantages of the present utility model more apparent. It should be understood that the following text is intended to describe only one or more specific embodiments of the utility model and does not limit the scope of the utility model strictly as claimed.
As shown in fig. 1 to 3, an unmanned aerial vehicle support capable of adjusting the center of gravity is applied to an unmanned aerial vehicle and comprises a main body support 10, a bearing plate 11 is arranged in the main body support 10, an angle sensor 12 is fixed at the upper end of the bearing plate 11, a balancing weight 13 is arranged at the lower end of the main body support 10, a center of gravity adjusting part 20 is arranged at the lower end of the bearing plate 11, the center of gravity adjusting part 20 is connected with the balancing weight 13, and the angle sensor 12 can monitor the inclination of the main body support 10 and drive the center of gravity adjusting part 20 to adjust the position of the balancing weight 13.
Here, unmanned aerial vehicle's inside is provided with data transmission module, and a remote control unit in addition with unmanned aerial vehicle supporting use, and loading board 11 and unmanned aerial vehicle pass through wire electric connection, and remote control unit and loading board 11 can carry out data transmission through unmanned aerial vehicle.
Specifically, in order to better describe the working process of the device, when the unmanned aerial vehicle is in a horizontal state, a coordinate system is established by the center of the unmanned aerial vehicle, the direction in which the length of the unmanned aerial vehicle is located is marked as an X axis, the direction in which the width of the unmanned aerial vehicle is located is marked as a Y axis, the direction in which the height of the unmanned aerial vehicle is located is marked as a Z axis, the length of the unmanned aerial vehicle is marked as a +X axis at one end of the center, the length of the unmanned aerial vehicle is marked as a-X axis at the other end of the center of the unmanned aerial vehicle, the width of the unmanned aerial vehicle is marked as a-Y axis at the other end of the center of the unmanned aerial vehicle, the height of the unmanned aerial vehicle is marked as a +Z axis at the upper end of the unmanned aerial vehicle, the horizontal plane in which the unmanned aerial vehicle is located is divided into four areas by the X axis and the Y axis, the area between the +X axis and the +Y axis is marked as a first quadrant, the area between the-X axis and the +Y axis is marked as a second quadrant, the area between the-X axis and the +Y axis is marked as a-Y axis, the width of the unmanned aerial vehicle is marked as a-Y axis, the height is marked as a-Z axis at the +Z axis, the area between the +X axis and the +Y axis is in the quadrant, and the quadrant area between the first quadrant area and the +X axis and the initial area and the quadrant area and the initial area and the quadrant area and the position in the quadrant 13;
it should be noted that, a control program is also used with the unmanned aerial vehicle, an inclination threshold is set in the control program, in this embodiment, the inclination threshold is set to 15 °, when the unmanned aerial vehicle is in a landing state, and after the inclination angle of the unmanned aerial vehicle exceeds the inclination threshold, the control program can start the gravity center adjusting part 20 to adjust the position of the balancing weight 13, and adjust the position of the balancing weight 13 according to the inclination direction and the angle of the unmanned aerial vehicle, where, because the forms of the unmanned aerial vehicle are different, the sizes are different, the specific relationship between the inclination direction of the unmanned aerial vehicle and the moving distance of the balancing weight 13 and the moving direction of the balancing weight 13 can be obtained through multiple training, and also can be obtained through corresponding software or/and simulation analysis without specific limitation.
In a preferred embodiment, as shown in fig. 4 to 6, the gravity center adjusting portion 20 includes a first driving element 21, a U-shaped plate 22, a second driving element 23, a shaft lever 24, a guide rod 25, and a transmission bush 26, wherein the first driving element 21 is fixed at an upper end of the bearing plate 11, an output end of the first driving element 21 penetrates through the bearing plate 11 and extends to a lower end of the bearing plate 11, the U-shaped plate 22 is fixed at an output end of the bearing plate 11, the second driving element 23 is fixed at one end of the U-shaped plate 22, the shaft lever 24 is fixed at an output end of the second driving element 23, the shaft lever 24 and the U-shaped plate 22 are rotatably connected through a ball bearing, the shaft lever 24 penetrates through the U-shaped plate 22 and extends to the other end of the U-shaped plate 22, an external thread is provided at an end of the shaft lever 24 away from the U-shaped plate 22, the guide rod 25 is fixed at the other end of the U-shaped plate 22, and the end of the guide rod 25 away from the U-shaped plate 22 and the shaft lever 24 are rotatably connected through a ball bearing, the transmission bush 26 is threadedly connected to an external side of the shaft lever 24, and the weight 13 and the guide rod 25 are fixedly connected with the transmission bush 26.
In a preferred embodiment, the first driving element 21 and the unmanned aerial vehicle, and the second driving element 23 and the unmanned aerial vehicle are electrically connected through wires.
The counterweight 13 and the guide bar 25 are slidingly connected in a clearance fit.
In a preferred scheme, the four end angles at the bottom of the main body support 10 are all fixed with the supporting legs 14, and a plurality of supporting legs 14 are annularly distributed at the lower end of the main body support 10, and the distance between two supporting legs 14 positioned at opposite angles is larger than the rotation diameter of the guide rod 25.
In a preferred scheme, the outside of guide bar 25 has seted up the direction and has led to the groove, and the outside of drive bush 26 is fixed with the guide pin pole, and guide pin pole sliding connection leads to the inside in groove in the direction, and guide bar 25 and drive bush 26 pass through guide pin pole and direction and lead to groove sliding connection, through the setting of above-mentioned scheme for when axostylus axostyle 24 drive guide bar 25 and balancing weight 13 remove, avoid guide bar 25 to follow axostylus axostyle 24 and take place to rotate.
In a preferred embodiment, the sum of the weights of the weight block 13, the shaft lever 24, the guide rod 25 and the transmission bush 26 is equal to the weight of the second driving element 23, and when the unmanned aerial vehicle performs the flying operation, the weight block 13 is moved to the position closest to the U-shaped plate 22, so that the weight imbalance of the gravity center adjusting portion 20 can be avoided, and the balance of the unmanned aerial vehicle is affected.
In a preferred scheme, the shape of the balancing weight 13 is spherical or elliptical, and through the scheme, the wind resistance of the unmanned aerial vehicle in the flight process can be reduced.
In the present embodiment, since the through hole is formed in the counterweight 13, the polishing process is performed to avoid the occurrence of an acute angle at the two ends of the through hole, and the shape of the counterweight 13 is not particularly limited.
The working principle of the utility model is as follows:
when unmanned aerial vehicle lands, can monitor unmanned aerial vehicle's inclination through angle sensor 12, after inclination exceeds the inclination threshold value, start first actuating element 21, drive U-shaped board 22 through first actuating element 21 and rotate, through U-shaped board 22 and the fixed connection of second actuating element 23, the rotation of U-shaped board 22 and axostylus axostyle 24 is connected and the fixed connection of U-shaped board 22 and guide bar 25, make U-shaped board 22 drive second actuating element 23, axostylus axostyle 24 and guide bar 25 rotate, sliding connection through guide bar 25 and balancing weight 13, make guide bar 25 drive balancing weight 13 rotate, make balancing weight 13 remove to unmanned aerial vehicle's inclination's high point department, start second actuating element 23, through the fixed connection of second actuating element 23 and axostylus axostyle 24, make second actuating element 23 drive axostylus axostyle 24 rotate, threaded connection through axostyle 24 and transmission bush 26, make transmission bush 26 drive balancing weight 13 remove in unmanned aerial vehicle's inclination, and then, through balancing weight 13 adjusts the device, the focus, even avoid the situation of toppling over to take place, the device is caused by tilting, and the like.
In a specific embodiment, when the unmanned aerial vehicle lands, the unmanned aerial vehicle is inclined due to the non-horizontal state of the landing site, the inclination angle of the unmanned aerial vehicle detected by the angle sensor 12 is 13 degrees of the +X-axis balancing weight and 0 degrees of the +Y-axis, and the device does not operate due to the fact that the inclination angle is smaller than the inclination threshold value.
In another specific embodiment, when the unmanned aerial vehicle lands, due to the non-horizontal state of the landing point, the unmanned aerial vehicle is inclined, the inclination angle of the unmanned aerial vehicle is detected to be 20 degrees by the angle sensor 12, the inclination angle of the unmanned aerial vehicle is greater than the inclination threshold value, the second driving element 23 is started, the shaft lever 24 is driven to rotate by the second driving element 23, the balancing weight 13 is driven to move in the direction away from the U-shaped plate 22 on the +X axis by the shaft lever 24, and the gravity center of the unmanned aerial vehicle is regulated.
In another specific embodiment, when the unmanned aerial vehicle lands, due to the non-horizontal state of the landing point, the unmanned aerial vehicle is inclined, the inclination angle of the unmanned aerial vehicle is detected to be +x-18 degrees by the angle sensor 12, the inclination angle of the unmanned aerial vehicle is greater than the inclination threshold value, +y-0 degrees, the first driving element 21 is started, the U-shaped plate 22 is driven to rotate by the first driving element 21, the balancing weight 13, the shaft lever 24 and the guide rod 25 are driven to rotate by the U-shaped plate 22, the balancing weight 13, the shaft lever 24 and the guide rod 25 are driven to rotate to the-X axis, the second driving element 23 is started, the shaft lever 24 is driven to rotate by the second driving element 23, the balancing weight 13 is driven to move in the direction away from the U-shaped plate 22 on the-X axis by the shaft lever 24, and the gravity center of the unmanned aerial vehicle is regulated.
In another specific embodiment, when the unmanned aerial vehicle lands, due to the non-horizontal state of the landing point, the unmanned aerial vehicle is inclined, the inclination angle of the unmanned aerial vehicle is +x axis +18 degrees, +y axis +20 degrees of the gravity center adjusting part is detected by the angle sensor 12, the inclination angle of the unmanned aerial vehicle is larger than the inclination threshold value, the first driving element 21 is started, the U-shaped plate 22 is driven to rotate by the first driving element 21, the balancing weight 13, the shaft lever 24 and the guide rod 25 are driven to rotate by the U-shaped plate 22, the balancing weight 13, the shaft lever 24 and the guide rod 25 are enabled to rotate into the first quadrant, the second driving element 23 is started, the shaft lever 24 is driven to rotate by the second driving element 23, the balancing weight 13 is driven to move in the direction away from the U-shaped plate 22 in the first quadrant by the shaft lever 24, and the gravity center of the unmanned aerial vehicle is adjusted.
The foregoing is merely a preferred embodiment of the present utility model and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present utility model, which are intended to be comprehended within the scope of the present utility model. Structures, devices and methods of operation not specifically described and illustrated herein, unless otherwise indicated and limited, are implemented according to conventional means in the art.
Claims (6)
1. Can adjust focus's unmanned aerial vehicle support is applied to unmanned aerial vehicle, its characterized in that: including main part support (10), the inside of main part support (10) is provided with loading board (11), the upper end of loading board (11) is fixed with angle sensor (12), the lower extreme of main part support (10) is provided with balancing weight (13), the lower extreme of loading board (11) is equipped with focus adjustment portion (20), just focus adjustment portion (20) are connected with balancing weight (13), wherein, angle sensor (12) can monitor the gradient of main part support (10) and drive the position of focus adjustment portion (20) adjustment balancing weight (13).
2. The unmanned aerial vehicle support capable of adjusting the center of gravity according to claim 1, wherein: the gravity center adjusting part (20) comprises a first driving element (21), a U-shaped plate (22), a second driving element (23), a shaft rod (24), a guide rod (25) and a transmission bushing (26), wherein the first driving element (21) is fixed at the upper end of the bearing plate (11), the U-shaped plate (22) is fixed at the output end of the bearing plate (11), the second driving element (23) is fixed at one end of the U-shaped plate (22), the shaft rod (24) is fixed at the output end of the second driving element (23), the shaft rod (24) is connected with the U-shaped plate (22) in a rotating mode, the guide rod (25) is fixed at the other end of the U-shaped plate (22), the guide rod (25) is far away from one end of the U-shaped plate (22) and is connected with the shaft rod (24) in a rotating mode, the transmission bushing (26) is connected with the outer side of the shaft rod (24) in a threaded mode, sliding connection is achieved between the transmission bushing (26) and the guide rod (25) and the balancing weight (13) and the guide rod (25), and the transmission bushing (26) are fixedly connected with the transmission bushing (26).
3. The unmanned aerial vehicle support capable of adjusting the center of gravity according to claim 2, wherein: the four end corners of the bottom of the main body support (10) are respectively fixed with a supporting leg (14), a plurality of supporting legs (14) are annularly distributed at the lower end of the main body support (10), and the distance between two supporting legs (14) positioned at opposite angles is larger than the rotation diameter of the guide rod (25).
4. The unmanned aerial vehicle support capable of adjusting the center of gravity according to claim 2, wherein: the outside of guide bar (25) has offered the direction and has led to the groove, the outside of transmission bush (26) is fixed with the guide pin pole, guide pin pole sliding connection is in the inside of leading to the groove, guide bar (25) and transmission bush (26) are through guide pin pole and direction logical groove sliding connection.
5. The unmanned aerial vehicle support capable of adjusting the center of gravity according to claim 2, wherein: the sum of the weights of the balancing weight (13), the shaft (24), the guide rod (25) and the transmission bushing (26) is equal to the weight of the second driving element (23).
6. The unmanned aerial vehicle support capable of adjusting the center of gravity according to claim 1, wherein: the shape of the balancing weight (13) is spherical or elliptic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321191658.6U CN220332979U (en) | 2023-05-17 | 2023-05-17 | Can adjust centrobaric unmanned aerial vehicle support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321191658.6U CN220332979U (en) | 2023-05-17 | 2023-05-17 | Can adjust centrobaric unmanned aerial vehicle support |
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| Publication Number | Publication Date |
|---|---|
| CN220332979U true CN220332979U (en) | 2024-01-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321191658.6U Active CN220332979U (en) | 2023-05-17 | 2023-05-17 | Can adjust centrobaric unmanned aerial vehicle support |
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| Country | Link |
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| CN (1) | CN220332979U (en) |
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2023
- 2023-05-17 CN CN202321191658.6U patent/CN220332979U/en active Active
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Effective date of registration: 20240326 Address after: No. 28, Xiamai Group, Huayuan Village, Mawan Town, Dushan County, Qiannan Buyi and Miao Autonomous Prefecture, Guizhou Province, 558200 Patentee after: Mo Linhong Country or region after: China Patentee after: Ren Chongyang Patentee after: Wei Zupin Address before: Room 105a, block B, animation building, No.11 Xinghuo Road, Jiangbei new district, Nanjing, Jiangsu 210000 Patentee before: Nanjing gangguo Electronic Technology Co.,Ltd. Country or region before: China |
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Effective date of registration: 20240416 Address after: 710000 Room 1904, Unit 1, Building 1, No. 3, Xijing West Street, Yanta District, Xi'an City, Shaanxi Province Patentee after: Xi'an Yueheng Electromechanical Engineering Co.,Ltd. Country or region after: China Address before: No. 28, Xiamai Group, Huayuan Village, Mawan Town, Dushan County, Qiannan Buyi and Miao Autonomous Prefecture, Guizhou Province, 558200 Patentee before: Mo Linhong Country or region before: China Patentee before: Ren Chongyang Patentee before: Wei Zupin |