CN218703871U - Low-altitude measurement unmanned aerial vehicle - Google Patents
Low-altitude measurement unmanned aerial vehicle Download PDFInfo
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- CN218703871U CN218703871U CN202222726607.0U CN202222726607U CN218703871U CN 218703871 U CN218703871 U CN 218703871U CN 202222726607 U CN202222726607 U CN 202222726607U CN 218703871 U CN218703871 U CN 218703871U
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Abstract
The utility model discloses a low-altitude measurement unmanned aerial vehicle, which belongs to the technical field of engineering measurement and comprises a machine body, wherein two sides of the machine body are provided with power mechanisms, the bottom of the machine body is fixedly connected with a motor, the bottom of the motor is fixedly connected with a fixing frame, one side of the fixing frame is provided with a rotating mechanism, one side of the rotating mechanism is fixedly connected with a measuring instrument, the bottom of the machine body is fixedly connected with a damper, the outside of the damper is provided with a damping spring, the bottom of the damper is fixedly connected with a supporting claw, and the bottoms of two sides of the machine body are fixedly provided with a supporting frame; the utility model discloses an organism, measuring apparatu, attenuator, damping spring, support claw and support frame can be better measure unmanned aerial vehicle to the low latitude and advance shock attenuation and buffering, have avoided most low latitude to measure unmanned aerial vehicle, are difficult to carry out the problem of shock attenuation and buffering to it to the use of measuring unmanned aerial vehicle has brought the facility for the low latitude.
Description
Technical Field
The utility model relates to an engineering survey technical field especially relates to an unmanned aerial vehicle is measured to low latitude.
Background
The aerial survey is a ground survey means using an aircraft in the atmosphere as a survey carrier, and the survey object is the position relation of a ground object, so as to draw the coordinates of the ground through data obtained by aerial photography, and the commonly adopted method is aerial photogrammetry.
Most low latitude measures unmanned aerial vehicle at the in-process that descends, because the in-process that descends probably causes certain impact to low latitude measurement unmanned aerial vehicle in the twinkling of an eye, traditional low latitude measures unmanned aerial vehicle, be difficult to cushion it when descending, lead to the one instant probably to cause the condition of damage to the low latitude caliber of descending, and most low latitude measures unmanned aerial vehicle, most is being difficult to advance the buffering to it when descending, also do not reserve certain buffer space, thereby make the condition of the damage of the instrument in the low latitude measurement unmanned aerial vehicle easily.
For this reason we propose a low-altitude survey drone.
SUMMERY OF THE UTILITY MODEL
Not enough to prior art, the utility model provides a low latitude measures unmanned aerial vehicle has overcome the not enough of prior art, aims at solving the problem in the background art.
In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an unmanned aerial vehicle is measured to low latitude, includes the organism, the both sides of organism are provided with power unit, the bottom fixedly connected with motor of organism, the bottom fixedly connected with mount of motor, one side of mount is provided with slewing mechanism, one side fixedly connected with measuring apparatu of slewing mechanism, the bottom fixed connection attenuator of organism, the externally mounted of attenuator has damping spring, the bottom fixedly connected with support claw of attenuator, the bottom fixed mounting of the both sides of organism has the support frame.
As a preferred technical scheme of the utility model, the power mechanism comprises a motor, the motor is fixedly connected with the machine body, and a spiral blade is fixedly connected to an output shaft of the motor; the output shaft on the motor drives the spiral blade to rotate, so that the aircraft can be better driven to take off.
As a preferred technical scheme of the utility model, the surface of the first motor is provided with radiating fins; the output shaft on the motor drives the fixing frame to move, and the fixing frame can be better driven to rotate.
As a preferred technical scheme of the utility model, the rotating mechanism comprises a second motor, the second motor is fixedly connected with the fixing frame, a transmission rod is fixedly connected to an output shaft of the second motor, and the transmission rod is fixedly connected with the measuring instrument; the output shaft on the second motor drives the transmission rod to rotate, and then the transmission rod drives the measuring instrument to rotate, so that the measuring instrument can be better driven to adjust the angle.
As a preferred technical scheme of the utility model, damping spring's quantity is two sets of for altogether, and every group is two altogether, through damping spring can be better carry out the effect of buffering to the organism.
As a preferred technical scheme of the utility model, the bottom of the supporting claw is fixedly connected with an anti-skid pad; carry out the shock attenuation through the attenuator to the organism, cushion by damping spring again, drive by the attenuator again and support the claw and support, can be better carry out the shock attenuation buffering to the organism.
As a preferred technical proposal of the utility model, one end of the supporting frame is fixedly connected with an anti-tilting block; the machine body can be better supported and prevented from inclining through the support frame and the anti-inclining block at the bottom.
The utility model has the advantages that:
the utility model discloses an organism, measuring apparatu, attenuator, damping spring, support claw and support frame can be better measure unmanned aerial vehicle to the low latitude and advance shock attenuation and buffering, have avoided most low latitude to measure unmanned aerial vehicle, are difficult to carry out the problem of shock attenuation and buffering to it to the use of measuring unmanned aerial vehicle has brought the facility for the low latitude.
Drawings
Fig. 1 is a schematic perspective view of the structure of the present invention;
fig. 2 is a schematic diagram of the structure of the present invention.
In the figure: 1. a body; 2. a power mechanism; 21. a motor; 22. helical leaves; 3. a first motor; 4. a fixed mount; 5. a rotating mechanism; 51. a second motor; 52. a transmission rod; 6. a measuring instrument; 7. a damper; 8. a damping spring; 9. a support claw; 10. a support frame.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Example one
Please refer to fig. 1-2, a low-altitude measurement unmanned aerial vehicle, including organism 1, its characterized in that, the both sides of organism 1 are provided with power unit 2, the bottom fixedly connected with motor 3 of organism 1, the bottom fixedly connected with mount 4 of motor 3, one side of mount 4 is provided with slewing mechanism 5, one side fixedly connected with measuring apparatu 6 of slewing mechanism 5, the bottom fixedly connected with attenuator 7 of organism 1, the externally mounted of attenuator 7 has damping spring 8, the bottom fixedly connected with of attenuator 7 supports claw 9, the bottom fixed mounting of the both sides of organism 1 has support frame 10.
In this embodiment, the power mechanism 2 includes a motor 21, the motor 21 is fixedly connected with the machine body 1, and a spiral blade 22 is fixedly connected to an output shaft of the motor 21; the output shaft of the motor 21 drives the spiral blade 22 to rotate, so that the aircraft body 1 can be better driven to take off.
In this embodiment, the surface of the first motor 3 is provided with a heat sink; the output shaft on the first motor 3 drives the fixing frame 4 to move, and the fixing frame 4 can be better driven to rotate.
In the embodiment, the rotating mechanism 5 includes a second motor 51, the second motor 51 is fixedly connected with the fixing frame 4, an output shaft of the second motor 51 is fixedly connected with a transmission rod 52, and the transmission rod 52 is fixedly connected with the measuring instrument 6; the output shaft of the second motor 51 drives the transmission rod 52 to rotate, and then the transmission rod 52 drives the measuring instrument 6 to rotate, so that the measuring instrument 6 can be better driven to adjust the angle.
The working principle is as follows: the output shaft on the motor 21 drives the spiral blade 22 to rotate, the machine body 1 can be better driven to take off, the output shaft on the first motor 3 drives the fixing frame 4 to move, the fixing frame 4 can be better driven to rotate, the output shaft on the second motor 51 drives the transmission rod 52 to rotate, the transmission rod 52 drives the measuring instrument 6 to rotate, and the measuring instrument 6 can be better driven to adjust the angle.
The number of the damping springs 8 is two, and each group is two, so that the machine body 1 can be better buffered through the damping springs 8, and the bottoms of the supporting claws 9 are fixedly connected with anti-skid pads; the machine body 1 is damped through the damper 7, then the damping is carried out through the damping spring 8, and then the damper 7 drives the supporting claw 9 to support, so that the machine body 1 can be better damped and buffered, and one end of the supporting frame 10 is fixedly connected with an anti-tilting block; the machine body 1 can be better supported and prevented from inclining through the support frame 10 and the anti-inclining block at the bottom.
The working principle is as follows: through the effect that damping spring 8 can be better cushion organism 1, carry out the shock attenuation through attenuator 7 to organism 1, cushion by damping spring 8 again, drive by attenuator 7 again and support claw 9 and support, can be better carry out the shock attenuation buffering to organism 1, through the piece of preventing inclining of support frame 10 and bottom, can be better support preventing inclining organism 1.
Finally, it should be noted that: in the description of the present invention, it should be noted that the terms "vertical", "upper", "lower", "horizontal", 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 in a specific orientation, and be operated, and thus should not be construed as limiting the present invention.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either 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 according to specific situations by those skilled in the art.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing embodiments, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. The utility model provides an unmanned aerial vehicle is measured to low latitude, includes organism (1), its characterized in that, the both sides of organism (1) are provided with power unit (2), motor (3) of bottom fixedly connected with of organism (1), bottom fixedly connected with mount (4) of motor (3), one side of mount (4) is provided with slewing mechanism (5), one side fixedly connected with measuring apparatu (6) of slewing mechanism (5), bottom fixed connection attenuator (7) of organism (1), the externally mounted of attenuator (7) has damping spring (8), the bottom fixedly connected with of attenuator (7) supports claw (9), the bottom fixed mounting of the both sides of organism (1) has support frame (10).
2. The low-altitude measurement unmanned aerial vehicle of claim 1, wherein the power mechanism (2) comprises a motor (21), the motor (21) is fixedly connected with the machine body (1), and a spiral blade (22) is fixedly connected to an output shaft of the motor (21).
3. The low-altitude measurement unmanned aerial vehicle of claim 1, wherein the surface of the first motor (3) is provided with cooling fins.
4. The unmanned aerial vehicle for low altitude measurement according to claim 1, wherein the rotating mechanism (5) comprises a second motor (51), the second motor (51) is fixedly connected with the fixing frame (4), a transmission rod (52) is fixedly connected to an output shaft of the second motor (51), and the transmission rod (52) is fixedly connected with the measuring instrument (6).
5. A low-altitude measurement unmanned aerial vehicle according to claim 1, wherein the number of the damping springs (8) is two groups, and each group is two.
6. The low-altitude measurement unmanned aerial vehicle of claim 1, wherein a non-slip mat is fixedly connected to the bottom of the supporting claw (9).
7. The unmanned aerial vehicle for low altitude survey according to claim 1, wherein one end of the supporting frame (10) is fixedly connected with an anti-tilt block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222726607.0U CN218703871U (en) | 2022-10-17 | 2022-10-17 | Low-altitude measurement unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222726607.0U CN218703871U (en) | 2022-10-17 | 2022-10-17 | Low-altitude measurement unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218703871U true CN218703871U (en) | 2023-03-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222726607.0U Active CN218703871U (en) | 2022-10-17 | 2022-10-17 | Low-altitude measurement unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218703871U (en) |
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2022
- 2022-10-17 CN CN202222726607.0U patent/CN218703871U/en active Active
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