CN209833988U - A hydraulic engineering unmanned aerial vehicle for remote sensing survey and drawing - Google Patents
A hydraulic engineering unmanned aerial vehicle for remote sensing survey and drawing Download PDFInfo
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- CN209833988U CN209833988U CN201920252080.8U CN201920252080U CN209833988U CN 209833988 U CN209833988 U CN 209833988U CN 201920252080 U CN201920252080 U CN 201920252080U CN 209833988 U CN209833988 U CN 209833988U
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Abstract
The utility model discloses a hydraulic engineering unmanned aerial vehicle for remote sensing survey and drawing relates to unmanned air vehicle technical field, when aiming at solving unmanned aerial vehicle and descending with great speed, the problem of the great impact force of unmanned aerial vehicle is given to landing place surface transmission. Its technical scheme main points are, including the fuselage and along four foot rests of fuselage circumference evenly distributed, the foot rest is including the vertical first supporting leg that is fixed in the fuselage, and the one end that the fuselage was kept away from to first supporting leg articulates there is cylindric second supporting leg, and the second supporting leg slope is connected in the upper end of first supporting leg and second supporting leg and the contained angle between the first supporting leg is the acute angle, and the articulated department of first supporting leg and second supporting leg is located the one end that the second supporting leg is close to the upper end. When unmanned aerial vehicle landed, the lower extreme of second supporting leg contacted the landing surface earlier, and then under the self action of gravity of fuselage, the second supporting leg rotated to laminating with ground for the landing has certain buffering time, reaches the purpose that reduces the landing impact force.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle's technique and specifically relates to a hydraulic engineering unmanned aerial vehicle for remote sensing survey and drawing is related to.
Background
Unmanned aerial vehicle is the unmanned vehicles who utilizes radio remote control equipment and self-contained program control device operation, and at present, unmanned aerial vehicle extensively is used for the water conservancy to measure. The requirements of water conservancy and hydropower engineering on terrain, cost and precision are higher and higher, the traditional engineering measurement technology has certain thorny chirality in dealing with high-precision and real-time data information acquisition work, and the unmanned aerial vehicle has incomparable superiority in the aspect of remote sensing measurement due to the characteristics of flexibility, high resolution, low cost, high timeliness and the like.
The current chinese patent with an authorization bulletin number of CN104386249B discloses a surveying and mapping method for rapidly surveying and mapping multi-rotor unmanned aerial vehicle, which comprises a frame, a flight lifting mechanism, a holder mechanism and a control mechanism, the frame stretches out four arms along its organism, the organism lower part is provided with a foot rest, the arms and the foot rest are foldable structures, the flight lifting mechanism is arranged at the tail ends of the four arms, the holder mechanism is hung at the bottom of the unmanned aerial vehicle organism through a hanging rod, a camera is installed on the holder mechanism, the holder mechanism is used for adjusting the optical axis of the camera to be perpendicular to the ground all the time, and the control mechanism is used for controlling the unmanned aerial vehicle to fly to a specified height and.
The above prior art solutions have the following drawbacks: when unmanned aerial vehicle need descend with great speed, the landing place surface can transmit the great impact force of unmanned aerial vehicle organism through the foot rest, leads to unmanned aerial vehicle to land unstably easily, consequently remains further to improve.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a hydraulic engineering unmanned aerial vehicle for remote sensing survey and drawing, it has the effect that reduces the landing impact force.
The above technical purpose of the present invention can be achieved by the following technical solutions:
the utility model provides a hydraulic engineering unmanned aerial vehicle for remote sensing survey and drawing, includes the fuselage and follows four foot rests of fuselage circumference evenly distributed, the foot rest is including the vertical first supporting leg that is fixed in the fuselage, the one end that the fuselage was kept away from to first supporting leg articulates there is cylindric second supporting leg, second supporting leg slope is connected in the upper end of first supporting leg and second supporting leg and the contained angle between the first supporting leg is the acute angle, the articulated department of first supporting leg and second supporting leg is located the one end that the second supporting leg is close to the upper end.
Through adopting above-mentioned technical scheme, when unmanned aerial vehicle landed, the lower extreme of second supporting leg contacted the landing surface earlier. Subsequently under unmanned aerial vehicle self action of gravity, the second supporting leg rotates gradually to laminating with ground, and at this in-process, the landing has certain buffering time, has reduced the impact force to the fuselage when landing to make unmanned aerial vehicle steadily fall to the ground.
The utility model discloses further set up to: an elastic piece is connected between the upper end of the second supporting leg and the first supporting leg.
By adopting the technical scheme, the lower end of the second supporting leg firstly contacts the landing surface when landing. Subsequently under unmanned aerial vehicle self action of gravity, the second supporting leg rotates gradually to laminating with ground, and at this in-process, the elastic component is stretched, has certain cushioning effect, has reduced the impact force to the fuselage when landing.
The utility model discloses further set up to: and one end of the second supporting leg, which lands first, is wrapped with a cylindrical rubber pad.
Through adopting above-mentioned technical scheme, when unmanned aerial vehicle landed, because the lower extreme of second supporting leg contacts the landing surface earlier, under the parcel effect of rubber pad, the contact jaw of second supporting leg has obtained the protection, has reduced the rigid contact to reduce the wearing and tearing of second supporting leg, prolonged the life of second supporting leg.
The utility model discloses further set up to: the circumference side of the one end of second supporting leg that lands earlier is gone up the circumference equidistance interval and is provided with a plurality of rubber fixture blocks, the inner wall of rubber pad is seted up with rubber fixture block inlay card complex draw-in groove.
Through adopting above-mentioned technical scheme, through the corresponding draw-in groove of rubber fixture block card embedding, because there is certain frictional force between rubber fixture block and the rubber pad, install the rubber pad on the second supporting leg. When the rubber pad is worn and needs to be replaced, the rubber clamping block and the clamping groove are separated, and a new rubber pad is replaced quickly.
The utility model discloses further set up to: the second supporting leg is provided with an adsorption piece on the end face which is landed firstly, and an adsorption piece which is magnetically attracted with the adsorption piece is arranged on the inner bottom wall of the rubber pad.
Through adopting above-mentioned technical scheme, inhale the piece and adsorb the gravitation effect between the piece through magnetism, improve the stability that the rubber pad is connected.
The utility model discloses further set up to: and a cushion pad is arranged on the landing surface of the second supporting leg.
Through adopting above-mentioned technical scheme, the blotter can adopt the rubber material, and when the second supporting leg landed completely, the blotter contacted with the landing surface, had certain cushioning effect, reduced the impact force of falling to the ground.
The utility model discloses further set up to: a plurality of cavities are arranged in the cushion pad at equal intervals along the length direction of the second supporting leg.
Through adopting above-mentioned technical scheme, the cavity makes to be local hollow state in the blotter, has increased the flexibility of blotter. When the second supporting leg completely lands, the cushion pad is in contact with the landing surface to play a role in buffering, and the landing impact force is further reduced.
The utility model discloses further set up to: and a spring with the elastic force direction being consistent with the axial direction of the first supporting leg when the second supporting leg completely lands is arranged in the cavity.
Through adopting above-mentioned technical scheme, because the blotter is the rubber material, after the live time is long under the oxidation, the elasticity decline of blotter, the cooperation of spring and cavity makes the blotter keep lasting elasticity, prolongs the life of blotter.
To sum up, the utility model discloses a beneficial technological effect does:
1. through the arrangement of the second supporting legs, when the unmanned aerial vehicle lands, the lower ends of the second supporting legs firstly contact with a landing surface, and then the second supporting legs gradually rotate to be attached to the ground under the action of the gravity of the unmanned aerial vehicle;
2. through the arrangement of the elastic piece, the elastic piece is stretched in the process that the second supporting leg gradually rotates to be attached to the ground, so that a certain buffering effect is achieved, and the impact force on the machine body during landing is further reduced;
3. through the setting of rubber pad, under the parcel effect of rubber pad, the contact jaw of second supporting leg has obtained the protection, has reduced the rigid contact to reduce the wearing and tearing of second supporting leg, prolonged the life of second supporting leg.
Drawings
Fig. 1 is a schematic view of the overall structure of an unmanned aerial vehicle in an embodiment of the present invention when the unmanned aerial vehicle is not landed;
fig. 2 is a schematic sectional view of a part of the structure of the unmanned aerial vehicle landing according to the embodiment of the present invention;
FIG. 3 is an enlarged schematic view of portion A of FIG. 2;
fig. 4 is a partially exploded schematic view for showing a rubber pad coupling structure.
In the figure, 1, a fuselage; 2. a foot rest; 21. a first support leg; 22. a second support leg; 3. an elastic member; 4. a rubber pad; 41. a card slot; 5. an adsorbing member; 6. a magnetic member; 7. a cushion pad; 71. a cavity; 72. a spring; 8. and (4) a rubber clamping block.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Referring to fig. 1, for the utility model discloses a hydraulic engineering unmanned aerial vehicle for remote sensing survey and drawing, including fuselage 1 and along 1 circumference evenly distributed's of fuselage four foot rests 2, install camera device on fuselage 1, fuselage 1 can be in the high altitude stable flight under the rotation of screw, utilizes camera device to carry out high definition shooting and shoot night to realize the topography survey and drawing. Each foot rest 2 comprises a first support leg 21 fixed on the body 1, and the first support leg 21 is arranged along the vertical direction. One end of the first supporting leg 21, which is far away from the machine body 1, is hinged with a second supporting leg 22, and the second supporting leg 22 and the first supporting leg 21 are both made of aluminum alloy materials, so that the weight of the machine body 1 is reduced, and the cruising ability is improved. The second support leg 22 is obliquely arranged relative to the first support leg 21, an included angle between the upper end of the second support leg 22 and the first support leg 21 is an acute angle, and the angle a in fig. 1 is 45 °. The hinge joint of the first support leg 21 and the second support leg 22 is located at one end of the second support leg 22 near the upper end, so that the center of the second support leg 22 does not coincide with the axis of the first support leg 21.
Referring to fig. 1 and 2, in order to reduce the impact force to the body 1 when landing, an elastic member 3 is connected between the upper end of the second support leg 22 and the first support leg 21, and the elastic member 3 may be a spring. Second supporting leg 22 rotates gradually to the in-process with ground laminating, and elastic component 3 is stretched, for landing provides certain buffering time, has certain cushioning effect to make unmanned aerial vehicle steadily fall to the ground.
Referring to fig. 2 and 3, a cushion 7 is further bonded to the landing surface of the second support leg 22, and the cushion 7 is made of rubber. When the second support leg 22 completely lands, the buffer pad 7 is in contact with the landing surface, and has a certain buffer function. In order to further improve the buffering effect of the buffering cushion 7, a plurality of cavities 71 are formed in the buffering cushion 7, and the cavities 71 are equidistantly distributed along the length direction of the buffering cushion 7. The cavity 71 makes the inside of the cushion pad 7 partially hollow, and increases the flexibility of the cushion pad 7. Because the buffer pad 7 is made of rubber, the elasticity of the buffer pad 7 is reduced under the oxidation action after the use time. In order to maintain the cushion 7 with a permanent elastic force, a spring 72 is provided in the cavity 71. When the second support leg 22 is completely engaged with the landing surface, the spring force direction of the spring 72 coincides with the axial direction of the first support leg 21. The cooperation of the spring 72 and the cavity 71 enables the cushion pad 7 to maintain a lasting elastic force, and prolongs the service life of the cushion pad 7. And spring 72 further plays the elastic buffer effect for unmanned aerial vehicle steadily falls to the ground.
Referring to fig. 3 and 4, when the unmanned aerial vehicle lands, one end of the second support leg 22 close to the lower side contacts the landing surface first, and in order to protect the landing end of the second support leg 22, the end of the second support leg 22 which lands first is wrapped with a cylindrical rubber pad 4. Under the wrapping effect of rubber pad 4, the contact end of second supporting leg 22 has been protected, has reduced the rigid contact to reduce the wearing and tearing of second supporting leg 22, prolonged the life of second supporting leg 22. After the rubber pad 4 is worn and torn, in order to change the rubber pad 4 conveniently, a plurality of rubber fixture blocks 8 are adhered to the circumferential side face of the end, landing first, of the second supporting leg 22 at intervals in the circumferential direction, and the rubber fixture blocks 8 are rectangular. The inner wall of the rubber pad 4 is provided with a clamping groove 41 which is in clamping fit with the rubber clamping block 8. In order to maintain the connection stability of the rubber pad 4, the end face of the second support leg 22, which is landed first, is embedded with the adsorbing member 5, and the inner bottom wall of the rubber pad 4 is embedded with the magnetic attracting member 6 which is magnetically attracted to the adsorbing member 5. In this embodiment, the adsorbing member 5 is an iron sheet, and the magnetic member 6 is a magnet. The rubber pad 4 is further stably mounted on the second support leg 22 by the attraction force between the attraction member 5 and the magnetic attraction member 6. When the rubber pad 4 is replaced, the attraction force between the magnetic attraction piece 6 and the adsorption piece 5 is overcome, and the rubber pad 4 is pulled outwards, so that the clamping groove 41 is separated from the rubber clamping block 8.
The implementation principle of the embodiment is as follows: when unmanned aerial vehicle landed, the lower extreme of second supporting leg 22 contacted the landing surface earlier, and then under 1 action of gravity of unmanned aerial vehicle's fuselage, second supporting leg 22 rotates gradually to laminating with the landing surface, and elastic component 3 is stretched simultaneously, provides certain buffering time for the landing, has reduced the impact force to fuselage 1 when landing to make unmanned aerial vehicle steadily fall to the ground.
The embodiment of this specific implementation mode is the preferred embodiment of the present invention, not limit according to this the utility model discloses a protection scope, so: all equivalent changes made according to the structure, shape and principle of the utility model are covered within the protection scope of the utility model.
Claims (8)
1. The utility model provides a hydraulic engineering unmanned aerial vehicle for remote sensing survey and drawing, includes fuselage (1) and four foot rests (2) along fuselage (1) circumference evenly distributed, its characterized in that: the tripod (2) comprises a vertical first supporting leg (21) fixed on the machine body (1), and one end, far away from the machine body (1), of the first supporting leg (21) is hinged with a cylindrical second supporting leg (22); the included angle that second supporting leg (22) slope is connected between the upper end of first supporting leg (21) and second supporting leg (22) and first supporting leg (21) is the acute angle, the articulated department of first supporting leg (21) and second supporting leg (22) is located second supporting leg (22) and is close to the one end of upper end.
2. The hydraulic engineering unmanned aerial vehicle for remote sensing surveying and mapping of claim 1, wherein: an elastic piece (3) is connected between the upper end of the second supporting leg (22) and the first supporting leg (21).
3. The hydraulic engineering unmanned aerial vehicle for remote sensing surveying and mapping of claim 1, wherein: one end of the second supporting leg (22) which lands firstly is wrapped with a cylindrical rubber pad (4).
4. A hydraulic engineering drone for remote sensing surveying according to claim 3, characterized in that: the first landing end of the second supporting leg (22) is circumferentially provided with a plurality of rubber clamping blocks (8) at equal intervals, and the inner wall of the rubber pad (4) is provided with clamping grooves (41) which are in clamping fit with the rubber clamping blocks (8).
5. The hydraulic engineering unmanned aerial vehicle for remote sensing surveying of claim 4, wherein: the end face of the second supporting leg (22) which is landed firstly is provided with an adsorption piece (5), and the inner bottom wall of the rubber pad (4) is provided with a magnetic piece (6) which is magnetically attracted with the adsorption piece (5).
6. The hydraulic engineering unmanned aerial vehicle for remote sensing surveying and mapping of claim 1, wherein: a cushion pad (7) is arranged on the landing surface of the second supporting leg (22).
7. The hydraulic engineering unmanned aerial vehicle for remote sensing surveying of claim 6, wherein: a plurality of cavities (71) are arranged in the buffer pad (7) at equal intervals along the length direction of the second supporting leg (22).
8. The hydraulic engineering unmanned aerial vehicle for remote sensing surveying and mapping of claim 7, wherein: and a spring (72) with the elastic force direction being consistent with the axial direction of the first supporting leg (21) when the second supporting leg (22) completely lands is arranged in the cavity (71).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920252080.8U CN209833988U (en) | 2019-02-28 | 2019-02-28 | A hydraulic engineering unmanned aerial vehicle for remote sensing survey and drawing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920252080.8U CN209833988U (en) | 2019-02-28 | 2019-02-28 | A hydraulic engineering unmanned aerial vehicle for remote sensing survey and drawing |
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| Publication Number | Publication Date |
|---|---|
| CN209833988U true CN209833988U (en) | 2019-12-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920252080.8U Expired - Fee Related CN209833988U (en) | 2019-02-28 | 2019-02-28 | A hydraulic engineering unmanned aerial vehicle for remote sensing survey and drawing |
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| CN (1) | CN209833988U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111874215A (en) * | 2020-08-10 | 2020-11-03 | 浙江广盛环境建设集团有限公司 | Remote sensing unmanned aerial vehicle |
-
2019
- 2019-02-28 CN CN201920252080.8U patent/CN209833988U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111874215A (en) * | 2020-08-10 | 2020-11-03 | 浙江广盛环境建设集团有限公司 | Remote sensing unmanned aerial vehicle |
| CN111874215B (en) * | 2020-08-10 | 2022-06-24 | 浙江广盛环境建设集团有限公司 | Remote sensing unmanned aerial vehicle |
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| GR01 | Patent grant | ||
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191224 |
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| CF01 | Termination of patent right due to non-payment of annual fee |