CN216887212U - Solar energy continuation of journey unmanned aerial vehicle system - Google Patents
Solar energy continuation of journey unmanned aerial vehicle system Download PDFInfo
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- CN216887212U CN216887212U CN202123041493.8U CN202123041493U CN216887212U CN 216887212 U CN216887212 U CN 216887212U CN 202123041493 U CN202123041493 U CN 202123041493U CN 216887212 U CN216887212 U CN 216887212U
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- unmanned aerial
- aerial vehicle
- vehicle body
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- 230000007246 mechanism Effects 0.000 claims abstract description 54
- 238000013016 damping Methods 0.000 claims description 18
- 235000017166 Bambusa arundinacea Nutrition 0.000 claims description 15
- 235000017491 Bambusa tulda Nutrition 0.000 claims description 15
- 241001330002 Bambuseae Species 0.000 claims description 15
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims description 15
- 239000011425 bamboo Substances 0.000 claims description 15
- 238000007789 sealing Methods 0.000 claims description 11
- 210000004027 cell Anatomy 0.000 description 15
- 230000000712 assembly Effects 0.000 description 5
- 238000000429 assembly Methods 0.000 description 5
- 238000009434 installation Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 210000000170 cell membrane Anatomy 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 239000000049 pigment Substances 0.000 description 1
- 239000007921 spray Substances 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
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The utility model relates to the technical field of aircrafts, in particular to a solar cruising unmanned aerial vehicle system, which comprises a power supply mechanism, an unmanned aerial vehicle body and two balance mechanisms, wherein each balance mechanism comprises a motor, a rotating screw rod, a switching ring, a balancing weight, a slide rail, a slide block, a vertical plate and a bearing, the two balance mechanisms are respectively positioned at the top and the bottom of the unmanned aerial vehicle body and are arranged in an intersecting manner, so that one balance mechanism balances the left and right weight of the unmanned aerial vehicle body, one balance mechanism balances the front and back weight of the unmanned aerial vehicle body, the motor drives the rotating screw rod to rotate on the vertical plate through the bearing and drives the switching ring to drive the balancing weight to slide on the slide rail to the lighter side of the unmanned aerial vehicle body during rotation until the weights at the two sides of the unmanned aerial vehicle body are equal to the motor to stop outputting and keep the existing state, and the problem that equipment installed on the unmanned aerial vehicle body causes the overweight of one side of the unmanned aerial vehicle body is solved, make the unmanned aerial vehicle body take place the problem of slope when the flight.
Description
Technical Field
The utility model relates to the technical field of aircrafts, in particular to a solar endurance unmanned aerial vehicle system.
Background
Convert solar energy into the duration of electric energy for unmanned aerial vehicle body power supply multiplicable unmanned aerial vehicle body.
At present, prior art (CN109383808A) discloses a myriad unmanned aerial vehicle body that is applicable to low latitude and shoots, including the unmanned aerial vehicle body, unmanned aerial vehicle body surface scribbles the waterproof layer, the last fixed surface of unmanned aerial vehicle body installs the photovoltaic solar cell membrane, the lower fixed surface of rotor installs the storage case, the lower fixed surface of storage case is connected with high pressure nozzle, the lower fixed surface of unmanned aerial vehicle body installs infrared receiver, the other end fixedly connected with buffer of supporting leg. According to the utility model, through the buffer device, the buffer support can be provided when the unmanned aerial vehicle body is landed after being aerial-photographed, the pigment placed in the storage box is sprayed in the air through the high-pressure spray head through the first electric hydraulic rod, a certain atmosphere is added to a wedding when the unmanned aerial vehicle body is aerial-photographed, and through the standby cruising system formed by the photovoltaic solar cell film, the storage battery and other components, the standby electric energy is provided for the unmanned aerial vehicle body during aerial-photographing, so that the cruising ability of the unmanned aerial vehicle body is improved.
In this way, because of the equipment of installation leads to one side overweight of unmanned aerial vehicle body on the unmanned aerial vehicle body for the unmanned aerial vehicle body takes place to incline when the flight, deviates from the flight route.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a solar endurance unmanned aerial vehicle system, and aims to solve the problem that one side of an unmanned aerial vehicle body is too heavy due to equipment installed on the unmanned aerial vehicle body, so that the unmanned aerial vehicle body is inclined in flight.
In order to achieve the purpose, the utility model provides a solar cruising unmanned aerial vehicle system which comprises a power supply mechanism, an unmanned aerial vehicle body and two balance mechanisms, wherein the power supply mechanism is arranged on one side of the unmanned aerial vehicle body, and the two balance mechanisms are respectively arranged on two sides of the unmanned aerial vehicle body;
the balancing mechanism comprises a motor, a rotating screw rod, a switching ring, a balancing weight, a sliding rail, a sliding block, a vertical plate and a bearing, wherein the motor is fixedly connected with the unmanned aerial vehicle body and is positioned on the outer side wall of the unmanned aerial vehicle body, the rotating screw rod is fixedly connected with the output end of the motor, the switching ring is rotatably connected with the rotating screw rod and is positioned on the outer side wall of the rotating screw rod, the balancing weight is fixedly connected with the switching ring and is positioned on the outer side wall of the switching ring, the sliding rail is fixedly connected with the unmanned aerial vehicle body and is positioned on one side close to the motor, one side of the sliding block is fixedly connected with the balancing weight, the other side of the sliding block is slidably connected with the sliding rail and is positioned on the inner side wall of the sliding rail, the vertical plate is fixedly connected with the unmanned aerial vehicle body and is positioned on one side close to the motor, and the inner ring of the bearing is fixedly connected with the rotating screw rod, the outer ring of the bearing is fixedly connected with the vertical plate and is positioned between the rotary screw rod and the vertical plate.
The balance mechanism further comprises a sliding rod, the sliding rod is fixedly connected with the sliding rail and is located on the inner side wall of the sliding rail, and the sliding block is connected with the sliding rod in a sliding mode and is located on the outer side wall of the sliding rod.
The balance mechanism further comprises two buffer springs, one sides of the two buffer springs are fixedly connected with the sliding block respectively and located on two sides of the sliding block respectively, and the other sides of the two buffer springs are fixedly connected with the sliding rail respectively and located on the inner side wall of the sliding rail.
Wherein, power supply mechanism includes battery and solar cell panel, the battery with unmanned aerial vehicle body fixed connection, and be located unmanned aerial vehicle body top, solar cell panel with battery fixed connection, and be located keep away from one side of unmanned aerial vehicle body.
Wherein, power supply mechanism still includes a plurality of direction subassemblies and a plurality of damping spring, and is a plurality of one side of direction subassembly respectively with solar cell panel fixed connection, it is a plurality of the opposite side of direction subassembly respectively with unmanned aerial vehicle body fixed connection all is located solar cell panel with between the unmanned aerial vehicle body, it is a plurality of damping spring respectively with a plurality of direction subassembly fixed connection all is located in the direction subassembly.
Wherein, power supply mechanism still includes the sealing washer, one side of sealing washer with solar cell panel fixed connection, the opposite side of sealing washer with unmanned aerial vehicle body fixed connection, and be located solar cell panel with between the unmanned aerial vehicle body.
Wherein, the direction subassembly includes a fixed section of thick bamboo and a guide cylinder, a fixed section of thick bamboo with unmanned aerial vehicle body fixed connection to be located and be close to one side of solar cell panel, damping spring with a fixed section of thick bamboo fixed connection, and be located in the fixed section of thick bamboo, a guide cylinder with damping spring fixed connection, and run through a fixed section of thick bamboo, solar cell panel with guide cylinder fixed connection.
According to the solar continuous-flight unmanned aerial vehicle system, the two balance mechanisms are respectively positioned at the top and the bottom of the unmanned aerial vehicle body and are arranged in an intersecting manner, so that one balance mechanism balances the left and right weight of the unmanned aerial vehicle body, the other balance mechanism balances the front and back weight of the unmanned aerial vehicle body, the motor of the balance mechanism drives the rotating screw rod to rotate on the vertical plate through the bearing and drives the adapter ring to drive the balancing weight to slide on the sliding rail to the lighter side of the unmanned aerial vehicle body when rotating until the weights of the two sides of the unmanned aerial vehicle body are equal, the motor stops outputting and keeps the existing state, and the problem that the unmanned aerial vehicle body inclines when flying due to the fact that equipment installed on the unmanned aerial vehicle body is too heavy on one side of the unmanned aerial vehicle body is solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a solar cruising unmanned aerial vehicle system provided by the utility model.
Fig. 2 is a front view of a solar cruising unmanned aerial vehicle system provided by the utility model.
Fig. 3 is a cross-sectional view taken along plane a-a of fig. 2.
Fig. 4 is a top view of a solar cruising unmanned aerial vehicle system provided by the utility model.
Fig. 5 is a cross-sectional view taken along plane B-B of fig. 4.
1-power supply mechanism, 2-unmanned aerial vehicle body, 3-balance mechanism, 4-motor, 5-rotating screw rod, 6-adapter ring, 7-counterweight block, 8-slide rail, 9-slide block, 10-vertical plate, 11-bearing, 12-slide bar, 13-buffer spring, 14-storage battery, 15-solar panel, 16-guide component, 17-damping spring, 18-sealing ring, 19-fixing cylinder, 20-guide cylinder, 21-supporting leg and 22-buffer pad.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the utility model and are not to be construed as limiting the utility model.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
Referring to fig. 1 to 5, the utility model provides a solar cruising unmanned aerial vehicle system, which includes a power supply mechanism 1, an unmanned aerial vehicle body 2 and two balance mechanisms 3, wherein the power supply mechanism 1 is arranged on one side of the unmanned aerial vehicle body 2, and the two balance mechanisms 3 are respectively arranged on two sides of the unmanned aerial vehicle body 2;
the balancing mechanism 3 comprises a motor 4, a rotating screw rod 5, a switching ring 6, a balancing weight 7, a slide rail 8, a slide block 9, a vertical plate 10 and a bearing 11, wherein the motor 4 is fixedly connected with the unmanned aerial vehicle body 2 and is positioned on the outer side wall of the unmanned aerial vehicle body 2, the rotating screw rod 5 is fixedly connected with the output end of the motor 4, the switching ring 6 is rotatably connected with the rotating screw rod 5 and is positioned on the outer side wall of the rotating screw rod 5, the balancing weight 7 is fixedly connected with the switching ring 6 and is positioned on the outer side wall of the switching ring 6, the slide rail 8 is fixedly connected with the unmanned aerial vehicle body 2 and is positioned on one side close to the motor 4, one side of the slide block 9 is fixedly connected with the balancing weight 7, the other side of the slide block 9 is slidably connected with the slide rail 8 and is positioned on the inner side wall of the slide rail 8, and the vertical plate 10 is fixedly connected with the unmanned aerial vehicle body 2, and is located near one side of the motor 4, the inner ring of the bearing 11 is fixedly connected with the rotary screw rod 5, the outer ring of the bearing 11 is fixedly connected with the vertical plate 10 and is located between the rotary screw rod 5 and the vertical plate 10.
In the embodiment, the unmanned aerial vehicle body 2 provides installation conditions for the power supply mechanism 1, two balance mechanisms 3 and other devices, the power supply mechanism 1 converts solar energy into electric energy to provide electric quantity for the operation of the unmanned aerial vehicle body 2, the cruising ability of the unmanned aerial vehicle body 2 is increased, the two balance mechanisms 3 are used for balancing the weight of the unmanned aerial vehicle body 2, so that the surrounding gravity of the unmanned aerial vehicle body 2 is still equal after the devices are installed, the unmanned aerial vehicle body 2 is prevented from inclining in flight and colliding with other unmanned aerial vehicles deviating from the flight line, specifically, the two balance mechanisms 3 are respectively positioned at the top and the bottom of the unmanned aerial vehicle body 2 and are arranged in an intersecting manner, so that one balance mechanism 3 balances the weight of the unmanned aerial vehicle body 2 on the left and right, and one balance mechanism 3 balances the weight of the unmanned aerial vehicle body 2 on the front and back, balance mechanism 3 motor 4 drive rotate lead screw 5 and pass through bearing 11 is in rotate on the riser 10, and the drive when rotating switching ring 6 drives balancing weight 7 is in on the slide rail 8 to the one side that unmanned aerial vehicle body 2 is lighter slides, until the weight of 2 both sides of unmanned aerial vehicle body equals, motor 4 stops the output and keeps current state, and the equipment of having solved installation on the unmanned aerial vehicle body 2 leads to one side overweight of unmanned aerial vehicle body 2 for unmanned aerial vehicle body 2 takes place the problem of slope when flying.
Further, the balance mechanism 3 further comprises a slide bar 12, the slide bar 12 is fixedly connected with the slide rail 8 and is positioned on the inner side wall of the slide rail 8, and the slide block 9 is slidably connected with the slide bar 12 and is positioned on the outer side wall of the slide bar 12; the balance mechanism 3 further comprises two buffer springs 13, one sides of the two buffer springs 13 are fixedly connected with the sliding block 9 respectively and located on two sides of the sliding block 9 respectively, and the other sides of the two buffer springs 13 are fixedly connected with the sliding rail 8 respectively and located on the inner side wall of the sliding rail 8.
In this embodiment, the slide bar 12 runs through the slider 9, will the slider 9 is further connected on the slide rail 8, can avoid 2 bottoms of unmanned aerial vehicle body 3 the slider 9 drops because of gravity follows on the slide rail 8, buffer spring 13 can absorb the unmanned aerial vehicle body 2 transmits the vibration of slider 9 when flying to increase on the slider 9 the stability of balancing weight 7.
Further, the power supply mechanism 1 comprises a storage battery 14 and a solar panel 15, the storage battery 14 is fixedly connected with the unmanned aerial vehicle body 2 and is located at the top of the unmanned aerial vehicle body 2, and the solar panel 15 is fixedly connected with the storage battery 14 and is located on one side far away from the unmanned aerial vehicle body 2; the power supply mechanism 1 further comprises a plurality of guide assemblies 16 and a plurality of damping springs 17, one sides of the guide assemblies 16 are fixedly connected with the solar cell panel 15, the other sides of the guide assemblies 16 are fixedly connected with the unmanned aerial vehicle body 2 and are located between the solar cell panel 15 and the unmanned aerial vehicle body 2, and the damping springs 17 are fixedly connected with the guide assemblies 16 and are located in the guide assemblies 16; the power supply mechanism 1 further comprises a sealing ring 18, one side of the sealing ring 18 is fixedly connected with the solar cell panel 15, and the other side of the sealing ring 18 is fixedly connected with the unmanned aerial vehicle body 2 and is positioned between the solar cell panel 15 and the unmanned aerial vehicle body 2; the direction subassembly 16 is including a fixed section of thick bamboo 19 and a guide cylinder 20, a fixed section of thick bamboo 19 with 2 fixed connection of unmanned aerial vehicle body, and be located and be close to one side of solar cell panel 15, damping spring 17 with a fixed section of thick bamboo 19 fixed connection, and be located in a fixed section of thick bamboo 19, a guide cylinder 20 with damping spring 17 fixed connection, and run through a fixed section of thick bamboo 19, solar cell panel 15 with a guide cylinder 20 fixed connection.
In this embodiment, the solar panel 15 of the power supply mechanism 1 converts solar energy into electric energy to be stored in the storage battery 14, the storage battery 14 provides electric power for the operation of the unmanned aerial vehicle body 2, the guiding component 16 connects the solar panel 15 with the unmanned aerial vehicle body 2, the damping spring 17 absorbs the vibration transmitted to the solar panel 15 when the unmanned aerial vehicle body 2 flies, the guiding cylinder 20 of the guiding component 16 slides in the fixing cylinder 19 to guide the damping spring 17, so that the damping spring 17 can only perform telescopic damping in the fixing cylinder 19, the damping spring 17 is prevented from bending to drive the solar panel 15 to swing, and the sealing ring 18 is used for filling a gap between the solar panel 15 and the unmanned aerial vehicle body 2, avoid impurity and rainwater to fall into unmanned aerial vehicle body 2 from the gap in, it is right battery 14 causes the damage.
Further, the power supply mechanism 1 further comprises a plurality of support legs 21, and the support legs 21 are respectively and fixedly connected with the unmanned aerial vehicle body 2 and are all positioned at the bottom of the unmanned aerial vehicle body 2; power supply mechanism 1 still includes a plurality of blotter 22, and is a plurality of blotter 22 respectively with a plurality of supporting leg 21 fixed connection all is located and keeps away from one side of unmanned aerial vehicle body 2.
In this embodiment, the supporting leg 21 is used for increasing the distance between the bottom of the unmanned aerial vehicle body 2 and the placing surface, and avoiding that the distance between the unmanned aerial vehicle body 2 and the placing surface is too close, so that the balance mechanism 3 at the bottom of the unmanned aerial vehicle body 2 is damaged due to friction with the placing surface, and the cushion pad 22 can provide protection for the unmanned aerial vehicle body 2 by impact generated when the unmanned aerial vehicle body 2 descends.
While the present invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the utility model.
Claims (7)
1. A solar cruising unmanned aerial vehicle system is characterized in that,
the unmanned aerial vehicle comprises a power supply mechanism, an unmanned aerial vehicle body and two balance mechanisms, wherein the power supply mechanism is arranged on one side of the unmanned aerial vehicle body, and the two balance mechanisms are respectively arranged on two sides of the unmanned aerial vehicle body;
the balancing mechanism comprises a motor, a rotating screw rod, a switching ring, a balancing weight, a sliding rail, a sliding block, a vertical plate and a bearing, wherein the motor is fixedly connected with the unmanned aerial vehicle body and is positioned on the outer side wall of the unmanned aerial vehicle body, the rotating screw rod is fixedly connected with the output end of the motor, the switching ring is rotatably connected with the rotating screw rod and is positioned on the outer side wall of the rotating screw rod, the balancing weight is fixedly connected with the switching ring and is positioned on the outer side wall of the switching ring, the sliding rail is fixedly connected with the unmanned aerial vehicle body and is positioned on one side close to the motor, one side of the sliding block is fixedly connected with the balancing weight, the other side of the sliding block is slidably connected with the sliding rail and is positioned on the inner side wall of the sliding rail, the vertical plate is fixedly connected with the unmanned aerial vehicle body and is positioned on one side close to the motor, and the inner ring of the bearing is fixedly connected with the rotating screw rod, the outer ring of the bearing is fixedly connected with the vertical plate and is positioned between the rotary screw rod and the vertical plate.
2. The solar endurance drone system of claim 1,
the balance mechanism further comprises a sliding rod, the sliding rod is fixedly connected with the sliding rail and is positioned on the inner side wall of the sliding rail, and the sliding block is slidably connected with the sliding rod and is positioned on the outer side wall of the sliding rod.
3. The solar endurance drone system of claim 1,
the balance mechanism further comprises two buffer springs, one sides of the two buffer springs are fixedly connected with the sliding block respectively and located on two sides of the sliding block respectively, and the other sides of the two buffer springs are fixedly connected with the sliding rail respectively and located on the inner side wall of the sliding rail.
4. The solar endurance drone system of claim 1,
the power supply mechanism comprises a storage battery and a solar cell panel, the storage battery is fixedly connected with the unmanned aerial vehicle body and is positioned at the top of the unmanned aerial vehicle body, and the solar cell panel is fixedly connected with the storage battery and is positioned at one side of the unmanned aerial vehicle body.
5. The solar endurance drone system of claim 4,
power supply mechanism still includes a plurality of direction subassemblies and a plurality of damping spring, and is a plurality of one side of direction subassembly respectively with solar cell panel fixed connection, it is a plurality of the opposite side of direction subassembly respectively with unmanned aerial vehicle body fixed connection all is located solar cell panel with between the unmanned aerial vehicle body, it is a plurality of damping spring respectively with a plurality of direction subassembly fixed connection all is located in the direction subassembly.
6. The solar endurance drone system of claim 4,
the power supply mechanism further comprises a sealing ring, one side of the sealing ring is fixedly connected with the solar cell panel, the other side of the sealing ring is fixedly connected with the unmanned aerial vehicle body and located between the solar cell panel and the unmanned aerial vehicle body.
7. The solar endurance drone system of claim 5,
the direction subassembly includes a fixed section of thick bamboo and a guide cylinder, a fixed section of thick bamboo with unmanned aerial vehicle body fixed connection to be located and be close to one side of solar cell panel, damping spring with a fixed section of thick bamboo fixed connection, and be located in the fixed section of thick bamboo, a guide cylinder with damping spring fixed connection, and run through a fixed section of thick bamboo, solar cell panel with guide cylinder fixed connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123041493.8U CN216887212U (en) | 2021-12-06 | 2021-12-06 | Solar energy continuation of journey unmanned aerial vehicle system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123041493.8U CN216887212U (en) | 2021-12-06 | 2021-12-06 | Solar energy continuation of journey unmanned aerial vehicle system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216887212U true CN216887212U (en) | 2022-07-05 |
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ID=82204006
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123041493.8U Expired - Fee Related CN216887212U (en) | 2021-12-06 | 2021-12-06 | Solar energy continuation of journey unmanned aerial vehicle system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216887212U (en) |
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2021
- 2021-12-06 CN CN202123041493.8U patent/CN216887212U/en not_active Expired - Fee Related
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220705 |