CN110077579B - Unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle Download PDFInfo
- Publication number
- CN110077579B CN110077579B CN201910410033.6A CN201910410033A CN110077579B CN 110077579 B CN110077579 B CN 110077579B CN 201910410033 A CN201910410033 A CN 201910410033A CN 110077579 B CN110077579 B CN 110077579B
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- Prior art keywords
- battery
- host
- aerial vehicle
- unmanned aerial
- driving motor
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
- H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
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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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
Abstract
The invention discloses an unmanned aerial vehicle, which comprises an unmanned aerial vehicle remotely controlled by a remote controller, wherein the unmanned aerial vehicle comprises a host, a battery assembly is arranged at the bottom of the host in an opening-closing manner, a propeller is arranged at the top of the host, a control mainboard and a driving motor are arranged inside the host, the driving motor is arranged on a supporting plate inside the host, the power input end of the control mainboard supplies power through the battery assembly, the driving motor is controlled and supplied power through the control mainboard, the propeller is arranged on a motor shaft extending out of the driving motor, and the motor is fixedly arranged on the supporting plate through a motor bracket at the bottom and a screw; the invention cancels the undercarriage structure, separates the battery components from the main machine, has good heat dispersion performance, can open each battery component when landing, utilizes the battery components as the buffer landing of the whole aircraft, has higher safety performance, and reasonably sets the positions of the battery components.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle.
Background
An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer.
The structure of the existing unmanned aerial vehicle is single, the unmanned aerial vehicle generally comprises an integrated host, a propeller is arranged at the top of the host, an undercarriage is arranged at the bottom of the host, the undercarriage is used for flying, a battery assembly is arranged in the host, when flying, the heat of a battery can be transferred to the host of the unmanned aerial vehicle, so that the internal heat is improved, the heat dissipation performance is poor, the overheating condition is easy to occur, the normal flight is influenced, the host of the unmanned aerial vehicle becomes larger due to the mode of internally arranging the battery, the number of the batteries used by the host is not large, the endurance capacity is also poor, and the problem of position arrangement of a lithium battery of the unmanned aerial vehicle is an important solution;
in addition, owing to set up the undercarriage, unmanned aerial vehicle's the decline of rising and falling all supports through the undercarriage, and unmanned aerial vehicle itself does not have the function of buffering speed reduction, leads to the undercarriage damage often to appear, so caused economic loss for the user, and the undercarriage after the damage often can not play the effect of speed reduction protection, does not bring any effect for descending, installs only can increase weight on the host computer.
Disclosure of Invention
The invention aims to solve the technical problems that the number of batteries is increased, the batteries are arranged externally, and the positions of the batteries are arranged at the positions of landing gears of the unmanned aerial vehicle, so that the problem of landing buffering of the unmanned aerial vehicle can be solved, the problem of installation of lithium batteries can be solved, the external lithium batteries not only solve the problem of space occupation of a host, but also solve the problem that heat of the internal lithium batteries cannot be well dissipated, and various defects in the prior art can be well solved.
The invention is realized by the following technical scheme: an unmanned aerial vehicle comprises an unmanned aerial vehicle remotely controlled by a remote controller, wherein the unmanned aerial vehicle comprises a host, a battery assembly is arranged at the bottom of the host in an opening-closing mode, a propeller is arranged at the top of the host, a control main board and a driving motor are arranged inside the host, the driving motor is arranged on a supporting plate inside the host, the power input end of the control main board supplies power through the battery assembly, the driving motor is controlled and supplied power through the control main board, the propeller is arranged on a motor shaft extending out of the driving motor, the motor is fixedly arranged on the supporting plate through a motor bracket at the bottom and a screw, an aerial camera is arranged on the outer end face of the host, a wireless transceiving module is arranged on the control main board, and the wireless transceiving module is;
the bottom of host computer sets up a fixed chamber, and the electro-magnet subassembly is packed into to fixed intracavity, and the electro-magnet subassembly part passes fixed chamber and stretches into inside the host computer, and the pad on the positive negative wiring connection control mainboard of electro-magnet subassembly to through the control mainboard control break-make electricity, battery pack are provided with more than one, and it articulates the bottom at the host computer respectively, and battery pack forms a circular choking ring after opening.
As the preferred technical scheme, the bottom of the main machine corresponds to each group of battery packs and is provided with two connecting lugs, a rotating cavity is formed between the connecting lugs, a first pin shaft hole is formed in each connecting lug, a rotating lug is arranged at the top of each battery pack, a second pin shaft hole is formed in each rotating lug, each rotating lug is arranged in each rotating cavity, a rotating pin is arranged by penetrating through the corresponding second pin shaft hole, a torsion spring is sleeved in the middle of each rotating pin, each rotating pin extends towards the outside of each rotating lug and carries a torsion spring to be fixedly arranged in the corresponding first pin shaft hole in each connecting lug, and each battery pack is parallel to the horizontal plane under the action of the torsion spring.
As the preferred technical scheme, each group of battery components comprises a battery shell and a lithium battery embedded in the battery shell, the outer side surface of the battery shell is an arc-shaped convex surface, the inner side of the battery shell is an arc-shaped concave surface, a wire outlet hole is formed in the top of the battery shell, a wire inlet hole is formed in the host machine right opposite to the wire outlet hole, and positive and negative connection wires of the lithium battery respectively penetrate through the wire outlet hole and the wire inlet hole to be connected with a power input interface of the internal control mainboard.
As the preferred technical scheme, a static magnet piece is fixedly bonded in an arc-shaped concave surface of the battery shell, and the static magnet piece is an arc-shaped concave surface opposite to one side of the electromagnet assembly and is assembled and attracted with the electromagnet assembly with a cylindrical structure.
According to the preferable technical scheme, the electromagnet assembly comprises a metal rod, a coil is wound on the metal rod, a positive electrode wire and a negative electrode wire of the coil are connected with the control main board, a spring is bonded at the bottom of the metal rod, and a flexible silica gel pad is bonded and fixed at the bottom of the spring.
As a preferred technical scheme, adjacent battery components are arranged around the electromagnet component in the middle to form a columnar structure, the static magnet pieces on the battery components are attracted with the electromagnet component, and a clearance cavity is formed between the battery shells of the battery components.
As the preferred technical scheme, a flow blocking layer is arranged between every two adjacent battery shells, the two sides of the flow blocking layer are respectively bonded and fixed with the outer wall surface of each battery shell through strong glue, or fixing grooves are formed in the battery shells, and the two sides of the flow blocking layer are respectively inserted into the fixing grooves and then are fixed through glue.
As a preferred technical scheme, the current blocking layers are all elastic rubber layers, and when the static magnet pieces on the battery shell are attracted with the electromagnet assemblies, the current blocking layers are compressed in a gap cavity formed between the battery shells.
The invention has the beneficial effects that: the battery assembly is arranged at the bottom of the host machine, so that the mounting position of the battery is solved, the internal space of the host machine is not occupied, heat is not transferred to the inside of the host machine, and the external structure has better heat dissipation performance;
when the unmanned aerial vehicle lands, each battery assembly can be scattered to form a circular buffer structure, so that the unmanned aerial vehicle has very high buffer capacity and the safety during landing is improved;
utilize the spring of electromagnet assembly bottom to play the purpose of descending buffering, utilize the electromagnet to realize the purpose of shock attenuation buffering, saved the setting of undercarriage, simplify overall structure.
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 view of the overall structure of the present invention;
FIG. 2 is a bottom view of the present invention;
FIG. 3 is a diagram of the internal structure of the host according to the present invention;
fig. 4 is a perspective view of a battery module according to the present invention;
FIG. 5 is a schematic diagram of the construction of the electromagnet assembly of the present invention;
fig. 6 is a schematic structural view of each battery module according to the present invention after being unfolded.
Detailed Description
As shown in figure 1 of the drawings, in which, as shown in fig. 2 and 3, the unmanned aerial vehicle includes an unmanned aerial vehicle remotely controlled by a remote controller, the unmanned aerial vehicle includes a host 2, a battery assembly is mounted at the bottom of the host 2 in an opening and closing manner, a propeller 3 is disposed at the top of the host, a control mainboard 21 and a driving motor 18 are disposed inside the host 2, the driving motor 18 is mounted on a support plate 22 inside the host 2, a power input end of the control mainboard 21 is powered by the battery assembly, the driving motor 18 is controlled and powered by the control mainboard 21, the propeller 3 is mounted on a motor shaft extending out of the driving motor 18, the motor is fixedly mounted on a screw hole position of the support plate 22 through a motor bracket at the bottom and a screw, an aerial camera 51 is disposed on an outer end face of the host 2, and a wireless transceiver module is disposed on the control mainboard and is matched with the remote;
the bottom of host computer 2 sets up a fixed chamber, and electromagnet assembly 100 is packed into to fixed intracavity, and electromagnet assembly 100 part passes fixed chamber and stretches into inside host computer 2, and electromagnet assembly's positive negative pole wiring connection control mainboard on the pad to through the control mainboard 21 control break-make electricity, battery pack are provided with more than one, and it articulates respectively in the bottom of host computer 2, and battery pack forms a circular choking ring after opening.
Wherein, the bottom of the main frame is provided with two connecting lugs 4 corresponding to each group of battery components, a rotating cavity is formed between the connecting lugs 4, the connecting lugs are all provided with a first pin shaft hole 41, the top of the battery component is provided with a rotating lug 12, the rotating lug 12 is provided with a second pin shaft hole 11, the rotating lug 12 is respectively arranged in the rotating cavity, a rotating pin 1 is arranged by penetrating through the second pin shaft hole 11, a torsion spring is sleeved in the middle of the rotating pin 1, the rotating pin 1 extends towards the outside of the rotating lug and carries the torsion spring to be fixedly arranged in the first pin shaft hole 41 on the connecting lug, the battery component is parallel to the horizontal plane under the action of the torsion spring, thus when the electromagnet component is de-energized, the battery component can be separated from the battery component, the battery component is unfolded under the action of the torsion spring, as shown in fig. 6, under the state, the unfolded structure can be used as the air flow buffer when the unmanned aerial vehicle descends, the descending speed of the unmanned aerial vehicle is rapidly reduced.
As shown in fig. 4, each battery pack includes a battery case 6 and a lithium battery (not shown) embedded in the battery case 6, the outer side surface of the battery case is an arc-shaped convex surface, the inner surface is an arc-shaped concave surface, a wire outlet 9 is arranged at the top of the battery case, a wire inlet hole 19 is formed in the host computer just opposite to the wire outlet, the positive and negative connection wires of the lithium battery respectively penetrate through the wire outlet and the wire inlet hole to be connected with a power input interface of the internal control mainboard, and the sealing rings are all plugged in the wire inlet and outlet holes to seal the wire inlet and outlet.
A static magnet piece 8 is fixedly bonded in the arc concave surface of the battery shell, and the arc concave surface is arranged on one side of the static magnet piece 8 opposite to the electromagnet assembly and is assembled and attracted with the electromagnet assembly of the cylindrical structure.
Because a plurality of battery packs are arranged, the flight endurance is very good, and because each battery pack is exposed in the flight process, the battery packs are quickly cooled by external air flow.
As shown in fig. 5, the electromagnet assembly includes a metal rod, a coil 5 is wound on the metal rod, the positive and negative electrode lines of the coil 5 are connected to the control main board, a spring 13 is bonded to the bottom of the metal rod, and a flexible silica gel pad 14 is bonded and fixed to the bottom of the spring 13.
The adjacent battery components are arranged around the electromagnet component in the middle to form a columnar structure, the static magnet pieces 8 on the battery components are attracted with the electromagnet component, and a clearance cavity 17 is formed between the battery shells of the battery components, as shown in figure 1, the structure is simple in integral structure and regular in shape during flying, and the flying resistance can be greatly reduced.
All set up a choking layer 7 between the adjacent battery case, the both sides of choking layer 7 are fixed with battery case's outer wall through the bonding of powerful glue respectively, or set up the fixed slot on battery case, insert the both sides of choking layer respectively in the fixed slot in glue is fixed again, the choking layer is all adopted elastic rubber layer, when the static magnet piece on battery case is inhaled with electromagnet assembly, the choking layer compresses the clearance intracavity that forms between battery case, after each battery module expandes, as shown in figure 5, all choking layers are opened this moment, form a circular shape resistance net, cushion for unmanned aerial vehicle, increase the area of contact with the air, all operations above all are all through remote controller remote control, and is simple and convenient.
In addition, the spring and the silica gel pad at the bottom of the electromagnet assembly slightly protrude out of the lower end face of the battery assembly when the battery assembly is not unfolded, so that the electromagnet assembly can land stably without opening each battery assembly and is supported by the extending spring and the silica gel pad in a grounding mode at some times if the climate is good. In this case, in order to increase safety, a silica gel layer can be adhered to the bottom of the battery shell to assist in supporting the battery shell on the ground.
The invention has the beneficial effects that: the battery assembly is arranged at the bottom of the host machine, so that the mounting position of the battery is solved, the internal space of the host machine is not occupied, heat is not transferred to the inside of the host machine, and the external structure has better heat dissipation performance;
when the unmanned aerial vehicle lands, each battery assembly can be scattered to form a circular buffer structure, so that the unmanned aerial vehicle has very high buffer capacity and the safety during landing is improved;
utilize the spring of electromagnet assembly bottom to play the purpose of descending buffering, utilize the electromagnet to realize the purpose of shock attenuation buffering, saved the setting of undercarriage, simplify overall structure.
The above description is only an embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that are not thought of through the inventive work should be included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope defined by the claims.
Claims (7)
1. An unmanned vehicles, includes the unmanned vehicles through remote control of remote controller, its characterized in that: the unmanned aerial vehicle comprises a host, a battery assembly is arranged at the bottom of the host in an opening-closing manner, a propeller is arranged at the top of the host, a control main board and a driving motor are arranged inside the host, the driving motor is arranged on a supporting board inside the host, the power input end of the control main board supplies power through the battery assembly, the driving motor is controlled and supplied with power through the control main board, the propeller is arranged on a motor shaft extending out of the driving motor, the motor is fixedly arranged on the supporting board through a motor bracket at the bottom and a screw, an aerial photography camera is arranged on the end face of the outer side of the host, a wireless receiving and sending module is arranged on the control main board;
the bottom of the host is provided with a fixed cavity, an electromagnet assembly is arranged in the fixed cavity, part of the electromagnet assembly penetrates through the fixed cavity and extends into the host, positive and negative connecting wires of the electromagnet assembly are connected with a bonding pad on the control mainboard and are controlled to be switched on and off through the control mainboard, more than one battery assembly is arranged and is respectively hinged to the bottom of the host, and the battery assembly forms a circular choking ring after being opened;
every group battery pack all includes a battery case and imbeds the lithium cell that sets up in battery case, all sets up a choking layer between the adjacent battery case, the both sides on choking layer are fixed through the bonding of powerful glue with battery case's outer wall respectively, perhaps set up the fixed slot on battery case, insert the both sides on choking layer respectively in the fixed slot beat glue again fixedly.
2. The unmanned aerial vehicle of claim 1, wherein: the bottom of host computer corresponds every group battery pack and all is provided with two engaging lugs, forms a rotation chamber between the engaging lug, all sets up a first round pin shaft hole on the engaging lug, battery pack's top all is provided with one and rotates the ear, rotates and has all seted up second round pin shaft hole on the ear, rotates the ear and packs into respectively in rotating the intracavity, passes second round pin shaft hole and sets up a rotation round pin, all suits a torsion spring in the middle of the rotation round pin, and the rotation round pin is towards rotating the outside extension of ear and carrying torsion spring and fixed packing into in the first round pin shaft hole on the engaging lug, and battery pack is its parallel to the horizontal plane under torsion spring's effect.
3. The unmanned aerial vehicle of claim 2, wherein: the lateral surface of battery case is an arc convex surface, and the inner face is an arc concave surface, and battery case's top is provided with the wire hole, has just seted up the entrance hole on the host computer of wire hole, and the positive negative pole wiring of lithium cell passes the wire hole and the power input interface of entrance hole connection internal control mainboard respectively.
4. The unmanned aerial vehicle of claim 3, wherein: a static magnet sheet is fixedly bonded in the arc concave surface of the battery shell, and the arc concave surface is arranged on one side of the static magnet sheet opposite to the electromagnet assembly and is assembled and attracted with the electromagnet assembly with a cylindrical structure.
5. The unmanned aerial vehicle of claim 1, wherein: the electromagnet assembly comprises a metal rod, a winding coil is wound on the metal rod, a positive electrode wire and a negative electrode wire of the winding coil are connected with the control main board, a spring is bonded at the bottom of the metal rod, and a flexible silica gel pad is bonded and fixed at the bottom of the spring.
6. The unmanned aerial vehicle of claim 4, wherein: the adjacent battery components are arranged around the electromagnet component in the middle to form a columnar structure, the static magnet pieces on the battery components are attracted with the electromagnet component, and a clearance cavity is formed between the battery shells of the battery components.
7. The unmanned aerial vehicle of claim 6, wherein: the current blocking layer is an elastic rubber layer, and when the static magnet piece on the battery shell is attracted with the electromagnet assembly, the current blocking layer is compressed in a gap cavity formed between the battery shells.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910410033.6A CN110077579B (en) | 2019-05-16 | 2019-05-16 | Unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910410033.6A CN110077579B (en) | 2019-05-16 | 2019-05-16 | Unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN110077579A CN110077579A (en) | 2019-08-02 |
| CN110077579B true CN110077579B (en) | 2020-11-06 |
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| CN201910410033.6A Active CN110077579B (en) | 2019-05-16 | 2019-05-16 | Unmanned aerial vehicle |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205396522U (en) * | 2015-12-29 | 2016-07-27 | 天津中科昊宇科技有限公司 | Unmanned aerial vehicle |
| CN106410086A (en) * | 2016-11-16 | 2017-02-15 | 上海未来伙伴机器人有限公司 | Heat dissipation device for battery of aircraft |
| CN107719625A (en) * | 2017-11-06 | 2018-02-23 | 郑州航空港飘天下物联网科技有限公司 | Helium flight rod |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9845165B2 (en) * | 2014-07-16 | 2017-12-19 | Airogistic, L.L.C. | Methods and apparatus for unmanned aerial vehicle landing and launch |
| KR101858619B1 (en) * | 2016-08-24 | 2018-05-17 | 한국과학기술원 | Three-phase AC power wirelessly-chargable unmanned aerial vehicle and three-phase AC power wirelessly-charging apparatus for the same |
-
2019
- 2019-05-16 CN CN201910410033.6A patent/CN110077579B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205396522U (en) * | 2015-12-29 | 2016-07-27 | 天津中科昊宇科技有限公司 | Unmanned aerial vehicle |
| CN106410086A (en) * | 2016-11-16 | 2017-02-15 | 上海未来伙伴机器人有限公司 | Heat dissipation device for battery of aircraft |
| CN107719625A (en) * | 2017-11-06 | 2018-02-23 | 郑州航空港飘天下物联网科技有限公司 | Helium flight rod |
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| CN110077579A (en) | 2019-08-02 |
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