CN110667863A - Unmanned aerial vehicle driving system capable of being separated step by step - Google Patents
Unmanned aerial vehicle driving system capable of being separated step by step Download PDFInfo
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- CN110667863A CN110667863A CN201911096208.7A CN201911096208A CN110667863A CN 110667863 A CN110667863 A CN 110667863A CN 201911096208 A CN201911096208 A CN 201911096208A CN 110667863 A CN110667863 A CN 110667863A
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- unmanned aerial
- aerial vehicle
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- 238000004146 energy storage Methods 0.000 claims abstract description 70
- 239000000178 monomer Substances 0.000 claims abstract description 47
- 239000002184 metal Substances 0.000 claims description 9
- 239000000945 filler Substances 0.000 claims description 6
- 230000005611 electricity Effects 0.000 claims description 3
- 230000002035 prolonged effect Effects 0.000 abstract 1
- 238000000926 separation method Methods 0.000 description 4
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000012272 crop production Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 229940079593 drug Drugs 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229920000728 polyester Polymers 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
- B64D1/12—Releasing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
- G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/42—Determining position
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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
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention provides an unmanned aerial vehicle power system capable of being separated step by step, and belongs to the technical field of unmanned aerial vehicles. Unmanned aerial vehicle includes the unmanned aerial vehicle organism, the top of unmanned aerial vehicle organism is equipped with the remote signal antenna, the bottom of unmanned aerial vehicle organism is equipped with the undercarriage, unmanned aerial vehicle driving system is including the multistage energy source of locating unmanned aerial vehicle organism bottom, multistage energy source is by a plurality of energy storage monomers by supreme connection gradually down and constitutes, when multistage energy source is the unmanned aerial vehicle power supply, every energy storage monomer supplies power in proper order, when the free energy of energy storage is exhausted, the energy storage monomer that this energy was exhausted breaks away from with the unmanned aerial vehicle organism. Each energy storage monomer is provided with a GPS (global positioning system), so that the separated landing place can be accurately found and reused; the adjacent energy storage monomers are connected through electromagnetic attraction, when the energy storage monomers are exhausted, the electromagnetic attraction device is disconnected, the energy storage monomers exhausted by electric quantity are separated, the weight of the airplane body is reduced, and the flight time is prolonged.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle power system capable of prolonging endurance flight time and realizing step-by-step separation.
Background
An Unmanned Aerial Vehicle (UAV) is a device in rapid development, and has the advantages of flexibility, quick response, unmanned flight and low operation requirement. Unmanned aerial vehicle can realize functions such as image real-time transmission, high-risk area detection through carrying on multiclass sensor. At present, the application range of unmanned aerial vehicles has been expanded to three fields of military affairs, scientific research and civil use, and the unmanned aerial vehicles are particularly widely applied in the fields of electric power, communication, weather, agriculture, oceans, exploration, photography, disaster prevention and reduction, crop production estimation, drug control and smuggling, border patrol, public security and counter terrorism, and especially are prevalent in aerial photography at present.
The unmanned aerial vehicle mainly comprises a body, a power system and some functional equipment (such as aerial photography equipment and the like). However, the existing unmanned aerial vehicle mostly adopts an energy storage battery as a power source, the mass of the energy storage battery is too large, and the energy storage battery with exhausted electric quantity still can cause burden to the unmanned aerial vehicle in flying, so that the endurance flight time is reduced.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle power system capable of reducing the load pressure of an unmanned aerial vehicle to the maximum extent and increasing the endurance flight time and capable of realizing gradual separation, so as to solve at least one technical problem in the background technology.
In order to achieve the purpose, the invention adopts the following technical scheme:
the unmanned aerial vehicle comprises an unmanned aerial vehicle body, the two sides of the unmanned aerial vehicle body are provided with arms, unmanned aerial vehicle rotating blades are arranged on the arms, the top of the unmanned aerial vehicle body is provided with a remote signal antenna, the bottom of the unmanned aerial vehicle body is provided with a landing gear, the unmanned aerial vehicle power system comprises a multistage energy source arranged at the bottom of the unmanned aerial vehicle body, the multistage energy source is formed by sequentially connecting a plurality of energy storage monomers from bottom to top, when the multistage energy source supplies power to the unmanned aerial vehicle, each energy storage monomer supplies power in sequence, and when the energy of the energy storage monomers is exhausted, the energy-exhausted energy storage monomers are separated from the unmanned aerial vehicle body.
Preferably, adjacent energy storage monomers are connected through a first electromagnetic attraction device, each energy storage monomer is connected with a voltage sensor, the voltage sensors are connected with a control circuit board, and the control circuit board is connected with the first electromagnetic attraction device through a proximity switch; the lower part of unmanned aerial vehicle organism stretches out there is unmanned aerial vehicle supply circuit, each the energy storage monomer all is connected with affiliated unmanned aerial vehicle supply circuit.
Preferably, the energy storage monomer includes the shell, be equipped with the battery in the shell, the outside of shell is equipped with first electromagnetic attraction device, the outside of shell one end is equipped with the metal contact, the battery with the metal contact electricity is connected, the metal contact with unmanned aerial vehicle supply circuit contacts and connects.
Preferably, the housing is filled with a shock-absorbing filler.
Preferably, the other end of the shell is provided with a parachute device.
Preferably, the parachute device includes the holding shell, and the holding shell has the ejection core in, launches and is equipped with the parachute on the core, the lower extreme of ejection core passes through the bottom that second electromagnetic attraction device connects the holding shell, the holding shell the bottom with be equipped with the spring between the ejection core, second electromagnetic attraction device passes through proximity switch and connects control circuit board.
Preferably, each energy storage monomer is provided with a GPS positioning system.
Preferably, the control circuit board is a PLC control circuit board.
Preferably, the first electromagnetic attraction device and the second electromagnetic attraction device are both electromagnets.
Preferably, the number of the energy storage monomers is 3.
The invention has the beneficial effects that: the device is characterized in that an energy storage system is mounted at the lower part of the unmanned aerial vehicle, the energy storage system is divided into a plurality of energy storage monomers, and when the energy storage electric quantity of each stage is used up, the system automatically separates the energy storage part with the electric quantity exhausted from the energy storage system; each energy storage monomer is provided with a GPS (global positioning system), so that the separated landing place can be accurately found according to the system positioning of the background, and the reutilization is realized; the adjacent energy storage single bodies are connected through electromagnetic attraction, the conductive part is an electromagnetic clutch, when the energy storage unit of each stage is in no power, the attraction device is disconnected, the no-power unit falls and separates, a damping filler is arranged in each unit, a parachute opening device is arranged at one end of each unit, and after the power is cut off, the energy storage single bodies are separated, and the parachutes are opened; after the unmanned aerial vehicle energy storage does not divide the electric quantity to use up, automatic and unmanned aerial vehicle organism separation, the whole quality of fuselage reduces, has increased flight time.
Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a schematic view of an installation structure of a gradually separable unmanned aerial vehicle power system on an unmanned aerial vehicle body according to an embodiment of the present invention.
Fig. 2 is a structural diagram of an unmanned aerial vehicle power system capable of being separated step by step according to an embodiment of the invention.
Fig. 3 is a structural view of a parachute apparatus according to an embodiment of the present invention.
Wherein: 1-unmanned aerial vehicle body; 2-a machine arm; 3-rotating the paddle; 4-a remote signal antenna; 5-a landing gear; 6-a multi-stage energy source; 7-energy storage monomers; 8-a first electromagnetic attraction device; 9-a power supply circuit; 10-a housing; 11-a storage battery; 12-a shock-absorbing filler; 13-a parachute assembly; 14-a containment shell; 15-parachute; 16-a second electromagnetic attraction device; 17-a spring; 18-GPS positioning system; 20-a ballistic core; 21-control circuit board.
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 by way of the drawings are illustrative only and are not to be construed as limiting the invention.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.
In the description of this patent, it is to be understood that the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings for the convenience of describing the patent and for the simplicity of description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the patent.
In the description of this patent, it is noted that unless otherwise specifically stated or limited, the terms "mounted," "connected," and "disposed" are to be construed broadly and can include, for example, fixedly connected, disposed, detachably connected, disposed, or integrally connected and disposed. The specific meaning of the above terms in this patent may be understood by those of ordinary skill in the art as appropriate.
For the purpose of facilitating an understanding of the present invention, the present invention will be further explained by way of specific embodiments with reference to the accompanying drawings, which are not intended to limit the present invention.
It should be understood by those skilled in the art that the drawings are merely schematic representations of embodiments and that the elements shown in the drawings are not necessarily required to practice the invention.
Examples
As shown in fig. 1 to 3, an embodiment of the invention provides an unmanned aerial vehicle power system capable of being separated step by step, the unmanned aerial vehicle includes an unmanned aerial vehicle body 1, two sides of the unmanned aerial vehicle body 1 are provided with booms 2, the booms 2 are provided with unmanned aerial vehicle rotating blades 3, the top of the unmanned aerial vehicle body 1 is provided with a remote signal antenna 4, the bottom of the unmanned aerial vehicle body 1 is provided with an undercarriage 5, the unmanned aerial vehicle power system includes a multistage energy source 6 arranged at the bottom of the unmanned aerial vehicle body 1, the multistage energy source 6 is formed by sequentially connecting a plurality of energy storage monomers 7 from bottom to top, when the unmanned aerial vehicle is powered by the multistage energy source, each energy storage monomer 7 sequentially supplies power, and when the energy storage monomers 7 exhausted by energy are exhausted, the energy storage monomers 7 exhausted by energy are separated from the.
The adjacent energy storage single bodies 7 are connected through a first electromagnetic attraction device 8, each energy storage single body 7 is connected with a voltage sensor, the voltage sensors are connected with a control circuit board, and the control circuit board is connected with the first electromagnetic attraction device 8 through a proximity switch; unmanned aerial vehicle organism 1's lower part is stretched out and is had unmanned aerial vehicle supply circuit 9, each energy storage monomer 7 all is connected with affiliated unmanned aerial vehicle supply circuit 9.
Energy storage monomer 7 includes shell 10, be equipped with battery 11 in the shell 10, the outside of shell 10 is equipped with first electromagnetic attraction device 8, the outside of shell 10 one end is equipped with the metal contact, battery 11 with the metal contact electricity is connected, the metal contact with the contact of unmanned aerial vehicle supply circuit 9 is connected.
The housing 10 is filled with a shock-absorbing filler 12, such as sponge, polyester fiber, etc
The other end of the housing is provided with a parachute device 13.
Each energy storage unit 7 is provided with a GPS positioning system 18.
The control circuit board is a PLC control circuit board.
The first electromagnetic attraction device and the second electromagnetic attraction device are electromagnets.
The number of the energy storage monomers is 3.
In practical use, the number of the energy storage monomers is not limited to the above 3, and those skilled in the art can specifically set the number of the energy storage monomers according to practical situations.
In summary, in the unmanned aerial vehicle power system capable of being separated step by step according to the embodiment of the present invention, the energy storage system is mounted on the lower portion of the unmanned aerial vehicle, the system is divided into three stages, when the energy storage capacity of each stage is used up, the voltage sensor detects that the voltage signal of the energy storage monomer is transmitted to the control circuit board 21, the control circuit board 21 detects that the voltage of the energy storage monomer is used up or is smaller than the preset threshold, the proximity switch connected to the energy storage monomer with the used up voltage is controlled to disconnect the first electromagnetic attraction device of the energy storage monomer, and after the first electromagnetic attraction device is powered off, the energy storage monomer with the used up voltage automatically falls off and is separated from the. Each energy storage unit is provided with a protective cover (namely a shell) outside and a shock absorption filler inside, so that the energy storage battery can be protected from being damaged after falling to the ground. The second electromagnetic suction device of the separated parachute device of the energy storage monomer is powered off to pop up the parachute; each level of energy storage monomer is provided with a GPS, and the separated landing place can be accurately found according to the system positioning of the background, so that the energy storage monomer can be recycled. Unmanned aerial vehicle self has the energy storage part, and the effect does: after the three-level energy storage part of the mounting is used up, the unmanned aerial vehicle is guaranteed to have enough electric quantity to return to the home. After the unmanned aerial vehicle energy storage does not divide the electric quantity to use up, automatic and unmanned aerial vehicle organism separation, the whole quality of fuselage reduces like this, has increased flight time.
Those of ordinary skill in the art will understand that: the components in the device in the embodiment of the present invention may be distributed in the device in the embodiment according to the description of the embodiment, or may be correspondingly changed in one or more devices different from the embodiment. The components of the above embodiments may be combined into one component, or may be further divided into a plurality of sub-components.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a can separate unmanned aerial vehicle driving system step by step, unmanned aerial vehicle includes unmanned aerial vehicle organism (1), the both sides of unmanned aerial vehicle organism (1) are equipped with horn (2), be equipped with unmanned aerial vehicle rotating paddle (3) on horn (2), the top of unmanned aerial vehicle organism (1) is equipped with remote signal antenna (4), the bottom of unmanned aerial vehicle organism (1) is equipped with undercarriage (5), its characterized in that: unmanned aerial vehicle driving system is including locating multistage energy source (6) of unmanned aerial vehicle organism (1) bottom, multistage energy source (6) are connected gradually by a plurality of energy storage monomers (7) from lower supreme and are constituteed, and when multistage energy source was the unmanned aerial vehicle power supply, every energy storage monomer (7) supplied power in proper order, and when the energy of energy storage monomer (7) was exhausted, this energy storage monomer (7) that exhausts broke away from with unmanned aerial vehicle organism (1).
2. The stage-by-stage separable unmanned aerial vehicle power system of claim 1, wherein: the adjacent energy storage monomers (7) are connected through a first electromagnetic attraction device (8), each energy storage monomer (7) is connected with a voltage sensor, the voltage sensors are connected with a control circuit board (21), and the control circuit board (21) is connected with the first electromagnetic attraction device (8) through a proximity switch; the lower part of unmanned aerial vehicle organism (1) stretches out unmanned aerial vehicle supply circuit (9), each energy storage monomer (7) all are connected with affiliated unmanned aerial vehicle supply circuit (9).
3. The stage-by-stage separable unmanned aerial vehicle power system of claim 2, wherein: energy storage monomer (7) include shell (10), be equipped with battery (11) in shell (10), the outside of shell (10) is equipped with first electromagnetic attraction device (8), the outside of shell (10) one end is equipped with the metal contact, battery (11) through control circuit board (21) with the metal contact electricity is connected, the metal contact with unmanned aerial vehicle supply circuit (9) contact is connected.
4. The stage-by-stage separable unmanned aerial vehicle power system of claim 3, wherein: the shell (10) is filled with shock-absorbing filler (12).
5. The stage-by-stage separable unmanned aerial vehicle power system of claim 4, wherein: and a parachute device (13) is arranged at the other end of the shell.
6. The stage-by-stage separable unmanned aerial vehicle power system of claim 5, wherein: parachute device (13) are including holding shell (14), hold shell (14) and have shot core (20) in the holding, are equipped with parachute (15) on shooting core (20), the lower extreme of shooting core (20) passes through the bottom that second electromagnetism actuation device (16) are connected and hold the shell, hold the bottom of shell with be equipped with spring (17) between shooting core (20), second electromagnetism actuation device (16) are connected through proximity switch control circuit board.
7. The stage-by-stage separable unmanned aerial vehicle power system of claim 6, wherein: each energy storage monomer (7) is provided with a GPS (global positioning system) positioning system (18).
8. The stage-by-stage separable unmanned aerial vehicle power system of claim 7, wherein: the control circuit board (21) is a PLC control circuit board.
9. The stage-by-stage separable unmanned aerial vehicle power system of claim 8, wherein: the first electromagnetic attraction device and the second electromagnetic attraction device are electromagnets.
10. A progressively separable unmanned aerial vehicle power system as claimed in any one of claims 1 to 9, wherein: the number of the energy storage monomers is 3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911096208.7A CN110667863A (en) | 2019-11-11 | 2019-11-11 | Unmanned aerial vehicle driving system capable of being separated step by step |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911096208.7A CN110667863A (en) | 2019-11-11 | 2019-11-11 | Unmanned aerial vehicle driving system capable of being separated step by step |
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| CN110667863A true CN110667863A (en) | 2020-01-10 |
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| CN201911096208.7A Pending CN110667863A (en) | 2019-11-11 | 2019-11-11 | Unmanned aerial vehicle driving system capable of being separated step by step |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114802730A (en) * | 2022-05-09 | 2022-07-29 | 歌尔科技有限公司 | Unmanned aerial vehicle and system |
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| US20190061937A1 (en) * | 2017-08-28 | 2019-02-28 | Airbus Operations Gmbh | Coupling device for coupling modules with each other, aircraft comprising the coupling device, method for the coupling and decoupling of modules |
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