CN110212129A - Unmanned plane battery fastening structure and unmanned plane - Google Patents
Unmanned plane battery fastening structure and unmanned plane Download PDFInfo
- Publication number
- CN110212129A CN110212129A CN201910470885.4A CN201910470885A CN110212129A CN 110212129 A CN110212129 A CN 110212129A CN 201910470885 A CN201910470885 A CN 201910470885A CN 110212129 A CN110212129 A CN 110212129A
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- fixed body
- unmanned plane
- mounting rack
- hole
- fastening structure
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 33
- 239000007787 solid Substances 0.000 claims description 8
- 230000009471 action Effects 0.000 claims description 2
- 229940101303 bodyglide Drugs 0.000 claims description 2
- 238000009434 installation Methods 0.000 description 5
- 230000000875 corresponding effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000007689 inspection Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 206010039203 Road traffic accident Diseases 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L53/00—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles
- B60L53/80—Exchanging energy storage elements, e.g. removable batteries
-
- 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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- 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
-
- 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
- H01M50/50—Current conducting connections for cells or batteries
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L2200/00—Type of vehicles
- B60L2200/10—Air crafts
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M2220/00—Batteries for particular applications
- H01M2220/20—Batteries in motive systems, e.g. vehicle, ship, plane
-
- 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
-
- 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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/70—Energy storage systems for electromobility, e.g. batteries
-
- 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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Power Engineering (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Battery Mounting, Suspending (AREA)
Abstract
The invention discloses a kind of unmanned plane battery fastening structure and unmanned planes, are related to aviation aircraft technical field, and main purpose is so that the battery disassembly and assembly of unmanned plane is easy to operate, to improve the disassembly efficiency of battery.Main technical schemes of the invention are as follows: the unmanned plane battery fastening structure includes mounting rack；Fixed body, the fixed body are slidably connected in the mounting rack, and chamfered shape is provided in the fixed body and is adapted with the chamfered shape of the battery, and multiple accommodating chambers for accommodating multiple batteries；Driving portion, the output end of the driving portion are detachably connected with the fixed body, and the driving portion is used to be electrically connected with the flight control system of the unmanned plane, and the fixed body can be driven to slide in or out the mounting rack under the control of the flight control system.Present invention is mainly used for the disassembly efficiencies for improving unmanned machine battery.
Description
Technical field
The present invention relates to aviation aircraft technical fields, in particular to a kind of unmanned plane battery fastening structure and nothing
It is man-machine.
Background technique
Unmanned plane is just increasingly extensive for the application development of various industries, at this stage, unmanned plane have been applied to take photo by plane, agriculture
Woods plant protection, geological prospecting, electric inspection process, oil and gas pipeline inspection, expressway traffic accident management, forest fire protection inspection collection pollution environment
The every field such as prospecting.
Wherein, multi-rotor unmanned aerial vehicle is a kind of inorganic man-machine type for capableing of VTOL, and it is mostly electronic unmanned plane.Mesh
Before, multi-rotor unmanned aerial vehicle is usually powered by multiple batteries, and each battery generallys use magic band or baffle is fixed on
On the mounting rack of fuselage.When needing to charge the battery or replace, usually by operator's craft by each battery from peace
It shelves and removes, at the end of to be charged or replacement, then each battery is fixed on and is installed, inconvenient, the dismounting effect of battery
Rate is lower.
Summary of the invention
In view of this, it is to make that the embodiment of the present invention, which provides a kind of unmanned plane battery fastening structure and unmanned plane, main purpose,
The battery disassembly and assembly for obtaining unmanned plane is easy to operate, to improve the disassembly efficiency of battery.
In order to achieve the above objectives, present invention generally provides following technical solutions:
On the one hand, the embodiment of the invention provides a kind of unmanned plane battery fastening structures, comprising:
Mounting rack；
Fixed body, the fixed body are slidably connected in the mounting rack, be provided in the fixed body chamfered shape with
The chamfered shape of the battery is adapted, and multiple accommodating chambers for accommodating multiple batteries；
Driving portion, the output end of the driving portion are detachably connected with the fixed body, and the driving portion is used for and institute
The flight control system electrical connection of unmanned plane is stated, and the fixed body can be driven to slide in or out under the control of the flight control system
The mounting rack.
Further, the driving portion includes steering engine, rocker arm and push-and-pull connecting rod；
The output shaft of one end of the rocker arm and the steering engine is rotatablely connected；
One end of the push-and-pull connecting rod and the other end of the rocker arm are rotatablely connected, the other end of the push-and-pull connecting rod and institute
Fixed body is stated removably to be rotatablely connected；
The steering engine with the flight control system of the unmanned plane for being electrically connected, under the control of the flight control system,
The fixed body is pushed and pulled by the rocker arm and the push-and-pull connecting rod, so that the fixed body skids off or slide into the mounting rack.
Further, the other end of the rocker arm is provided with multiple the first mounting holes arranged along its length；
One end of the push-and-pull connecting rod is provided with the second mounting hole；
Second mounting hole can be rotatablely connected by shaft and each first mounting hole.
Further,
The other end of the push-and-pull connecting rod is rotatably connected to connecting plate, and third mounting hole is provided on the connecting plate；
It is provided with the 4th mounting hole on the fixed body, is inserted in the third mounting hole and the 4th mounting hole tight
Firmware.
Further, the unmanned plane battery fastening structure further include:
Fixed frame is provided with the first through hole along fixed body glide direction arrangement on the fixed frame；
The steering engine is set in the fixed frame, and the other end of the rocker arm passes through the first through hole and the push-and-pull
One end of connecting rod is rotatablely connected, and the rocker arm is swung in the first through hole.
Further, the unmanned plane battery fastening structure further include:
Locking part, the locking part are set to the mounting rack, and the locking part has lockup state and unlocked state；
When the locking part is in lockup state, the fixed physical efficiency is locked in the mounting rack；
When the locking part is in the unlocked state, the fixed physical efficiency skids off the mounting rack.
Further, the locking part includes:
It is respectively arranged on the mounting rack and the fixed body and opposite the second through-hole and third through-hole；
Connector, the connector are connected to the mounting rack bottom；
Handle, the handle are rotatablely connected by elastic component and the connector；
Positioning pin, one end of the positioning pin and the handle are rotatablely connected, and the other end penetrates second through-hole and institute
State third through-hole；
Wherein, when the handle is pressed, the positioning pin can be retracted in second through-hole, form the locking
The unlocked state in portion；When the handle is released, the handle capable of being resets under the action of the elastic component, and described in drive
Positioning pin resets, and forms the lockup state of the locking part.
Further, charging interface is provided on the fixed body, the charging interface with the battery for being electrically connected.
Further, the first sliding rail is provided on the mounting rack；
The second sliding rail being slidably connected with first sliding rail is provided on the fixed body, the fixed body passes through described
First sliding rail and second sliding rail are slidably connected in the mounting rack.
On the other hand, the embodiment of the present invention also provides a kind of unmanned plane, comprising:
Fuselage, flight control system and unmanned plane battery fastening structure above-mentioned；
The mounting rack and the driving portion are all set in the fuselage；
The driving portion is electrically connected with the flight control system.
By above-mentioned technical proposal, the present invention is at least had the advantages that
Technical solution provided in an embodiment of the present invention, by setting mounting rack and fixed body, and with fixed body with it is removable
Unload the driving portion of connection, and driving portion can be electrically connected with the flight control system of unmanned plane, thus realize when need to battery into
When row charging or replacement, driving portion can drive fixed body to skid off mounting rack under the control of flight control system, then by driving portion with
Fixed body is dismantled, and the integral demounting of all batteries can be realized；It, can be by driving portion and fixation when needing to install battery
Body is attached, and driving portion can drive fixed body to slide into mounting rack, all batteries can be realized under the control of flight control system
Integral installation, it is inconvenient, improve the disassembly efficiency of battery.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of the unmanned plane battery fastening structure provided in an embodiment of the present invention at the first visual angle；
Fig. 2 is a kind of structural schematic diagram of the unmanned plane battery fastening structure provided in an embodiment of the present invention at the second visual angle；
Fig. 3 is the enlarged drawing in Fig. 1 at A；
Fig. 4 is the enlarged drawing in Fig. 2 at B；
Fig. 5 is a kind of structural schematic diagram of unmanned plane provided in an embodiment of the present invention.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with the preferred embodiment of the present invention
In attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or
Similar label indicates same or similar element or element with the same or similar functions.Described embodiment is this hair
Bright a part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to
It is used to explain the present invention, and is not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill
Personnel's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.
The embodiment of the present invention is described in detail with reference to the accompanying drawing.
In the description of the present embodiment, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the present embodiment and simplifies description, rather than indication or suggestion meaning
Device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as to the present embodiment
The limitation of protection scope.
As shown in Figure 1, the embodiment of the invention provides a kind of unmanned plane battery fastening structure, including mounting rack 1；Fixed body
2, which is slidably connected in mounting rack 1, and chamfered shape is provided in fixed body 2 and is adapted with the chamfered shape of battery,
And multiple accommodating chambers 21 for accommodating multiple batteries；Driving portion 3, output end and the fixed body 2 of the driving portion 3 detachably connect
It connects, and driving portion 3 is used to be electrically connected with the flight control system of unmanned plane, and fixed body 2 can be driven sliding under the control of flight control system
Enter or skid off mounting rack 1.
In some instances, which can be adapted for multi-rotor unmanned aerial vehicle, to conveniently realize
The integral disassembly, assembly of battery.Wherein, mounting rack 1 can be the frame body being mainly made of bottom plate and two side plates being connected on bottom plate
Structure can be placed with multiple through-holes on bottom plate and side plate, and the bottom plate and side plate can be made of carbon fibre material, with
Just the heat dissipation of loss of weight and battery.And fixed body 2 can be width rectangular-shape body structure compatible with cell widths, and
The settable demarcation plate in the body structure, multiple accommodating chambers 21 compatible with battery profile can be formed in fixed body 2,
To store multiple batteries, meet the requirement of unmanned plane.Specifically, which can be made of aluminum alloy materials,
Cost can be not only reduced, it is easy to process, moreover, it is also possible to be covered with through-hole on the surface of fixed body 2, can not only play to electricity
The heat spreading function in pond can also mitigate fuselage weight, and unmanned plane is enabled to carry more load or equipment.Driving portion 3 can
To be electrically connected with the flight control system of unmanned plane, it is powered and corresponding actions can be carried out under the control of flight control system.
Unmanned plane battery fastening structure provided in an embodiment of the present invention, by setting mounting rack and fixed body, and with it is solid
The driving portion determining body and being detachably connected, and driving portion can be electrically connected with the flight control system of unmanned plane, be needed to realize and work as
When charging the battery or replacing, driving portion can drive fixed body to skid off mounting rack under the control of flight control system, then
Driving portion and fixed body are dismantled, the integral demounting of all batteries can be realized；When needing to install battery, can will drive
Dynamic portion is attached with fixed body, and driving portion can drive fixed body to slide into mounting rack, Ji Keshi under the control of flight control system
The now integral installation of all batteries, it is inconvenient, improve the disassembly efficiency of battery.
Wherein, the structure type of driving portion 3 can there are many, as long as may be implemented to drive under the control of flight control system solid
Determine body 2 and carries out corresponding actions.
In some instances, referring to Fig. 1 or Fig. 2, driving portion 3 may include steering engine 31, rocker arm 32 and push-and-pull connecting rod 33；It shakes
One end of arm 32 can be rotatablely connected with the output shaft of steering engine 31；The one end for pushing and pulling connecting rod 33 can turn with the other end of rocker arm 32
The other end of dynamic connection, push-and-pull connecting rod 33 can be removably rotatablely connected with fixed body 2；Steering engine 31 is used for winged with unmanned plane
Control system electrical connection, for fixed body 2 being pushed and pulled by rocker arm 32 and push-and-pull connecting rod 33, so that solid under the control of flight control system
Determine body 2 and skids off or slide into mounting rack 1.It is connected by the way that the steering engine 31 for being electrically connected with flight control system is arranged, and by rocker arm 32
Connecting rod 33 is pushed and pulled, enables steering engine 31 under the control of flight control system, fixed body 2 is pushed by rocker arm 32 and push-and-pull connecting rod 33
Mounting rack 1 is skidded off, or fixed body 2 is pulled to slide into mounting rack 1, to realize the fast quick-detach of the entirety of battery, structure is simple, realizes
Reliably.
Since the weight of the battery of different model is typically different, and the endurance of the steering engine 31 of different model also usually not
Together, in order to guarantee that the unmanned plane battery fastening structure can be suitable for a variety of unmanned planes, in some instances, referring to Fig. 1 or figure
2, multiple the first mounting holes 321 arranged along its length can be set in the other end of rocker arm 32；Push and pull the one of connecting rod 33
End is provided with the second mounting hole；Second mounting hole can be rotatablely connected by shaft and each first mounting hole 321.
According to above-described embodiment, multiple first mounting holes 321 are arranged by the other end in rocker arm 32, so that push-and-pull connecting rod
33 can be rotatablely connected by the second mounting hole and shaft and any one first mounting hole 321, so as to adjust push-and-pull connecting rod 33
Link position on rocker arm 32, so that the unmanned plane battery fastening structure can adapt to tearing open for different unmanned machine batteries
Dress, improves the versatility of the unmanned plane battery fastening structure.For example, working as the heavier-weight of battery, and the endurance of steering engine 31
When smaller, push-and-pull connecting rod 33 can pass through the second mounting hole and rotation and the first mounting hole on rocker arm 32 close to 31 end of steering engine
321 rotation connections may make steering engine 31 steadily to push and pull fixed body 2 by rocker arm 32 and push-and-pull connecting rod 33, be better achieved
Battery entirety fast assembling-disassembling.
It should be noted that being removably rotatablely connected mode between push-and-pull connecting rod 33 above-mentioned and fixed body 2 can have
It is a variety of, as long as rotation connection between the two and detachable may be implemented.In some instances, referring to Fig. 3, and figure is combined
1, the other end of the push-and-pull connecting rod 33 can be rotatably connected to connecting plate 34, and third installation can be set on the connecting plate 34
Hole；The 4th mounting hole can be set on fixed body 2, specifically, the 4th mounting hole can be set in the end face of fixed body 2,
Fastener 35 is inserted in the third mounting hole and the 4th mounting hole.
According to above-described embodiment, pass through one connecting plate 34 of rotation connection, and the connecting plate in the other end of push-and-pull connecting rod 33
34 are connect by fastener 35 with fixed body 2, to realize the rotation connection between push-and-pull connecting rod 33 and fixed body 2.Moreover, working as
When removing or installing the fastener 35, connecting plate 34 can be separated or be connected with fixed body 2, so that push-and-pull connecting rod 33 and fixed body
2 separation or connection, to realize the disassembly or connection between push-and-pull connecting rod 33 and fixed body 2, structure is simple, realizes reliable.Tool
Body.The third mounting hole and the 4th mounting hole all can be threaded hole, and the fastener 35 can be butterfly-type bolt, in order to
Operation.
In some instances, referring to Fig. 1 or Fig. 2, which can also include fixed frame 4, this is solid
Determine that the first through hole 41 along 2 glide direction of fixed body arrangement can be set on frame 4；Steering engine 31 can be set in the fixed frame 4
Interior, the other end of rocker arm 32 may pass through first through hole 41 and push and pull one end rotation connection of connecting rod 33, and rocker arm 32 can be first
It is swung in through-hole 41, specifically when implementing, which can be set the fuselage end in unmanned plane.By the way that fixed frame is arranged
4, and steering engine 31 is arranged in the fixed frame 4, not only ensure that the position of steering engine 31 is fixed, to export stable torque, also
The protective effect to steering engine 31 can be played；Moreover, the fixed frame 4 is also provided with first through hole 41, so that rocker arm 32 is in steering engine
31 control lower swing, convenient for operation.Specifically, the structure type of fixed frame 4 can according to the actual situation depending on, do not do herein
It limits.
In some instances, referring to fig. 2, which can also include locking part 5, the locking part 5
It can be set in mounting rack 1, and the locking part 5 has lockup state and unlocked state；When the locking part 5 is in lockup state
When, fixed body 2 can be locked in mounting rack 1；When locking part 5 is in the unlocked state, fixed body 2 can skid off mounting rack 1.Work as installation
When battery, the fixed body 2 for being loaded with battery can be slided to the entrance of mounting rack 1, and it is connect with push-and-pull connecting rod 33, then
Fixed body 2 is pulled in into mounting rack 1 using steering engine 31, rocker arm 32 and push-and-pull connecting rod 33, locking part 5 may make to be in locking at this time
Fixed body 2 is locked in mounting rack 1 by state strongerly to realize, in unmanned plane operation, fixed body 2 will not be sent out
Life falls off and vibrates, and certainly, battery also will not be vibrated or be fallen off in fixed body 2, moreover, unmanned plane will not be because of fixed body
2 shift and influence the center of gravity of unmanned plane；When dismantling battery, locking part 5 can be made in the unlocked state, then utilized
Fixed body 2 is pushed out to the entrance of mounting rack 1 by steering engine 31, rocker arm 32 and push-and-pull connecting rod 33, then by fixed body 2 and pushes and pulls connecting rod 33
Separation, can be realized the disassembly of battery.
It should be noted that the structure type of locking part 5 can there are many, as long as can be realized fixed body 2 securely
It is locked in mounting rack 1 or fixed body 2 is enabled to skid off mounting rack 1.
In some instances, referring to fig. 4, and Fig. 2 is combined, which may include being respectively arranged at mounting rack 1 and consolidating
Determine on body 2 and opposite the second through-hole and third through-hole；Connector 51, the connector 51 can connect in 1 bottom of mounting rack；Hand
Handle 52 can be rotatablely connected by elastic component 53 and connector 51；Positioning pin 54, one end can be rotatablely connected with handle 52, another
End penetrates the second through-hole and the third through-hole.
In some instances, the second through-hole and third through-hole can be set corresponding with the bottom of fixed body 2 in mounting rack 1
Position, moreover, the third through-hole being arranged on fixed body 2 can also be card slot, as long as positioning pin 54 is passing through the of mounting rack 1
It can be plugged in third through-hole or card slot after two through-holes, with locking fixed body 2.Connector 51 can be to be fixed on mounting rack
The connecting plate of 1 bottom, and in order to save space, can the aperture on connecting plate so that the aperture of 54 through-hole of positioning pin penetrates second
Through-hole and third through-hole.And it includes 52 ontology of handle and arc panel connected to it, the company of the two that the structure of handle 52, which can be,
It meets place to be rotatablely connected by a fixing piece and connector 51, the end of arc panel and one end of positioning pin 54 are rotatablely connected；Elasticity
Part 53 can connect between connector 51 and arc panel, and the elastic component 53 can be spring.
According to above-described embodiment, when 52 ontology of handle is pressed, arc panel can overcome the elastic force of elastic component 53 and drive
Positioning pin 54 allows fixed body 2 to skid off mounting rack 1, from being retracted in the second through-hole in third through-hole so as to form lock
The unlocked state of stop 5；When 52 ontology of handle is released, 52 ontology of handle and arc panel are under the elastic force effect of elastic component 53
It resets, so that positioning pin 54 resets under the drive of arc panel, i.e., penetrates in third through-hole herein, by 2 locking of fixed body
In mounting rack 1, so as to form the lockup state of locking part 5, structure is simple, realizes reliable.
In some instances, limit plate 11 can be set in the end of mounting rack 1, to realize when fixed body 2 exists
When sliding into mounting rack 1 under the driving of steering engine 31, end can be abutted against with limit plate 11, i.e., limit plate 11 is played to solid
Determine the effect that body 2 is limited, further such that fixed body 2 is securely fixed in mounting rack 1, further avoids unmanned plane and exist
Flight course influences the center of gravity of unmanned plane because fixed body 2 shifts.
In some instances, referring to Fig. 1, charging interface 22 can be set on fixed body 2, which is used for
It is electrically connected with battery, to realize when needing to charge to battery, the charging interface 22 need to be only electrically connected with power interface, i.e.,
The charging of achievable battery, it is easy to use without carrying out other operations.Specifically, which can be set solid
The end of body 2 is determined, in order to its connection between power interface.
Mounting rack 1 is slid in or out for the ease of fixed body 2, it in some instances, can be on mounting rack 1 referring to Fig. 1
It is provided with the first sliding rail 12；And the second sliding rail being slidably connected with the first sliding rail 12 is set on fixed body 2, so that fixed body
231 can be slid in or out in mounting rack 1 by the first sliding rail 12 and the second sliding rail 23, so that multiple batteries can be integrally
And it is conveniently and efficiently loaded and unloaded on unmanned plane.
Wherein, the structure type of the first sliding rail 12 and the second sliding rail 23 can there are many, as long as may be implemented fixed body 2 with
Being slidably connected between mounting rack 1, in order to guarantee Stable sliding and positioning of the fixed body 2 in mounting rack 1, the first sliding rail
12 quantity can be four, and the four corners of mounting rack 1 can be distributed in along the length direction of mounting rack 1, and similarly, second is sliding
The quantity of rail 23 can be four, and the four corners of fixed body 2 can be distributed in along the length direction of fixed body 2.
In some instances, the second sliding rail 23 can be the sliding slot arranged along 2 length direction of fixed body；And the first sliding rail 12
It can be arranged on mounting rack 1 and to roll along multiple bearings of 1 length direction of mounting rack arrangement, multiple bearing and sliding slot reality
It is now slidably connected, structure is simple, realizes reliable.
In some instances, referring to Fig. 1, which can also include being set to 2 top surface of fixed body
Connecting plate 6；Second sliding rail 23 is set on the connecting plate.By the setting of connecting plate 6, so that the battery fixing structure is installed
To the mounting rack 1 of fuselage, fixed body 2 can have certain interval between the other components of fuselage, to avoid fuselage its
It is interfered between its components and fixed body 2, to guarantee respective work.Wherein, strong in order to mitigate weight and raising
Degree, which can be figure of eight plate.
As shown in figure 5, the embodiment of the invention also provides a kind of unmanned plane, including fuselage 10, flight control system and above-mentioned
Unmanned plane battery fastening structure, wherein mounting rack 1 and driving portion 3 are all set in fuselage 10；Driving portion 3 is electrically connected with flight control system
It connects.
Unmanned plane provided in an embodiment of the present invention, including unmanned plane battery fastening structure, the mounting structure pass through setting peace
Shelve and fixed body, and with fixed body and the driving portion that is detachably connected, and driving portion can be with the flight control system of unmanned plane
Electrical connection, to realize when needing to charge the battery or replace, driving portion can drive under the control of flight control system
Dynamic fixed body skids off mounting rack, then driving portion and fixed body are dismantled, and the integral demounting of all batteries can be realized；When need
When battery is installed, driving portion and fixed body can be attached, driving portion can drive solid under the control of flight control system
Determine body and slide into mounting rack, the integral installation of all batteries can be realized, it is inconvenient, improve the disassembly efficiency of battery.
Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although
Present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: it still may be used
To modify the technical solutions described in the foregoing embodiments or equivalent replacement of some of the technical features；
And these are modified or replaceed, technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution spirit and
Range.
Claims (10)
1. a kind of unmanned plane battery fastening structure characterized by comprising
Mounting rack；
Fixed body, the fixed body are slidably connected in the mounting rack, be provided in the fixed body chamfered shape with it is described
The chamfered shape of battery is adapted, and multiple accommodating chambers for accommodating multiple batteries；
Driving portion, the output end of the driving portion are detachably connected with the fixed body, and the driving portion is used for and the nothing
Man-machine flight control system electrical connection, and the fixed body can be driven to slide in or out described under the control of the flight control system
Mounting rack.
2. unmanned plane battery fastening structure according to claim 1, which is characterized in that
The driving portion includes steering engine, rocker arm and push-and-pull connecting rod；
The output shaft of one end of the rocker arm and the steering engine is rotatablely connected；
It is described push-and-pull connecting rod one end and the rocker arm the other end be rotatablely connected, it is described push-and-pull connecting rod the other end with it is described solid
Determine body to be removably rotatablely connected；
The steering engine with the flight control system of the unmanned plane for being electrically connected, for passing through under the control of the flight control system
The rocker arm and the push-and-pull connecting rod push and pull the fixed body, so that the fixed body skids off or slide into the mounting rack.
3. unmanned plane battery fastening structure according to claim 2, which is characterized in that
The other end of the rocker arm is provided with multiple the first mounting holes arranged along its length；
One end of the push-and-pull connecting rod is provided with the second mounting hole；
Second mounting hole can be rotatablely connected by shaft and each first mounting hole.
4. unmanned plane battery fastening structure according to claim 2, which is characterized in that
The other end of the push-and-pull connecting rod is rotatably connected to connecting plate, and third mounting hole is provided on the connecting plate；
It is provided with the 4th mounting hole on the fixed body, is inserted with fastening in the third mounting hole and the 4th mounting hole
Part.
5. unmanned plane battery fastening structure according to claim 2, which is characterized in that further include:
Fixed frame is provided with the first through hole along fixed body glide direction arrangement on the fixed frame；
The steering engine is set in the fixed frame, and the other end of the rocker arm passes through the first through hole and the push-and-pull connecting rod
One end rotation connection, and the rocker arm is swung in the first through hole.
6. unmanned plane battery fastening structure according to any one of claim 1 to 5, which is characterized in that further include:
Locking part, the locking part are set to the mounting rack, and the locking part has lockup state and unlocked state；
When the locking part is in lockup state, the fixed physical efficiency is locked in the mounting rack；
When the locking part is in the unlocked state, the fixed physical efficiency skids off the mounting rack.
7. unmanned plane battery fastening structure according to claim 6, which is characterized in that the locking part includes:
It is respectively arranged on the mounting rack and the fixed body and opposite the second through-hole and third through-hole；
Connector, the connector are connected to the mounting rack bottom；
Handle, the handle are rotatablely connected by elastic component and the connector；
Positioning pin, one end of the positioning pin and the handle are rotatablely connected, and the other end penetrates second through-hole and described the
Three through-holes；
Wherein, when the handle is pressed, the positioning pin can be retracted in second through-hole, form the locking part
Unlocked state；When the handle is released, the handle capable of being resets under the action of the elastic component, and drives the positioning
Pin resets, and forms the lockup state of the locking part.
8. according to claim 1 to unmanned plane battery fastening structure described in any one of 3,5 to 7, which is characterized in that
Charging interface is provided on the fixed body, the charging interface with the battery for being electrically connected.
9. according to claim 1 to unmanned plane battery fastening structure described in any one of 3,5 to 7, which is characterized in that
The first sliding rail is provided on the mounting rack；
The second sliding rail being slidably connected with first sliding rail is provided on the fixed body, the fixed body passes through described first
Sliding rail and second sliding rail are slidably connected in the mounting rack.
10. a kind of unmanned plane characterized by comprising
Fuselage, flight control system and unmanned plane battery fastening structure as claimed in any one of claims 1-9 wherein；
The mounting rack and the driving portion are all set in the fuselage；
The driving portion is electrically connected with the flight control system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910470885.4A CN110212129A (en) | 2019-05-31 | 2019-05-31 | Unmanned plane battery fastening structure and unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910470885.4A CN110212129A (en) | 2019-05-31 | 2019-05-31 | Unmanned plane battery fastening structure and unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110212129A true CN110212129A (en) | 2019-09-06 |
Family
ID=67790014
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910470885.4A Pending CN110212129A (en) | 2019-05-31 | 2019-05-31 | Unmanned plane battery fastening structure and unmanned plane |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111038326A (en) * | 2019-12-24 | 2020-04-21 | 江南大学 | Rotatory device of changing of unmanned aerial vehicle battery |
| CN114614183A (en) * | 2022-03-04 | 2022-06-10 | 上海沃兰特航空技术有限责任公司 | Battery package mounting structure and electric aircraft |
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|---|---|---|---|---|
| CN205944161U (en) * | 2016-06-29 | 2017-02-08 | 苏大毛 | Novel unmanned aerial vehicle uses intelligent battery structure |
| CN109624935A (en) * | 2019-02-20 | 2019-04-16 | 深圳市多翼创新科技有限公司 | A kind of automatically replacing battery structure, device and unmanned plane airport |
| CN210325884U (en) * | 2019-05-31 | 2020-04-14 | 沈阳无距科技有限公司 | Unmanned aerial vehicle battery mounting structure and unmanned aerial vehicle |
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2019
- 2019-05-31 CN CN201910470885.4A patent/CN110212129A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205944161U (en) * | 2016-06-29 | 2017-02-08 | 苏大毛 | Novel unmanned aerial vehicle uses intelligent battery structure |
| CN109624935A (en) * | 2019-02-20 | 2019-04-16 | 深圳市多翼创新科技有限公司 | A kind of automatically replacing battery structure, device and unmanned plane airport |
| CN210325884U (en) * | 2019-05-31 | 2020-04-14 | 沈阳无距科技有限公司 | Unmanned aerial vehicle battery mounting structure and unmanned aerial vehicle |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111038326A (en) * | 2019-12-24 | 2020-04-21 | 江南大学 | Rotatory device of changing of unmanned aerial vehicle battery |
| CN114614183A (en) * | 2022-03-04 | 2022-06-10 | 上海沃兰特航空技术有限责任公司 | Battery package mounting structure and electric aircraft |
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