CN107600439A - A kind of long endurance unmanned aircraft electrical source of power device and unmanned plane - Google Patents
A kind of long endurance unmanned aircraft electrical source of power device and unmanned plane Download PDFInfo
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- CN107600439A CN107600439A CN201710884972.5A CN201710884972A CN107600439A CN 107600439 A CN107600439 A CN 107600439A CN 201710884972 A CN201710884972 A CN 201710884972A CN 107600439 A CN107600439 A CN 107600439A
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- 238000000926 separation method Methods 0.000 claims description 21
- 239000012634 fragment Substances 0.000 claims description 6
- 230000003139 buffering effect Effects 0.000 claims description 4
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 3
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 229910052744 lithium Inorganic materials 0.000 claims description 3
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- 238000007726 management method Methods 0.000 description 17
- 238000005457 optimization Methods 0.000 description 7
- 239000002131 composite material Substances 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
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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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention discloses a kind of long endurance unmanned aircraft electrical source of power device, including support body, control storehouse and n independent battery compartments, when the electricity of first battery modules will exhaust, its corresponding battery compartment is opened to be thrown off it from unmanned plane, new battery modules are switched to power, the load of unmanned plane can so be mitigated, so as to effectively save the consumption of electric energy, cruising time and voyage can be effectively improved.Load can be mitigated step by step by being equipped with when the long endurance unmanned aircraft of above-mentioned long endurance unmanned aircraft electrical source of power device works in the air.
Description
Technical field
The invention belongs to unmanned plane power technology field, and in particular to a kind of long endurance unmanned aircraft electrical source of power device
And unmanned plane.
Background technology
At present, China's civil small-scale unmanned plane market is a piece of thriving, and industry experts represent, although domestic unmanned plane
Industry development is still at an early stage.But unmanned plane enterprise of China this several years is deep accumulated, shoots up, it has also become the whole industry
Outstanding person.2015, in the unmanned plane exhibition section in U.S. CE S consumer electronics shows, Chinese Enterprise account for half.Often sell 10 in the whole world
Frame unmanned plane, it is made in China just to have 7 framves.
Mobile Internet brings new opportunities to unmanned plane, also reduces operation threshold.Motion sensing manipulation pattern unmanned plane will
Originally it need to become simple by the unmanned plane during flying of the winged hand manipulation of specialty, and easily left-hand seat.
But civil small-scale unmanned plane most cruising time is shorter, voyage is near.This exists mainly due to most of unmanned planes
Single battery is used during flight, and for power, battery consumption is too fast.Although also there is the unmanned plane using multiple electrical source of power groups,
More electrical source of power groups are typically in parallel, and because the carry of civil small-scale unmanned plane is limited in one's ability, overweight take-off weight also increases
Add the consumption of electric energy, cause the lifting amplitude of cruising time and voyage extremely limited.
The content of the invention
For deficiencies of the prior art, the purpose of the invention is that providing a kind of long endurance unmanned aircraft moves
Power supply unit and unmanned plane.
To achieve these goals, the technical scheme that the invention uses is as follows：
A kind of long endurance unmanned aircraft electrical source of power device, it is characterised in that including support body, control storehouse and n independent electricity
Chi Cang, n are >=2 integer, and described support body is H type supports, is made up of a horizontal beam and two vertical beams, the horizontal beam
Both ends are separately fixed at the centre of two vertical beams；It is described to control the box body that storehouse is a closing, it is fixed on the upper beam of the horizontal beam
Face, the battery compartment are arranged on the underbeam face of the horizontal beam；PCB control boards, each battery are provided with described control storehouse
A battery modules and separator are all placed with storehouse；BMS battery management system moulds are provided with described PCB control boards
Block, each described battery modules are independently connected with the BMS battery management system modules, the BMS battery management systems
One of battery modules are connected by module with unmanned plane power supply circuit, as working battery module；The BMS battery managements system
The voltage sensor for monitoring relevant work battery modules voltage is provided with system and the signal for sending information of voltage is sent out
Emitter, the voltage sensor are parallel to the both ends of the working battery module, described voltage sensor and signal projector
It is connected；Information acquisition device, comparison processor and battery modules separation driver are additionally provided with described PCB control boards, it is described
Information acquisition device be used for receiving voltage information and be transferred to comparison processor；The comparison processor is used to believe voltage
Breath is compared with the threshold values of its storage inside；When the voltage of working battery module is less than threshold values, the comparison processor will
The information of voltage sends described BMS battery management system modules to, and the BMS battery management system modules are used to disconnect with being somebody's turn to do
Battery modules in another battery compartment are simultaneously connected by working battery module with unmanned plane power supply circuit, so that another battery mould
Group is used as work at present battery modules；The BMS battery management system modules separate driver with the battery modules and are connected, and use
Driver is separated in battery modules separation command is sent into the battery modules, the battery modules separation driver is used for
Start the separator of the battery compartment where previous working battery module, the separation dress when receiving battery modules separation command
Put for previous working battery module to be separated.
Further, the battery compartment includes warehouse and Cang Gai, and the warehouse is the open casing in bottom, the Cang Gai and institute
The open shape for stating warehouse is adapted, open to form the battery compartment of closing for closing；The Cang Gai is articulated with the storehouse
The open-mouth of body, formation are rotatably connected；Lock is provided between described warehouse and storehouse lid, for fastening described storehouse
Lid；Described separator is connected with described lock, for driving the opening and closing of lock.
Further, the separator includes clockwork spring and gear, and the two is installed in the open-mouth of the warehouse, the hair
Bar is connected with gear；Described lock is L-shaped, one end semicircular in shape of the lock, and the semicircular center of circle is hinged on described
Warehouse on, the gabarit of the semicircle sets with teeth, and for being engaged with gear, the other end is fastened on storehouse and covered, and can be touched in clockwork spring
Rotated during hair under the drive of gear to the direction away from Cang Gai to open Cang Gai.
Further, covered in described storehouse and be provided with two hard contacts, above-mentioned two hard contact respectively with BMS batteries
The positive and negative electrode connection of management system module；In the warehouse with being provided with spring on open farthest inwall.
Further, described battery modules separation driver is arranged in control terminal.
Further, the separator is arranged on the Cang Gai and the opposite side of warehouse hinged place with the lock.
As the design of another battery compartment, the battery compartment includes the left warehouse mutually fastened and right warehouse, institute
State left warehouse and right warehouse be open at one end cuboid box-like and open direction it is relative, so as to be formed when the two is being fastened
The battery compartment of closing；The left warehouse and right warehouse are hinged in the two open upper edge；Described left warehouse and right warehouse
Connecting rod is respectively arranged between horizontal beam, one end of the connecting rod is hinged on left warehouse or right warehouse, other end hinge
It is connected on horizontal beam；Described separator is the minitype cylinder above the hinged place of left warehouse and right warehouse, and this is micro-
The lower end of type cylinder is connected with pushing the upper end of push rod, can be moved downward under drive device driving and be promoted left warehouse and the right side
The hinged place of warehouse is to open battery compartment.
Further, a shell fragment is each provided with the right side of the left side of left warehouse and right warehouse, the upper end of the shell fragment is consolidated
It is scheduled on described horizontal beam, lower end freely extends downwards.
Further, the battery modules are lithium battery or battery pack；Cushion is coated with the outside of the battery modules,
Impulsion power during for buffering its landing；Parachute is additionally provided with described battery modules, for slowing down the speed of whereabouts.
A kind of long endurance unmanned aircraft, above-mentioned long endurance unmanned aircraft electrical source of power device is installed at ventral, in two institutes
State and T font projections are respectively arranged with the outside of vertical beam, two T font chutes, two T words are provided with described ventral
The spacing of type chute and the distance in the outside of two vertical beams are adapted；The cross sectional shape of the T fonts chute and the T words
Type projection is adapted.
Compared with prior art, the invention has the advantages that：
1st, the invention makes unmanned plane mitigate load step by step when working in the air, when the electricity of first battery modules is
When will exhaust, it is thrown off from unmanned plane, is switched to new battery modules to power, can so mitigate the negative of unmanned plane
Carry, so as to effectively save the consumption of electric energy, cruising time and voyage can be effectively improved.
2nd, the battery box structure of the invention design is simple, and energy consumption is low, opens soon, can rapidly isolate energy consumption
Most battery.
3rd, the long endurance unmanned aircraft electrical source of power device of the invention can widely use, to existing each model nobody
Machine can carry after carrying out simple refit.Meanwhile to ensure the continuous use of unmanned plane, multiple the invention can be equipped with
Long endurance unmanned aircraft electrical source of power device or battery modules, for replacing at any time.
Brief description of the drawings
Fig. 1 is that the PCB control boards of unmanned plane electrical source of power device arrange schematic diagram；
Fig. 2 is the structural representation of unmanned plane electrical source of power device；
Fig. 3 is another structural representation of unmanned plane electrical source of power device；
Fig. 4 is the multi-rotor unmanned aerial vehicle structural representation using the invention；
Fig. 5 is the composite wing unmanned plane structural representation using the invention；
In accompanying drawing：1-control storehouse；10-PCB control boards；101-BMS battery management system modules；102-information gathering
Device；103-compare processor；104-battery modules separate driver；11-horizontal beam；12-vertical beam；121-T fonts are convex
Block；20-battery modules；21-warehouse；22-Cang Gai；23-lock；24-gear；25-spring；26-left warehouse；27—
Right warehouse；28-connecting rod；29-push push rod；210-minitype cylinder；31-rotor；32-horn；33-body；34—
Long endurance unmanned aircraft electrical source of power device.
Embodiment
The invention is described in further detail with reference to specific embodiment.
As Figure 1-3, a kind of long endurance unmanned aircraft electrical source of power device, it is characterised in that including support body, control storehouse 1
With n independent battery compartments, n is >=2 integer, and described support body is H type supports, by a horizontal beam 11 and two vertical beams 12
Form, the both ends of the horizontal beam 11 are separately fixed at the centre of two vertical beams 12；The control storehouse 1 is the box body of a closing,
The upper beam face of the horizontal beam 11 is fixed on, the battery compartment is arranged on the underbeam face of the horizontal beam 11；Described control storehouse 1
In be provided with PCB control boards 10, a battery modules 20 and separator are placed with each battery compartment；In described PCB
Be provided with BMS battery management system modules 101 on control plate 10, each described battery modules 20 independently with the BMS batteries
Management system module 101 is connected, and the BMS battery management system modules 101 supply one of battery modules 20 and unmanned plane
Circuit connects, as working battery module；It is provided with the BMS battery management systems for monitoring relevant work battery mould
The voltage sensor of group voltage and the signal projector for sending information of voltage, the voltage sensor are parallel to the work
The both ends of battery modules, described voltage sensor are connected with signal projector；Letter is additionally provided with described PCB control boards 10
Collector 102, comparison processor 103 and battery modules separation driver 104, described information acquisition device 102 is ceased to be used to receive
Information of voltage is simultaneously transferred to comparison processor 103；The comparison processor 103 is used for information of voltage and its storage inside
Threshold values be compared；When the voltage of working battery module is less than threshold values, the comparison processor 103 passes the information of voltage
Described BMS battery management system modules 101 are given, the BMS battery management system modules 101 are used to disconnect and work electricity
Battery modules 20 in another battery compartment are simultaneously connected by pond module with unmanned plane power supply circuit, so that another battery modules 20
As work at present battery modules；The BMS battery management system modules 101 separate the phase of driver 104 with the battery modules
Even, driver 104, the battery modules separation driving are separated for battery modules separation command to be sent into the battery modules
Separation dress of the device 104 for the battery compartment where starting previous working battery module when receiving battery modules separation command
Put, the separator is used to separate previous working battery module.
When the electricity of first battery modules 20 will exhaust, it is thrown off from unmanned plane, is switched to new battery
Module 20 is powered, and can so mitigate the load of unmanned plane, so as to effectively save the consumption of electric energy, can be effectively improved continuous
ETS estimated time of sailing and voyage.
The threshold values of storage inside for comparing processor 103 is usually the 80% of rated voltage, based on battery operation principle, when
When the electricity remaining sum of battery modules 20 is 5%, its voltage is the 80% of original state, considers switching supplying cell module 20
Time difference, it is impossible to switch when electricity exhausts, when electricity remaining sum 5% or so, switching it is more suitable.If it is considered that battery is old
The reasons such as change, when voltage is the 80% of original state, electricity remaining sum can be lower, therefore, must now switch supplying cell mould
Group 20.
Described information acquisition device 102, comparison processor 103 and battery modules separation driver 104 can use DVP-ES2
The controller such as series, DVP-EX2 series, DVP-ES2-C series.
As optimization, as shown in Fig. 2 the battery compartment includes warehouse 21 and storehouse lid 22, the warehouse 21 is that bottom is open
Casing, the open shape of the storehouse lid 22 and the warehouse 21 is adapted, open to form the battery of closing for closing
Storehouse；The storehouse lid 22 is articulated with the open-mouth of the warehouse 21, and formation is rotatably connected；Described warehouse 21 and storehouse lid 22 it
Between be provided with lock 23, for fastening described storehouse lid 22；Described separator is connected with described lock 23, for driving
The opening and closing of lock 23.This structure processing is simple, can reduce processing cost, due to simple in construction, can also greatly reduce failure
Rate.
As optimization, the separator includes clockwork spring and gear 24, and the two is installed in the open-mouth of the warehouse 21,
The clockwork spring is connected with gear 24；Described lock 23 is L-shaped, one end semicircular in shape of the lock 23, the semicircular circle
The heart is hinged on described warehouse 21, and the gabarit setting of the semicircle is with teeth, and for being engaged with gear 24, the other end is fastened on Cang Gai
On 22, it can be rotated when clockwork spring triggers under the drive of gear 24 to the direction away from storehouse lid 22 to open storehouse lid 22.
It is safe and reliable as the actuating unit of separator using clockwork spring, and clockwork spring is as a kind of well-known accumulation of energy
Device, biggest advantage are exactly not consume electric energy, can so enter and a little improve cruising time.
As optimization, be provided with two hard contacts on described storehouse lid 22, above-mentioned two hard contact respectively with BMS
The positive and negative electrode connection of battery management system module 101；In the warehouse 21 with being provided with spring 25 on open farthest inwall.
So it is designed with two advantages：First, when battery modules 20 are powered, it can be compressed, improve the reliability of connection；Second,
After battery compartment opening, in the presence of spring 25, it is more beneficial for dishing out battery modules 20.
As optimization, described battery modules separation driver 104 is arranged in control terminal.Usual unmanned plane has behaviour
Make terminal (such as mobile phone, PDA, computer, remote control), battery modules separation driver 104 is provided with operation terminal, behaviour
Battery modules 20 of being dished out in suitable place can be selected by making personnel.
As optimization, the separator is arranged on pair of the storehouse lid 22 and the hinged place of warehouse 21 with the lock 23
Side.The effect so fastened is best, and storehouse lid 22 is opened and is also easier to.
As the design of another battery compartment, as shown in figure 3, the battery compartment includes the left warehouse 26 mutually fastened
With right warehouse 27, the left warehouse 26 and right warehouse 27 are the cuboid box-like of open at one end and open direction is relative, so that
The battery compartment of closing is formed when the two is being fastened；The left warehouse 26 and right warehouse 27 are in the two open upper edge hinge
Connect；It is respectively arranged with connecting rod 28 between described left warehouse 26 and right warehouse 27 and horizontal beam 11, the one of the connecting rod 28
End is hinged on left warehouse 26 or right warehouse 27, and the other end is hinged on horizontal beam 11；Described separator is installed in a left side
Minitype cylinder 210 above the hinged place of warehouse 26 and right warehouse 27, the lower end of the minitype cylinder 210 is with pushing the upper of push rod 29
End connection, it can be moved downward under drive device driving and promote the hinged place of left warehouse 26 and right warehouse 27 to open battery
Storehouse.
For this scheme when opening, the angle of opening is bigger, can preferably separate.Such as CG- can be used in minitype cylinder 210
The series of the series of L020~100, CG-F020~100, CG-020-24A~CG-100-24A series etc..
As optimization, a shell fragment is each provided with the right side in the left side of left warehouse 26 and right warehouse 27, the shell fragment
Upper end is fixed on described horizontal beam 11, and lower end freely extends downwards.So design is ensured when battery compartment is closed, and allows electricity
Pond module 20 is stably in connection status.
As optimization, the battery modules 20 are lithium battery or battery pack；It is coated with the outside of the battery modules 20
Cushion, impulsion power during for buffering its landing；Parachute is additionally provided with described battery modules 20, under slowing down
The speed fallen.
Cushion can be the elastic materials such as plastic cement, rubber, can be the vacuum bag equipped with check valve.
, under atmospheric pressure can be automatically into vacuum bag after battery modules 20 are separated, and check valve then can
The air for effectively preventing from entering leaks, so as to quickly form buffering pneumatic cushion.Preferably, check valve should be arranged below, in order to
Direction is constant when ensureing to fall, and can set mass in the bottom of battery modules 20.
A kind of long endurance unmanned aircraft, above-mentioned long endurance unmanned aircraft electrical source of power device is installed at ventral, in two institutes
The outside for stating vertical beam 12 is respectively arranged with T fonts projection 121, and two T font chutes, two institutes are provided with described ventral
The spacing and the distance in the outside of two vertical beams 12 for stating T font chutes are adapted；The cross sectional shape of the T fonts chute with
The T fonts projection 121 is adapted.
The long endurance unmanned aircraft electrical source of power device of the invention can widely use, to existing each model unmanned plane
Carry out after simple refit can carry, multi-rotor unmanned aerial vehicle as shown in Figure 4 and the composite wing unmanned plane shown in Fig. 5, on machine
There are rotor 31, horn 32, body 33, long endurance unmanned aircraft electrical source of power device 34.
In addition, to ensure the continuous use of unmanned plane, the long endurance unmanned aircraft power of multiple the invention can be equipped with
Supply unit or battery modules 20, for replacing at any time.
Above-described embodiment of the invention only creates example to illustrate the invention, and is not to this hair
The restriction of the embodiment of bright creation.For those of ordinary skill in the field, may be used also on the basis of the above description
To make other various forms of changes and variation.Here all embodiments can not be exhaustive.It is every to belong to this hair
Row of the obvious changes or variations that the technical scheme of bright creation is amplified out still in the protection domain of the invention.
Claims (10)
1. a kind of long endurance unmanned aircraft electrical source of power device, it is characterised in that including support body, control storehouse and n independent batteries
Storehouse, n are >=2 integer, and described support body is H type supports, is made up of a horizontal beam and two vertical beams, the two of the horizontal beam
End is separately fixed at the centre of two vertical beams；It is described to control the box body that storehouse is a closing, the upper beam face of the horizontal beam is fixed on,
The battery compartment is arranged on the underbeam face of the horizontal beam；PCB control boards are provided with described control storehouse, in each battery compartment
All it is placed with a battery modules and separator；
Be provided with BMS battery management system modules on described PCB control boards, each described battery modules independently with it is described
BMS battery management system modules are connected, and the BMS battery management system modules power one of battery modules and unmanned plane
Circuit connects, as working battery module；
The voltage sensor for monitoring relevant work battery modules voltage is provided with the BMS battery management systems and is used for
The signal projector of information of voltage is sent, the voltage sensor is parallel to the both ends of the working battery module, described electricity
Pressure sensor is connected with signal projector；
Information acquisition device, comparison processor and battery modules separation driver are additionally provided with described PCB control boards, it is described
Information acquisition device is used for receiving voltage information and is transferred to comparison processor；The comparison processor is used for information of voltage
It is compared with the threshold values of its storage inside；When the voltage of working battery module is less than threshold values, the comparison processor should
Information of voltage sends described BMS battery management system modules to, and the BMS battery management system modules are used to disconnect and the work
Make battery modules and be connected the battery modules in another battery compartment with unmanned plane power supply circuit, so that another battery modules
As work at present battery modules；
The BMS battery management system modules separate driver with the battery modules and are connected, for by battery modules separation finger
Order is sent to the battery modules separation driver, and the battery modules separation driver is used to receive battery modules separation
Start the separator of the battery compartment where previous working battery module during instruction, the separator is used for previous work electricity
Pond module separation.
2. long endurance unmanned aircraft electrical source of power device according to claim 1, it is characterised in that the battery compartment includes storehouse
Body and Cang Gai, the warehouse are the open casing in bottom, and the Cang Gai and the warehouse open shape are adapted, for sealing
Opening is closed to form the battery compartment of closing；The Cang Gai is articulated with the open-mouth of the warehouse, and formation is rotatably connected；Described
Warehouse and storehouse lid between be provided with lock, for fastening described Cang Gai；Described separator is connected with described lock,
For driving the opening and closing of lock.
3. long endurance unmanned aircraft electrical source of power device according to claim 2, it is characterised in that the separator includes
Clockwork spring and gear, the two is installed in the open-mouth of the warehouse, and the clockwork spring is connected with gear；Described lock is L-shaped, institute
One end semicircular in shape of lock is stated, the semicircular center of circle is hinged on described warehouse, and the gabarit of the semicircle sets with teeth, use
Engaged in gear, the other end is fastened on storehouse and covered, can be under the drive when clockwork spring triggers in gear to the side away from Cang Gai
To rotating to open Cang Gai.
4. long endurance unmanned aircraft electrical source of power device according to claim 2, it is characterised in that cover and set in described storehouse
Two hard contacts are equipped with, positive and negative electrode of the above-mentioned two hard contact respectively with BMS battery management system modules is connected；Institute
Warehouse is stated with being provided with spring on open farthest inwall.
5. long endurance unmanned aircraft electrical source of power device according to claim 2, it is characterised in that described battery modules point
It is arranged on from driver in control terminal.
6. according to any described long endurance unmanned aircraft electrical source of power devices of claim 2-6, it is characterised in that the separation dress
Put and be arranged on the Cang Gai and the opposite side of warehouse hinged place with the lock.
7. long endurance unmanned aircraft electrical source of power device according to claim 1, it is characterised in that the battery compartment includes phase
The left warehouse and right warehouse mutually fastened, the left warehouse and right warehouse are the cuboid box-like of open at one end and open direction phase
It is right, so as to form the battery compartment of closing when the two is being fastened；The left warehouse and right warehouse are in the two open upper edge
It is be hinged；Connecting rod is respectively arranged between described left warehouse and right warehouse and horizontal beam, one end of the connecting rod is hinged on
On left warehouse or right warehouse, the other end is hinged on horizontal beam；
Described separator is minitype cylinder above the hinged place of left warehouse and right warehouse, under the minitype cylinder
Hold and push the upper end connection of push rod, can be moved downward under drive device driving and promote left warehouse and right warehouse it is be hinged
Sentence opening battery compartment.
8. long endurance unmanned aircraft electrical source of power device according to claim 1, it is characterised in that in the left side of left warehouse and
A shell fragment is each provided with the right side of right warehouse, the upper end of the shell fragment is fixed on described horizontal beam, and lower end is free downwards
Extension.
9. the long endurance unmanned aircraft electrical source of power device according to claim 1 or 2 or 7, it is characterised in that the battery mould
Group is lithium battery or battery pack；Cushion is coated with the outside of the battery modules, impulsion power during for buffering its landing；
Parachute is additionally provided with described battery modules, for slowing down the speed of whereabouts.
A kind of 10. long endurance unmanned aircraft, it is characterised in that be provided with ventral long endurance as claimed in claim 9 nobody
Mechanomotive force supply unit, T font projections are respectively arranged with the outside of two vertical beams, two are provided with described ventral
Bar T font chutes, the spacing and the distance in the outside of two vertical beams of two T fonts chutes are adapted；The T fonts
The cross sectional shape of chute is adapted with the T fonts projection.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710884972.5A CN107600439B (en) | 2017-09-26 | 2017-09-26 | Long-endurance unmanned aerial vehicle power supply device and unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710884972.5A CN107600439B (en) | 2017-09-26 | 2017-09-26 | Long-endurance unmanned aerial vehicle power supply device and unmanned aerial vehicle |
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| CN107600439B CN107600439B (en) | 2024-05-14 |
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Cited By (8)
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| CN108287000A (en) * | 2018-01-25 | 2018-07-17 | 数字鹰电子（湖北）有限公司 | Environmental monitoring unmanned plane |
| CN108298060A (en) * | 2018-01-31 | 2018-07-20 | 倪惠芳 | High strength multifunctionality unmanned aerial vehicle load frame |
| CN108583893A (en) * | 2018-04-17 | 2018-09-28 | 深圳市安思科电子科技有限公司 | A kind of intelligent plant protection drone that the cruising ability being conveniently replaceable battery is strong |
| CN108945465A (en) * | 2018-08-22 | 2018-12-07 | 江苏心源航空科技有限公司 | A kind of battery for electronic multi-rotor aerocraft is jettisoninged and recycling positioning device |
| CN109398706A (en) * | 2018-12-05 | 2019-03-01 | 智灵飞（北京）科技有限公司 | A kind of unmanned plane during flying is the mechanical structure for extending endurance and leaving battery on horn |
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