CN208412154U - A kind of more battery pack unmanned plane power supply systems - Google Patents
A kind of more battery pack unmanned plane power supply systems Download PDFInfo
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- CN208412154U CN208412154U CN201820854385.1U CN201820854385U CN208412154U CN 208412154 U CN208412154 U CN 208412154U CN 201820854385 U CN201820854385 U CN 201820854385U CN 208412154 U CN208412154 U CN 208412154U
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- unmanned plane
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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
- 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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
A kind of more battery pack unmanned plane power supply systems, the unmanned plane includes fuselage, the unmanned plane power supply system includes the mainboard control module of power module and control power module work, the power module includes multiple battery components parallel with one another, the unmanned aerial vehicle body side is equipped with the installation position of multiple battery components, the battery component is elongated, and it is set in installation position vertically, each battery component is electrically connected with mainboard control module respectively, mainboard control module is enabled to control the operation and stopping of multiple battery components, and the sequence that shares out the work.Multiple groups battery component parallel with one another is arranged in the utility model, and after the electricity of one group of battery component is finished, another battery continues as unmanned plane continuation of the journey, substantially prolongs the flight time of unmanned plane, increases the experience of user.The critical electricity can be configured according to handling characteristics, more have specific aim.
Description
Technical field
The utility model relates to air vehicle technique fields, and in particular to a kind of more battery pack unmanned plane power supply systems.
Background technique
Common flight device is typically divided into fixed-wing, helicopter and more rotors (quadrotor mainstream the most).2010 it
Before, no matter fixed-wing and helicopter are taking photo by plane or model plane Sports Field, substantially occupy absolute leading position.However,
In several years later, because of excellent handling, more rotors rapidly become the nova taken photo by plane with model plane Sports Field.Because of the product
The difficulty and cost taken photo by plane are significantly reduced, the vast consumer group is obtained, becomes product most fast-selling so far.
Multi-rotor unmanned aerial vehicle is also the rotation by motor, so that propeller is generated lift and flies up.Such as quadrotor without
Man-machine, when the sum of lift of four propellers of aircraft is equal to aircraft gross weight amount, lift and the gravity of aircraft balance each other, and aircraft is just
It can hover in the sky.When aircraft needs wicking height, four propellers accelerate to rotate simultaneously, and lift increases, and aircraft is just
It can rise；Similarly when aircraft needs to reduce height, four propellers can reduce revolving speed simultaneously, and aircraft also just has dropped.
Multi-rotor unmanned aerial vehicle is many by favor reason, and such as in terms of handling, the manipulation of more rotors is simplest.It is not
Need runway can VTOL, can hover in the sky after taking off.Its manipulating principle is simple, four remote sensing operations of control device
The front and rear, left and right of corresponding aircraft, upper and lower and yaw direction movement.And the requirement of fixed-wing flying field is open, and helicopter
Interchannel coupling can be generated in flight course, autopilot controller design is difficult, and controller adjusts also highly difficult.
In terms of reliability, more rotors are also that performance is most outstanding.If only considering mechanical reliability, more rotors are not lived
Dynamic component, its reliability is substantially dependent on the reliability of brushless motor, therefore reliability is higher.In comparison, fixed
The wing and helicopter have movable mechanical connecting element, can generate abrasion in flight course, lead to reliability decrease.And more rotors
It can hover, flight range is controlled, and the relatively fixed wing is safer.
In terms of duties, the duties of more rotors are highest.Because its structure is simple, if motor, electron speed regulator, electricity
Pond, paddle and rack damage, it is easy to replace.And fixed-wing and helicopter part comparison are more, installation is also required to skill, relatively
Trouble.
However, existing multi-rotor unmanned aerial vehicle is due to needing to revolve paddle, consumed electric energy using multiple motor drivens
Also more, multi-rotor unmanned aerial vehicle in the prior art causes the flight time short mostly since power consumption is too many, and cruising ability is insufficient.
Utility model content
The utility model relates to a kind of more battery pack unmanned plane power supply systems, for solving unmanned plane power consumption in the prior art
Fastly, short problem in cruise duration.
To solve the above-mentioned problems, the utility model provides a kind of more battery pack unmanned plane power supply systems, the unmanned plane
Including fuselage, the unmanned plane power supply system includes the mainboard control module of power module and control power module work, described
Power module includes multiple battery components parallel with one another, and the unmanned aerial vehicle body side is equipped with the installation of multiple battery components
Position, the battery component is elongated, and vertically be set to installation position in, each battery component respectively with mainboard control module
Electrical connection, enables mainboard control module to control the operation and stopping of multiple battery components, and the sequence that shares out the work.
The fuselage is in approximate square shape, including four sides, wherein front side is equipped with the installation position of head assembly, institute
Head assembly is stated in the installation position, the fuselage interior is equipped with control system and circuit element, by external remote controller or
Mobile terminal can connect control system, and realize the control to unmanned plane.
In order to increase the cruise duration of unmanned plane, multiple groups battery component parallel with one another is arranged in the utility model, when one group
After the electricity of battery component is finished, another battery continues as unmanned plane continuation of the journey, when substantially prolonging the flight of unmanned plane
Between, increase the experience of user.
The mainboard control module is set to fuselage interior, can control in unmanned plane the opening and closing of electric elements and
It uses.Each battery component and mainboard control module link, and mainboard control module is enabled to control each battery pack
The starting and closing of part.
Therefore, the setting of multiple battery packs, control uses in a predetermined sequence, is able to extend the flight time.
Further, the battery component includes three battery components, and the fuselage includes front side, rear side, left side and the right side
Side, three battery components are respectively arranged on the left side, right side and rear side of fuselage.
In order to reduce the overall volume of unmanned plane, there are four rotor, the rotor intervals to be arranged for the utility model setting,
Middle battery component is arranged between two rotor assemblies, and since battery pack excessively equally will increase the power consumption of unmanned plane, instead
And be unfavorable for continuing a journey for a long time, it is preferred that 3 groups of batteries are arranged in the utility model, be separately positioned on the left side of fuselage, right side and after
Side, and the rear and front end on the left of the fuselage is respectively provided with one group of folding rotor assemblies, the right side and left side of the fuselage are right
Position is claimed to be equipped with two groups of folding rotor assemblies, the rotor is proximal end close to fuselage one end, and the other end is distal end, the rotation
The distal end of the wing is equipped with Collapsible rack, and when rotor and bracket are unfolded simultaneously, the unmanned plane can be placed smoothly on the ground, works as needs
When storage, bracket and rotor can all be folded, reduce the overall volume of unmanned plane.
The battery pack of the utility model setting is vertically installed at the side of fuselage, and the length of the battery component is less than fuselage
Height, the width of the battery component is less than the horizontal distance of adjacent two rotor assemblies proximal end.So that the center of gravity of fuselage is more
Middle part is concentrated on, while reducing unmanned plane volume, so that flight is more stable.
Further, the power module is equipped with critical electricity, described when electricity≤critical electricity of the battery component
Mainboard control module controls the battery component and stops working, while starting next battery component.
In order to protect battery, avoids exhausting electricity every time and damaging battery, influence the service life of battery, this is practical
It is novel to be provided with critical electricity, by the way that the value of critical electricity is arranged in mainboard control module, when the battery component to work
When remaining capacity≤critical electricity, the mainboard control module controls the battery component and stops working.The critical electricity can
To be configured according to handling characteristics, more there is specific aim.The mainboard control module controls the battery component and stops work
As while will start next battery component and start to work, realize the seamless interfacing between two battery components, ensure that nothing
Man-machine normal flight.
Further, the critical electricity is the 5% of battery component total electricity.
According to general use demand, the utility model selects that critical electricity is arranged as the remaining capacity of battery component to be to fill
The 5% of total electricity when full, both will not remaining excessive electricity cause electricity to waste, very few will not damage battery life.
Further, the power module is additionally provided with the electricity that makes a return voyage, the electricity of last block battery component≤make a return voyage
When electricity, the mainboard control module control unmanned plane makes a return voyage automatically.
It makes a return voyage automatically to guarantee to can be realized after unmanned plane during flying is gone out, the utility model is additionally provided with the electricity that makes a return voyage, institute
The setting for stating the electricity that makes a return voyage is that can have enough electricity realizations to make a return voyage automatically to guarantee unmanned plane after flight.The master
Plate control module can calculate the distance maked a return voyage according to location information, to judge the electricity for needing to make a return voyage, then control unmanned plane
Realization is maked a return voyage automatically.
Further, the electricity that makes a return voyage is the 30% of battery component total electricity.
Itself judgement of unmanned plane is made a fault in order to prevent, can also set the electricity that makes a return voyage, the electricity that makes a return voyage in advance
When remaining capacity for last group of battery component is 30% of total electricity when battery component is fully charged, the mainboard control module
Control unmanned plane makes a return voyage automatically.
Further, the battery component includes detachable battery and the battery holder equipped with battery interface, the battery
Seat is fixed on the side of unmanned aerial vehicle body.
For the ease of replacing battery, it is detachable structure that the battery, which is arranged, in the utility model.
Further, the battery holder is equipped with multiple groups ventilation opening, and the ventilation opening includes multiple air inlets set on side
With the multiple air outlets being located at the top.
Since battery is set in battery holder, a large amount of heat can be generated at work, it, can by the way that multiple ventilation openings are arranged
It realizes good heat dissipation, preferably optimizes cell operating conditions, improve service life.
Further, the battery interface is set to the upper end of battery holder and fuselage affixed side.
For the ease of installation and subsequent maintenance, battery interface is arranged and consolidates in battery holder and fuselage by the utility model
Determine the upper end of side, user can intuitively see whether battery connects completely, and also further battery seat goes wrong, and also facilitate from battery
Interface, which is started with, to be overhauled and is maintained.
Further, infrared inductor is equipped on front side of the fuselage, the rear side top of the fuselage is equipped with foldable day
Line, the folding direction of the antenna are to fold back.
The infrared inductor includes infrared transmitter and infrared remote receiver, is implemented in combination with keeping away for unmanned plane by the two
Hinder function.The rear side top that fuselage is arranged in the antenna is gone to vertical angles when it is desired to be used, when not needing to make
Used time is rotated backward and is accommodated just vertically downward direction.
The beneficial effects of the utility model
(1) the utility model setting multiple groups battery component parallel with one another, after the electricity of one group of battery component is finished,
Another battery continues as unmanned plane continuation of the journey, substantially prolongs the flight time of unmanned plane, increases the experience of user.
(2) the critical electricity can be configured according to handling characteristics, more have specific aim.The mainboard controls mould
Block, which controls, will start next battery component start-up operation while the battery component stops working, realize two battery components
Between seamless interfacing, ensure that the normal flight of unmanned plane.
(3) setting of the electricity that makes a return voyage ensure that unmanned plane in flight, can have enough electricity realizations to return automatically
Boat.The mainboard control module can calculate the distance maked a return voyage according to location information, thus judge the electricity for needing to make a return voyage, then
Control unmanned plane realization is maked a return voyage automatically.
(4) since battery is set in battery holder, a large amount of heat can be generated at work, by the way that multiple ventilation openings are arranged,
It can be realized good heat dissipation, preferably optimize cell operating conditions, improve service life.
Detailed description of the invention
Fig. 1 is the utility model power supply system schematic diagram.
Fig. 2 is the utility model unmanned plane perspective view.
Fig. 3 is the another perspective view of the utility model unmanned plane.
Fig. 4 is that the utility model unmanned plane takes out battery top view.
Fig. 5 is the another perspective view of the utility model unmanned plane.
Specific embodiment
To keep the purposes, technical schemes and advantages of the utility model implementation clearer, below in conjunction with the utility model
Attached drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the utility model.In the accompanying drawings, from beginning
Same or similar element or element with the same or similar functions are indicated to same or similar label eventually.Described reality
Applying example is the utility model a part of the embodiment, instead of all the embodiments.Below with reference to the embodiment of attached drawing description
It is exemplary, it is intended to for explaining the utility model, and should not be understood as limiting the present invention.It is practical new based on this
Embodiment in type, every other implementation obtained by those of ordinary skill in the art without making creative efforts
Example, fall within the protection scope of the utility model.The embodiments of the present invention are described in detail with reference to the accompanying drawing.
Embodiment
A kind of more battery pack unmanned plane power supply systems, as shown in Figure 1 and 2, the unmanned plane include fuselage 1, the unmanned plane
Power supply system includes the mainboard control module of power module and control power module work, and the power module includes multiple mutual
Battery component 2 in parallel, the unmanned aerial vehicle body side are equipped with the installation position of multiple battery components 2, and the battery component 2 is in length
Bar shaped, and be set in installation position vertically, each battery component 2 is electrically connected with mainboard control module respectively, so that mainboard control
Molding block can control the operation and stopping of multiple battery components 2, and the sequence that shares out the work.
The fuselage 1 is in approximate square shape, including four sides, wherein front side is equipped with the installation position of head assembly 3,
The head assembly 3 is set in installation position, mainboard control module and circuit element is equipped with inside the fuselage 1, by external
Remote controler or mobile terminal can connect mainboard control module, and realize the control to unmanned plane.
In order to increase the cruise duration of unmanned plane, multiple groups battery component 2 parallel with one another is arranged in the utility model, when one group
After the electricity of battery component 2 is finished, another battery continues as unmanned plane continuation of the journey, when substantially prolonging the flight of unmanned plane
Between, increase the experience of user.
The mainboard control module be set to fuselage 1 inside, can control the opening and closing of electric elements in unmanned plane with
And it uses.Each battery component 2 links with mainboard control module, and mainboard control module is enabled to control each battery
The starting and closing of component 2.
Therefore, the setting of multiple battery packs, control uses in a predetermined sequence, is able to extend the flight time.
Further, as shown in Fig. 2, the battery component 2 includes three battery components 2, the fuselage 1 includes front side,
Rear side, left and right side, three battery components 2 are respectively arranged on the left side, right side and rear side of fuselage 1.
In order to reduce the overall volume of unmanned plane, there are four rotor, the rotor intervals to be arranged for the utility model setting,
Middle battery component 2 is arranged between two rotor assemblies 4, and since battery pack excessively equally will increase the power consumption of unmanned plane,
Be unfavorable for continuing a journey for a long time instead, it is preferred that 3 groups of batteries are arranged in the utility model, be separately positioned on the left side of fuselage 1, right side and
Rear side, and the rear and front end in 1 left side of the fuselage is respectively provided with one group of folding rotor assemblies 4, the right side and a left side of the fuselage 1
Side symmetric position is equipped with two groups of folding rotor assemblies 4, and the rotor is proximal end close to 1 one end of fuselage, and the other end is distal end,
As shown in figure 5, the distal end of the rotor is equipped with Collapsible rack 41, when rotor and bracket 41 are unfolded simultaneously, the unmanned plane can
It smoothly places on the ground, when needing to store, bracket 41 and rotor can all be folded, reduce the overall volume of unmanned plane.
The battery pack of the utility model setting is vertically installed at the side of fuselage 1, and the length of the battery component 2 is less than machine
The height of body 1, the width of the battery component 2 are less than the horizontal distance of adjacent two rotor assemblies, 4 proximal end.So that the weight of fuselage 1
The heart is more concentrated on middle part, while reducing unmanned plane volume, so that flight is more stable.
Further, as shown in Figure 1, the power module is equipped with critical electricity, the electricity of the battery component 2≤critical
When electricity, the mainboard control module controls the battery component 2 and stops working, while starting next battery component 2.
In order to protect battery, avoids exhausting electricity every time and damaging battery, influence the service life of battery, this is practical
It is novel to be provided with critical electricity, by the way that the value of critical electricity is arranged in mainboard control module, when the battery component 2 to work
When remaining capacity≤critical electricity, the mainboard control module controls the battery component 2 and stops working.The critical electricity can
To be configured according to handling characteristics, more there is specific aim.The mainboard control module controls the battery component 2 and stops work
As while will start next battery component 2 and start to work, realize the seamless interfacing between two battery components 2, ensure that
The normal flight of unmanned plane.
Further, the critical electricity is the 5% of 2 total electricity of battery component.
According to general use demand, the utility model selects the critical electricity of setting to be for the remaining capacity of battery component 2
Full of when total electricity 5%, both will not remaining excessive electricity cause electricity to waste, very few will not damage battery life.
Further, the power module is additionally provided with the electricity that makes a return voyage, the electricity of last block battery component 2≤make a return voyage
When electricity, the mainboard control module control unmanned plane makes a return voyage automatically.
It makes a return voyage automatically to guarantee to can be realized after unmanned plane during flying is gone out, the utility model is additionally provided with the electricity that makes a return voyage, institute
The setting for stating the electricity that makes a return voyage is that can have enough electricity realizations to make a return voyage automatically to guarantee unmanned plane after flight.The master
Plate control module can calculate the distance maked a return voyage according to location information, to judge the electricity for needing to make a return voyage, then control unmanned plane
Realization is maked a return voyage automatically.
Further, the electricity that makes a return voyage is the 30% of 2 total electricity of battery component.
Itself judgement of unmanned plane is made a fault in order to prevent, can also set the electricity that makes a return voyage, the electricity that makes a return voyage in advance
When remaining capacity for last group of battery component 2 is 30% of total electricity when battery component 2 is fully charged, the mainboard controls mould
Block control unmanned plane makes a return voyage automatically.
Further, as shown in figure 4, the battery component 2 is including detachable battery 21 and equipped with battery interface 22
Battery holder 23, the battery holder are fixed on the side of unmanned aerial vehicle body 1.
For the ease of replacing battery, it is detachable structure that the battery 21, which is arranged, in the utility model.
Further, as shown in figure 5, the battery holder 23 is equipped with multiple groups ventilation opening 100, the ventilation opening 100 includes setting
Multiple air inlets in side and multiple air outlets for being located at the top.
Since battery 21 is set in battery holder 23, a large amount of heat can be generated at work, by the way that multiple ventilation openings are arranged
100, it can be realized good heat dissipation, preferably optimize cell operating conditions, improve service life.
Further, the battery interface 22 is set to the upper end of battery holder 23 and 1 affixed side of fuselage.
For the ease of installation and subsequent maintenance, battery interface 22 is arranged in battery holder 23 and machine the utility model
The upper end of 1 affixed side of body, user can intuitively see whether battery connects completely, and also further battery seat 23 goes wrong, also side
Just start with from battery interface 22 and overhauled and maintained.
Further, as shown in figure 5, being equipped with infrared inductor 5, the rear side top of the fuselage 1 on front side of the fuselage 1
Equipped with foldable antenna 6, the folding direction of the antenna 6 is to fold back.
The infrared inductor 5 includes infrared transmitter and infrared remote receiver, is implemented in combination with unmanned plane by the two
Barrier avoiding function.The rear side top that fuselage 1 is arranged in the antenna 6 is gone to vertical angles when it is desired to be used, when being not required to
It wants to be accommodated vertically downward direction in use, being rotated backward.
Embodiment of above is merely intended for describing the technical solutions of the present application, but not for limiting the present application, although referring to above preferably real
Mode is applied the utility model is described in detail, those skilled in the art should understand that, it can be practical new to this
The technical solution of type is modified or equivalent replacement should not all be detached from the spirit and scope of the technical scheme of the present invention.This field
Technical staff can also do the design that other variations etc. are used in the utility model within the spirit of the present invention, without departing from this
The technical effect of utility model.These changes made in accordance with the spirit of the present invention should all be included in the utility model
Within the scope of claimed.
Claims (10)
1. a kind of more battery pack unmanned plane power supply systems, the unmanned plane includes fuselage, which is characterized in that the unmanned plane power supply
System includes the mainboard control module of power module and control power module work, and the power module includes multiple parallel with one another
Battery component, the unmanned aerial vehicle body side be equipped with multiple battery components installation position, the battery component is elongated, and
It is set in installation position vertically, each battery component is electrically connected with mainboard control module respectively, enables mainboard control module
The operation and stopping of multiple battery components are enough controlled, and the sequence that shares out the work.
2. unmanned plane power supply system according to claim 1, which is characterized in that the battery component includes three battery packs
Part, the fuselage include front side, rear side, left and right side, three battery components be respectively arranged on the left side of fuselage, right side and
Rear side.
3. unmanned plane power supply system according to claim 1, which is characterized in that the power module is equipped with critical electricity,
When the electricity of the battery component≤critical electricity, the mainboard control module controls the battery component and stops working, simultaneously
Start next battery component.
4. unmanned plane power supply system according to claim 3, which is characterized in that the critical electricity is that battery component is always electric
The 5% of amount.
5. unmanned plane power supply system according to claim 1, which is characterized in that the power module is additionally provided with the electricity that makes a return voyage
Amount, when the electricity of last block battery component≤make a return voyage electricity, it is automatic that the mainboard control module controls the unmanned plane
It makes a return voyage.
6. unmanned plane power supply system according to claim 5, which is characterized in that the electricity that makes a return voyage is that battery component is always electric
The 30% of amount.
7. unmanned plane power supply system according to claim 1, which is characterized in that the battery component includes dismountable electricity
Pond and battery holder equipped with battery interface, the battery holder are fixed on the side of unmanned aerial vehicle body.
8. unmanned plane power supply system according to claim 7, which is characterized in that the battery holder is equipped with multiple groups ventilation opening,
The ventilation opening includes the multiple air outlets for being set to multiple air inlets of side and being located at the top.
9. unmanned plane power supply system according to claim 7, which is characterized in that the battery interface is set to battery holder and machine
The upper end of body affixed side.
10. unmanned plane power supply system according to claim 1, which is characterized in that be equipped with infrared induction on front side of the fuselage
Device, the rear side top of the fuselage are equipped with foldable antenna, and the folding direction of the antenna is to fold back.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820854385.1U CN208412154U (en) | 2018-06-04 | 2018-06-04 | A kind of more battery pack unmanned plane power supply systems |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201820854385.1U CN208412154U (en) | 2018-06-04 | 2018-06-04 | A kind of more battery pack unmanned plane power supply systems |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017221A (en) * | 2019-12-12 | 2020-04-17 | 张自明 | Aviation agricultural sprinkling irrigation unmanned aerial vehicle |
| CN111555401A (en) * | 2020-05-26 | 2020-08-18 | 天津市微卡科技有限公司 | Multi-battery power supply system for robot |
| CN115347336A (en) * | 2022-10-18 | 2022-11-15 | 中国空气动力研究与发展中心空天技术研究所 | Unmanned aerial vehicle distributed power battery |
-
2018
- 2018-06-04 CN CN201820854385.1U patent/CN208412154U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017221A (en) * | 2019-12-12 | 2020-04-17 | 张自明 | Aviation agricultural sprinkling irrigation unmanned aerial vehicle |
| CN111555401A (en) * | 2020-05-26 | 2020-08-18 | 天津市微卡科技有限公司 | Multi-battery power supply system for robot |
| CN115347336A (en) * | 2022-10-18 | 2022-11-15 | 中国空气动力研究与发展中心空天技术研究所 | Unmanned aerial vehicle distributed power battery |
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