CN109263979A - A kind of dual redundant power aerial vehicle - Google Patents
A kind of dual redundant power aerial vehicle Download PDFInfo
- Publication number
- CN109263979A CN109263979A CN201811259494.XA CN201811259494A CN109263979A CN 109263979 A CN109263979 A CN 109263979A CN 201811259494 A CN201811259494 A CN 201811259494A CN 109263979 A CN109263979 A CN 109263979A
- Authority
- CN
- China
- Prior art keywords
- battery pack
- rotor motor
- rack
- aerial vehicle
- vertical
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 230000009977 dual effect Effects 0.000 title claims abstract description 20
- 230000008878 coupling Effects 0.000 claims description 11
- 238000010168 coupling process Methods 0.000 claims description 11
- 238000005859 coupling reaction Methods 0.000 claims description 11
- 238000010586 diagram Methods 0.000 description 6
- 230000005611 electricity Effects 0.000 description 5
- 238000012544 monitoring process Methods 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 210000000554 iris Anatomy 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
-
- 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)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
The present invention provides a kind of dual redundant power aerial vehicle, including rack, four horns being arranged on the rack, the first rotor motor, the second rotor motor, is connected to first propeller on top on the first rotor motor output shaft, is connected to the second propeller of bottom end under the second rotor motor output shaft, the main circuit structure being arranged on the rack；Main circuit structure includes battery pack one, battery pack two, Horizontal tiltmeter circuit, power selection control, wireless remote control signals dual-mode antenna, and power selection control is electrically connected normally closed switch, normal open switch, Horizontal tiltmeter circuit, wireless remote control signals dual-mode antenna.Electronic horizon dipmeter circuit is arranged in dual redundant power aerial vehicle provided by the invention, and controller judges automatically the first power and deposits in the case of a fault, automatically switches to the progress of the second power drive aircraft, continues a journey and require when can adapt to long.
Description
Technical field
The present invention relates to unmanned vehicle technical fields, more particularly to a kind of dual redundant power aerial vehicle.
Background technique
Currently, being provided with double dynamical aircraft, therein double dynamical, one is storage battery power supply unit, and one is too
Positive energy charging unit, but in the case where sunlight effect is bad, in situation insufficient for battery power, solar energy
Electric energy can not just be replenished in time to battery.Therefore such double dynamical aircraft can not adapt to the weather condition at long-term cloudy day
Lower use.
Secondly, for using storage battery power supply and solar powered double dynamical aircraft, selection between two power,
It is that controllers are switched over by remote controler on the ground, the switching for action edge of going forward side by side can not be judged automatically.
Furthermore for using storage battery power supply and solar powered double dynamical aircraft, electric signal is exported in battery
In the case that circuit breaks down, it will be unable to realize flight, there are the risks of existing aircraft bombing.
Accordingly, it is desirable to provide a kind of dual redundant power aerial vehicle is to solve the above technical problems.
Summary of the invention
The invention mainly solves the technical problem of providing a kind of dual redundant power aerial vehicles, and electronic horizon dipmeter is arranged
Circuit, control panel judge automatically the first power and deposit in the case of a fault, automatically switch to the progress of the second power drive aircraft,
The requirement continued a journey when can adapt to long.
In order to solve the above technical problems, one technical scheme adopted by the invention is that providing a kind of dual redundant active flight
Device,
Including rack 1, four horns 2 being arranged in rack 1, upper and lower face that identical 2 tail end of horn is set
One rotor motor 3 and the second rotor motor 4, the first propeller 5 for being connected to top on 3 output shaft of the first rotor motor, connection
The second propeller 6 of bottom end, the main circuit structure being arranged in rack 1 under 4 output shaft of the second rotor motor；
Main circuit structure includes battery pack 1, battery pack 28, Horizontal tiltmeter circuit 12, is used in Horizontal tiltmeter electricity
The gradient that road 12 measures be more than predetermined value when closure normal open switch 10 and open normally closed switch 9 power selection control 11,
Wireless remote control signals dual-mode antenna 13, power selection control 11 are electrically connected normally closed switch 9, normal open switch 10, Horizontal tiltmeter
Circuit 12, wireless remote control signals dual-mode antenna 13；
Battery pack 1 is electrically connected normally closed switch 9 and the first rotor motor 3, and battery pack 28 is electrically connected normal open switch 10 and the
Two rotor motors 4, alternatively,
Pond group 1 is electrically connected normally closed switch 9 and the second rotor motor 4, and battery pack 28 is electrically connected normal open switch 10 and first
Rotor motor 3.
In embodiment, it is preferable that the rack 1 includes top plate 101 and bottom plate 102, and battery pack 1, battery pack 28 are set
Set on 101 top surface of top plate, power selection control 11, Horizontal tiltmeter circuit 12, wireless remote control signals dual-mode antenna 13, often
Make and break closes 9, normal open switch 10,2 inner end of horn between top plate 101 and bottom plate 102.
In embodiment, it is preferable that top plate 101 and bottom plate 102 distinguish rounded, the battery pack 1 and the difference of battery pack 28
Including three secondary battery units in parallel, and battery pack 1 and battery pack 28 are perpendicular about one for crossing the vertical central axes of rack 1
It is symmetrical to split.
In embodiment, it is preferable that a vertical locating rod 22 is respectively arranged on four horns, 2 inner end, it is described perpendicular
To 22 top holding of locating rod in the corresponding vertical hole on top plate 101, bottom end holding corresponding vertical hole on bottom plate 102
It is interior, and the distance value of four vertical locating rods 22 to the vertical central axes of rack 1 is equal.
In embodiment, it is preferable that the vertical supporting plate 103 there are two face is set on 101 top surface of top plate, and described two perpendicular
It is symmetrical about the vertical central axis of the top plate 101 to support plate 103, top cover is connected at the top of the rack 1.
In embodiment, it is preferable that each horn 2 is provided with a supporting leg 21 on the part of rack 1.
In embodiment, it is preferable that be provided with Coupling 23 at the top of the supporting leg 21, the Coupling 23 is socketed in horn 2
On, wherein Coupling 23 includes the upper and lower two vertical parts being spirally connected using lateral screw.
The beneficial effects of the present invention are: a kind of dual redundant power aerial vehicle provided by the invention, setting electronic horizon is tilted
Instrument circuit, control panel judge automatically the first power and deposit in the case of a fault, automatically switch to the second power drive aircraft into
Row, the requirement continued a journey when can adapt to long.
Detailed description of the invention
Fig. 1 is a kind of overlooking structure diagram of the first preferred embodiment of dual redundant power aerial vehicle of the invention；
Fig. 2 is the schematic perspective view of dual redundant power aerial vehicle shown in FIG. 1；
Fig. 3 is the enlarged structure schematic diagram that Fig. 2 centre circle B irises out part；
Fig. 4 is the enlarged structure schematic diagram of 1 part of rack in Fig. 2；
Fig. 5 is the enlarged structure schematic diagram that Fig. 2 centre circle A irises out part；
Fig. 6 is a kind of circuit structure block diagram of dual redundant power aerial vehicle of the invention.
It is as follows that number in Figure of description identifies corresponding component names difference:
1- rack；101- top plate；102- bottom plate；103- vertical supporting plate；2- horn；21- supporting leg；22- is vertically positioned
Bar；23- Coupling；The first rotor motor of 3-；The second rotor motor of 4-；The first propeller of 5-；The second propeller of 6-；7- battery pack
One；8- battery pack two；9- normally closed switch；10- normal open switch；11- power selection control；12- Horizontal tiltmeter circuit；13-
Wireless remote control signals dual-mode antenna.
Specific embodiment
Technical solution of the present invention is described in detail below with reference to diagram.
Referring to Figure 1, shown in Fig. 2, Fig. 3, the dual redundant power aerial vehicle of the present embodiment, including rack 1, setting are in rack
The first rotor motor 3 that identical 2 tail end of horn is arranged in and the second rotor motor 4 of four horns 2, upper and lower face on 1 connect
It connects first propeller 5 on the top on 3 output shaft of the first rotor motor, be connected to bottom end under 4 output shaft of the second rotor motor
Second propeller 6, the main circuit structure being arranged in rack 1；
As shown in fig. 6, main circuit structure includes battery pack 1, battery pack 28, Horizontal tiltmeter circuit 12, is used in water
It is closed normal open switch 10 when the gradient that flat dip instrument circuit 12 measures is more than predetermined value and opens the power selection of normally closed switch 9
Controller 11, wireless remote control signals dual-mode antenna 13, power selection control 11 are electrically connected normally closed switch 9, normal open switch 10, water
Flat dip instrument circuit 12, wireless remote control signals dual-mode antenna 13；
Please referring further to Fig. 6, battery pack 1 is electrically connected normally closed switch 9 and the first rotor motor 3, battery pack 28 are electrically connected
Normal open switch 10 and the second rotor motor 4 are connect, alternatively,
Pond group 1 is electrically connected normally closed switch 9 and the second rotor motor 4, and battery pack 28 is electrically connected normal open switch 10 and first
Rotor motor 3；
Therefore, it allows the first propeller 5 still to allow the second propeller 6 as the flying power under normality, is that designer is setting
Timing, can be without limitation with unrestricted choice.
In the present embodiment, Horizontal tiltmeter circuit 12 is used to monitor the gradient of the rack 1 of aircraft, and monitoring
Inclination data is transferred to power selection control 11, and the power selection control 11 is by the inclination data of the monitoring and in advance
A fixed predetermined value (critical value) compares, and when showing that the gradient monitored has been more than predetermined value, issues control
Instruction cuts off the supplying power for outside circuit of battery pack 1 so that the opening of normally closed switch 9；Corresponding closure normal open switch 10, closure electricity
The supplying power for outside circuit of pond group 28.
It therefore, is monitoring data of the power selection control 11 according to Horizontal tiltmeter circuit 12, automatically in the present embodiment
Switch supplying cell group and provide operating voltage for corresponding rotor motor, to guarantee the prolonged duration flight of aircraft.Only
It wants, as soon as in the case where 7 electricity shortage of battery pack or power supply circuit are broken down, entire aircraft will appear inclination angle
Degree significantly alters, and for Horizontal tiltmeter circuit 12 when the gradient for monitoring aircraft is more than predetermined value, immediately starting is electric
Pond group 28 provides power for the long-time continuation of the journey of aircraft.
In the present embodiment, automatically switch the continuation of the journey mode of power battery pack, carries out remote manual control without ground staff, so that
When aircraft one 7 electric power of battery pack in flight course is insufficient or output electrical signal circuitry breaks down, it is switched to electricity in time
Pond group 28 is powered, so that aircraft be avoided the generation of aircraft bombing harsh conditions occur.
Please referring further to shown in Fig. 1 and Fig. 2, in embodiment, it is preferable that the rack 1 includes top plate 101 and bottom plate
102, battery pack 1, battery pack 28 be arranged on 101 top surface of top plate, power selection control 11, Horizontal tiltmeter circuit 12,
Wireless remote control signals dual-mode antenna 13, normally closed switch 9, normal open switch 10,2 inner end of horn be located at top plate 101 and bottom plate 102 it
Between.Certainly, in other embodiments of the invention, power selection control 11, Horizontal tiltmeter circuit 12, wireless remote control signals
Dual-mode antenna 13, normally closed switch 9, normal open switch 10 also can be set on the bottom surface of bottom plate 102, without limitation.
In an embodiment of the present invention, it is preferable that top plate 101 and bottom plate 102 distinguish rounded, the battery pack 1 and electricity
Pond group 28 respectively includes three secondary battery units in parallel, and battery pack 1 and battery pack 28 are about the vertical axis of rack 1 excessively
The vertical split of one of line is symmetrical.
As shown in figure 4, in embodiment, it is preferable that be respectively arranged with a vertical locating rod on four horns, 2 inner end
22, the vertical 22 top holding of locating rod is in the corresponding vertical hole on top plate 101, bottom end holding is right on bottom plate 102
In the vertical hole answered, and the distance value of four vertical locating rods 22 to the vertical central axes of rack 1 is equal.When installing horn 2, erect
The inner end of horn 2 can be limited in advance to locating rod 22, then horn 2 is carried out close to the part of the edge of rack 1
Installation positioning, in this way, the accuracy that the direction that just can be improved horn 2 limits, reduces the installation difficulty of horn 2.
Please referring further to Fig. 1 and Fig. 4, in embodiment, it is preferable that be arranged that there are two the vertical of face on 101 top surface of top plate
Support plate 103, two vertical supporting plates 103 are symmetrical about the vertical central axis of the top plate 101, the rack 1
Top is connected with top cover (not shown).The setting of the vertical supporting plate 103 is to prevent top cover to be pressed onto when installing top cover
Battery pack 1 and battery pack 28, effective protection circuit structure.
Fig. 2 and Fig. 5 are please referred to, in embodiment, it is preferable that each horn 2 is provided with one on the part of rack 1
Supporting leg 21.Certainly, in other embodiments of the invention, the position of supporting leg 21 also can be set in the bottom of bottom plate 102
On face.
As shown in figure 5, in embodiment, it is preferable that be provided with Coupling 23,23 sets of the Coupling at the top of the supporting leg 21
It connects on horn 2, wherein Coupling 23 includes the upper and lower two vertical parts being spirally connected using lateral screw.Utilize lateral spiral shell
Two parts that silk is spirally connected constitute Coupling 23, so just facilitate the installation and removal to supporting leg 21.
The above description is only an embodiment of the present invention, is not intended to limit the scope of the invention, all to utilize this hair
Equivalent structure made by bright specification and accompanying drawing content is applied directly or indirectly in other relevant technical fields, similarly
It is included within the scope of the present invention.
Claims (7)
1. a kind of dual redundant power aerial vehicle, it is characterised in that:
Setting including rack (1), four horns (2), upper and lower face that are arranged on rack (1) is in identical horn (2) tail end
The first rotor motor (3) and the second rotor motor (4), the first spiral shell for being connected to top on the first rotor motor (3) output shaft
Rotation paddle (5), the master for being connected to the second propeller (6) of bottom end under the second rotor motor (4) output shaft, being arranged on rack (1)
Circuit structure；
Main circuit structure includes battery pack one (7), battery pack two (8), Horizontal tiltmeter circuit (12), is used in Horizontal tiltmeter
It is closed normal open switch (10) when the gradient that circuit (12) measures is more than predetermined value and opens the power selection control of normally closed switch (9)
Device (11) processed, wireless remote control signals dual-mode antenna (13), power selection control (11) electrical connection normally closed switch (9) normally opened are opened
Close (10), Horizontal tiltmeter circuit (12), wireless remote control signals dual-mode antenna (13)；
Battery pack one (7) is electrically connected normally closed switch (9) and the first rotor motor (3), and battery pack two (8) is electrically connected normal open switch
(10) and the second rotor motor (4), alternatively,
Chi Zuyi (7) is electrically connected normally closed switch (9) and the second rotor motor (4), and battery pack two (8) is electrically connected normal open switch (10)
With the first rotor motor (3).
2. dual redundant power aerial vehicle according to claim 1, it is characterised in that: the rack (1) includes top plate
(101) it is arranged on top plate (101) top surface with bottom plate (102), battery pack one (7), battery pack two (8), power selection control
(11), Horizontal tiltmeter circuit (12), wireless remote control signals dual-mode antenna (13), normally closed switch (9), normal open switch (10), machine
Arm (2) inner end is located between top plate (101) and bottom plate (102).
3. dual redundant power aerial vehicle according to claim 2, it is characterised in that: top plate (101) and bottom plate (102) are respectively
Rounded, the battery pack one (7) and battery pack two (8) respectively include three secondary battery units in parallel, and battery pack one (7)
It is symmetrical about a vertical split for crossing rack (1) vertical central axes with battery pack two (8).
4. dual redundant power aerial vehicle according to claim 3, it is characterised in that: on four horns (2) inner end
It is respectively arranged with a vertical locating rod (22), vertical locating rod (22) the top holding is corresponding on top plate (101)
In vertical hole, bottom end holding on bottom plate (102) in corresponding vertical hole, and four vertical locating rods (22) are erected to rack (1)
Distance value to central axes is equal.
5. dual redundant power aerial vehicle according to claim 3, it is characterised in that: be provided with two on top plate (101) top surface
The vertical supporting plate (103) of a face, vertical center of two vertical supporting plates (103) about the top plate (101)
Axisymmetrical, rack (1) top are connected with top cover.
6. dual redundant power aerial vehicle described in -5 any one according to claim 1, it is characterised in that: each horn
(2) supporting leg (21) is provided on the part of rack (1).
7. dual redundant power aerial vehicle according to claim 6, it is characterised in that: be provided at the top of the supporting leg (21)
Coupling (23), the Coupling (23) are socketed on horn (2), wherein Coupling (23) includes upper and lower two vertical benefits
The part being spirally connected with lateral screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811259494.XA CN109263979A (en) | 2018-10-26 | 2018-10-26 | A kind of dual redundant power aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811259494.XA CN109263979A (en) | 2018-10-26 | 2018-10-26 | A kind of dual redundant power aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109263979A true CN109263979A (en) | 2019-01-25 |
Family
ID=65194740
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811259494.XA Pending CN109263979A (en) | 2018-10-26 | 2018-10-26 | A kind of dual redundant power aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN109263979A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112078805A (en) * | 2020-08-25 | 2020-12-15 | 飞的科技有限公司 | Electric drive system and electric energy drive equipment |
Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204489196U (en) * | 2015-02-12 | 2015-07-22 | 深圳大学 | The many rotor wing unmanned aerial vehicles of a kind of fuels and energy |
| CN105253301A (en) * | 2015-09-28 | 2016-01-20 | 深圳一电科技有限公司 | Flight control method and apparatus for multiaxial flight vehicle |
| CN106165235A (en) * | 2015-06-30 | 2016-11-23 | 深圳市大疆创新科技有限公司 | A kind of battery management method, cell, flight control system and unmanned plane |
| US9527588B1 (en) * | 2012-09-28 | 2016-12-27 | Scott B. Rollefstad | Unmanned aircraft system (UAS) with active energy harvesting and power management |
| CN106414238A (en) * | 2014-03-13 | 2017-02-15 | 多韧***有限责任公司 | UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods |
| CN106716776A (en) * | 2016-02-26 | 2017-05-24 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle, and power supply system, method and device thereof |
| CN107077142A (en) * | 2016-10-25 | 2017-08-18 | 深圳市大疆创新科技有限公司 | Multi-rotor aerocraft and its control method, control device and flight control system |
| CN107219757A (en) * | 2017-07-30 | 2017-09-29 | 吴述梗 | One kind is electronic to be tethered at many rotor redundant power system architectures and control method |
| CN107352018A (en) * | 2017-06-30 | 2017-11-17 | 浙江大学 | A kind of folding unmanned plane undercarriage |
| CN107458595A (en) * | 2017-09-05 | 2017-12-12 | 南京荣骏科技发展有限公司 | A kind of oil electricity mixes heavily loaded multirotor helicopter |
| KR101815647B1 (en) * | 2016-10-27 | 2018-01-08 | 청주대학교 산학협력단 | Drone easy to safe landing |
| KR20180015985A (en) * | 2016-08-04 | 2018-02-14 | 권태욱 | Device for switching flight control for fall protection for drone |
| JP2018050419A (en) * | 2016-09-23 | 2018-03-29 | 第一精工株式会社 | Failure detection device and unmanned airplane |
| US20180134379A1 (en) * | 2015-04-19 | 2018-05-17 | Prodrone Co., Ltd. | Unmanned aerial vehicle |
| CN207631468U (en) * | 2017-12-21 | 2018-07-20 | 中交遥感天域科技江苏有限公司 | A kind of novel horn contraction structure |
| CN108602558A (en) * | 2015-12-21 | 2018-09-28 | 空客直升机德国有限公司 | Multi-rotor aerocraft |
| CN108614573A (en) * | 2018-05-15 | 2018-10-02 | 上海扩博智能技术有限公司 | The automatic fault tolerant attitude control method of six rotor wing unmanned aerial vehicles |
| CN209037854U (en) * | 2018-10-26 | 2019-06-28 | 珠海银通无人机科技有限公司 | A kind of dual redundant power aerial vehicle |
-
2018
- 2018-10-26 CN CN201811259494.XA patent/CN109263979A/en active Pending
Patent Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9527588B1 (en) * | 2012-09-28 | 2016-12-27 | Scott B. Rollefstad | Unmanned aircraft system (UAS) with active energy harvesting and power management |
| CN106414238A (en) * | 2014-03-13 | 2017-02-15 | 多韧***有限责任公司 | UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods |
| CN204489196U (en) * | 2015-02-12 | 2015-07-22 | 深圳大学 | The many rotor wing unmanned aerial vehicles of a kind of fuels and energy |
| US20180134379A1 (en) * | 2015-04-19 | 2018-05-17 | Prodrone Co., Ltd. | Unmanned aerial vehicle |
| CN106165235A (en) * | 2015-06-30 | 2016-11-23 | 深圳市大疆创新科技有限公司 | A kind of battery management method, cell, flight control system and unmanned plane |
| CN105253301A (en) * | 2015-09-28 | 2016-01-20 | 深圳一电科技有限公司 | Flight control method and apparatus for multiaxial flight vehicle |
| CN108602558A (en) * | 2015-12-21 | 2018-09-28 | 空客直升机德国有限公司 | Multi-rotor aerocraft |
| CN106716776A (en) * | 2016-02-26 | 2017-05-24 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle, and power supply system, method and device thereof |
| KR20180015985A (en) * | 2016-08-04 | 2018-02-14 | 권태욱 | Device for switching flight control for fall protection for drone |
| JP2018050419A (en) * | 2016-09-23 | 2018-03-29 | 第一精工株式会社 | Failure detection device and unmanned airplane |
| CN107077142A (en) * | 2016-10-25 | 2017-08-18 | 深圳市大疆创新科技有限公司 | Multi-rotor aerocraft and its control method, control device and flight control system |
| KR101815647B1 (en) * | 2016-10-27 | 2018-01-08 | 청주대학교 산학협력단 | Drone easy to safe landing |
| CN107352018A (en) * | 2017-06-30 | 2017-11-17 | 浙江大学 | A kind of folding unmanned plane undercarriage |
| CN107219757A (en) * | 2017-07-30 | 2017-09-29 | 吴述梗 | One kind is electronic to be tethered at many rotor redundant power system architectures and control method |
| CN107458595A (en) * | 2017-09-05 | 2017-12-12 | 南京荣骏科技发展有限公司 | A kind of oil electricity mixes heavily loaded multirotor helicopter |
| CN207631468U (en) * | 2017-12-21 | 2018-07-20 | 中交遥感天域科技江苏有限公司 | A kind of novel horn contraction structure |
| CN108614573A (en) * | 2018-05-15 | 2018-10-02 | 上海扩博智能技术有限公司 | The automatic fault tolerant attitude control method of six rotor wing unmanned aerial vehicles |
| CN209037854U (en) * | 2018-10-26 | 2019-06-28 | 珠海银通无人机科技有限公司 | A kind of dual redundant power aerial vehicle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112078805A (en) * | 2020-08-25 | 2020-12-15 | 飞的科技有限公司 | Electric drive system and electric energy drive equipment |
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