CN106697274A - Six-rotor wing unmanned aerial vehicle - Google Patents
Six-rotor wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106697274A CN106697274A CN201710042478.4A CN201710042478A CN106697274A CN 106697274 A CN106697274 A CN 106697274A CN 201710042478 A CN201710042478 A CN 201710042478A CN 106697274 A CN106697274 A CN 106697274A
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- fuselage
- motor
- unmanned aerial
- rotor wing
- wing unmanned
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- 230000005484 gravity Effects 0.000 claims abstract description 7
- 239000000446 fuel Substances 0.000 claims description 13
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 9
- 229910052739 hydrogen Inorganic materials 0.000 claims description 9
- 239000001257 hydrogen Substances 0.000 claims description 9
- 230000036647 reaction Effects 0.000 claims description 8
- 239000002828 fuel tank Substances 0.000 claims description 7
- 239000007789 gas Substances 0.000 claims description 7
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 6
- 229910052744 lithium Inorganic materials 0.000 claims description 6
- 230000005611 electricity Effects 0.000 claims description 4
- 210000001015 abdomen Anatomy 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 8
- 238000013461 design Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 229910001416 lithium ion Inorganic materials 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
Classifications
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- 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
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
-
- 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
- B64D47/00—Equipment not otherwise provided for
-
- 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
-
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention relates to a six-rotor wing unmanned aerial vehicle, and belongs to the technical field of aircrafts. The six-rotor wing unmanned aerial vehicle comprises a streamlined body, wherein two side jib arms and two tail jib arms are fixedly mounted on the body; the two side jib arms are both L-shaped; a front motor is mounted at an end part, in the position of the head of the body, of each side jib arm; a middle motor is mounted in a side surface position on the body, of each side jib arm; a tail motor is mounted on each tail jib arm; propellers are mounted on the front motor, the middle motor and the tail motor; the gravity center of the body is lower than the plane of the propellers; hanging rods are fixedly mounted at the belly of the body; the hanging rods extend to the direction of the tail part of the body from the direction of the head part of the body; and a power source is mounted on the body. The six-rotor wing unmanned aerial vehicle is capable of solving the technical problem that a conventional aircraft is poor in hanging property, and can be widely applied to aircrafts.
Description
Technical field
The present invention relates to vehicle technology field, and in particular to a kind of six rotor wing unmanned aerial vehicle.
Background technology
Six rotor wing unmanned aerial vehicles are a kind of miniature self-service flight for possessing the flexible flying quality advantage such as vertical lift, hovering
Device, there is practicality more more preferable than fixed-wing unmanned plane in some environments.It is provided by six motor of circumference
Power, attitude is adjusted by changing variable rotor speed, and position control is further realized by adjusting attitude, excellent with hovering performance
It is different, mobile flexibly, compact mechanical structure, part reliability high the advantages of, also therefore all have in military and civilian field wide
Wealthy application prospect.
By the development of several years, six rotor wing unmanned aerial vehicles have occurred in that variform, but still suffer from universal defect, such as
Carry ability is on the weak side, and the mission payload that most of six rotor wing unmanned aerial vehicles can only be carried within 3 kilograms performs task, and due to design
Theory falls behind, and carry mode is single, has rigors to task device；On the other hand, the energy density of lithium battery is limited by,
Cruise for a long time cannot be realized, which also limits the highly effective of six rotor wing unmanned aerial vehicles.
Current small and medium size unmanned aerial vehicles, multiaxis (especially with six axles typical case) occupies most of application market, but power
System still uses conventional lithium ion battery, and the energy density of lithium battery is relatively low compared to emerging energy (such as hydrogen fuel cell), closely
2 years with hydrogen fuel cell, oil electric mixed dynamic technology automotive field large-scale application, both power technologies are
Tend to ripe, but be constrained to volume, can not flexibly be reequiped on existing multiaxis unmanned plane, market is called and uses emerging power
The arrival of technology unmanned plane.
Therefore, based on drawbacks described above, in vehicle technology field, still suffer from studying and improved for six rotor wing unmanned aerial vehicles
Demand, this is also a study hotspot and emphasis in current vehicle technology field, and what even more the present invention was accomplished sets out
Point.
The content of the invention
It is an object of the invention to provide a kind of six rotor wing unmanned aerial vehicle, it is used to solve the skill of conventional aircraft carry ability
Art problem.
In order to solve the above technical problems, the technical scheme is that, there is provided a kind of six rotor wing unmanned aerial vehicle, including it is streamlined
Fuselage, two side horns and two tail horns are installed with the fuselage, two side horns are L-shaped, each
The end that the side horn is located at the Handpiece Location of the fuselage is mounted on an anterior motor, and each described side horn is located at institute
The lateral location for stating fuselage is mounted on a middle part motor, is mounted on an afterbody motor on each described tail horn, it is described before
Propeller, the plane of the center of gravity less than the propeller of the fuselage are mounted on portion's motor, middle part motor and afterbody motor；
The ventral of the fuselage is installed with carry bar, the carry bar from the fuselage tail from heading to the fuselage
Direction extends；Power source is installed, the power source connects the anterior motor, middle part motor and afterbody respectively on the fuselage
Motor.
Used as a kind of optimal technical scheme, the anterior motor, middle part motor and afterbody motor circularize array arrangement, and
3 degree of angles are provided between the mounting plane of the anterior motor, middle part motor and afterbody motor and the horizontal plane of the fuselage.
Used as a kind of optimal technical scheme, the side horn relative to the horizontal plane of the fuselage there is 8 degree upwarp to incline
Angle.
Used as a kind of optimal technical scheme, the side horn has 3 degree of angle of sweep with fuselage junction.
Used as a kind of optimal technical scheme, the tail horn relative to the horizontal plane of the fuselage there is 8 degree upwarp to incline
Angle.
Used as a kind of optimal technical scheme, the tail position of the Handpiece Location of the fuselage and the fuselage is mounted on
GPS module.
As a kind of optimal technical scheme, undercarriage is installed on the fuselage, the undercarriage is installed on the fuselage
Ventral position.
Used as another optimal technical scheme, the power source includes the lithium battery being arranged in the cabin of the fuselage.
Used as another optimal technical scheme, the power source includes the hydrogen storage gas being arranged in the cabin of the fuselage
Tank, mounts the fuel cell reaction pile for connecting the hydrogen storage gas tank, the fuel cell reaction pile on the carry bar
Respectively with the anterior motor, middle part motor and afterbody motor connection.
Used as another optimal technical scheme, the power source includes the fuel tank being arranged in the cabin of the fuselage, institute
State and the dynamic generator of the oil for connecting the fuel tank mounted on carry bar, the dynamic generator of oil respectively with the anterior motor, in
Portion's motor and afterbody motor connection.
The invention has the advantages that：
(1) ventral of fuselage of the present invention is installed with carry bar, compared with a traditional mount point, carry bar
Set and cause that enough mobile spaces are had on the bearing of trend of fuselage by extension object, therefore can be by adjusting by extension object
Position, and change the position of body nodal point, not only considerably increase carry ability, and also help adjustment balance so that
The present invention is more steady in flight course.
(2) due to being provided with 3 degree of angles between the mounting plane of motor and the horizontal plane of fuselage, different from side horn and tail machine
Arm upwarps angle, it is ensured that reduce loss in efficiency while stability.
(3) there is 3 degree of angle of sweep due to side horn and fuselage junction, two reaction torques of middle part motor are balanced,
Improve the stability in flight course.
(4) because the Handpiece Location of fuselage and the tail position of fuselage are mounted on GPS module, to instead of easily be subject to and do
The magnetic compass module disturbed, double difference location method is formed using front and rear GPS module, and high accuracy is high, realizes to course, the accurate survey of attitude
Amount.
Brief description of the drawings
Fig. 1 is the structural representation of the embodiment of the present invention one.
Fig. 2 is the floating state figure of the embodiment of the present invention one.
Fig. 3 is the forward traveling figure of the embodiment of the present invention one.
Fig. 4 is the structural representation of the embodiment of the present invention three.
Fig. 5 is the structural representation of the embodiment of the present invention four.
In figure：1st, fuselage, 101, head, 102, tail, 103, ventral, 104, cabin, 2, side horn, 3, tail horn, 4,
Middle part motor, 5, anterior motor, 6, afterbody motor, 7, propeller, 8, carry bar, 9, undercarriage, 10, GPS module, 11, hydrogen storage
Gas tank, 12, fuel cell reaction pile, 13, fuel tank, 14, the dynamic generator of oil.
Specific embodiment
Following examples are used to illustrate the present invention, but are not limited to the scope of the present invention.
Embodiment one
As shown in Figure 1, Figure 2 and Figure 3, the invention provides a kind of six rotor wing unmanned aerial vehicle, including fairshaped fuselage 1, machine
Two side horns 2 and two tail horns 3 are installed with body 1, two side horns 2 are L-shaped, each side horn 2 is located at machine
The end of the position of head 101 of body 1 is mounted on an anterior motor 5, and the lateral location that each side horn 2 is located at fuselage 1 is pacified
Equipped with a middle part motor 4, an afterbody motor 6, anterior motor 5, middle part motor 4 and afterbody electricity are mounted on each tail horn 3
Propeller 7, the plane of the center of gravity less than propeller 7 of fuselage 1, so as to obtain more preferable stability are mounted on machine 6；Fuselage 1
Ventral 103 be installed with carry bar 8, carry bar 8 has a left and right two, two carry bars 8 connect by three sections of straight carbon pipes and
Into curve carbon pipe composition, carry bar 8 extends from the direction of head 101 of fuselage 1 to the direction of tail 102 of fuselage 1, and and fuselage
1 it is streamlined consistent, compared with a traditional mount point, the setting of carry bar 8 cause by extension object fuselage 1 extension
There is enough mobile spaces on direction, therefore by adjusting by the position of extension object, and the position of the center of gravity of fuselage 1 can be changed
Put, not only considerably increase carry ability, and also help adjustment balance so that the present invention more puts down in flight course
Surely；Power source is installed, power source connects anterior motor 5, middle part motor 4 and afterbody motor 6 respectively on fuselage 1.
Side horn 2 has 8 degree and upwarps inclination angle, level of the tail horn 3 relative to fuselage 1 relative to the horizontal plane of fuselage 1
Face has 8 degree and upwarps inclination angle.Two anterior motors 5 are located at the direction position of head 101 of fuselage 1, and two afterbody motors 6 are located at fuselage
The 1 direction position of tail 102, anterior motor 5, middle part motor 4 and afterbody motor 6 circularize array arrangement, two adjacent motors
Between angle be 60 degree, and anterior motor 5, middle part motor 4 and afterbody motor 6 mounting plane and the horizontal plane of fuselage 1
Between be provided with 3 degree of angles, upwarp angle different from side horn 2 and tail horn 3, it is ensured that efficiency is reduced while stability
Loss.When unmanned plane normally hovers or places, fuselage 1 upwarps forward 8 degree, when unmanned plane is in cruising flight forward, machine
Body 1 upwarps angle and diminishes, and forms streamlined, reduces forward flight resistance, and due to the reasonable design of the curve of fuselage 1, lift is big,
So as to further lift flight efficiency.
Side horn 2 has 3 degree of angle of sweep with the junction of fuselage 1, and the angle of sweep is to balance two middle part motors 4
Reaction torque, improves the stability in flight course.
The position of head 101 of fuselage 1 and the position of tail 102 of fuselage 1 are mounted on GPS module 10, use front and rear GPS moulds
Block 10 forms double difference location method, and high precision is realized, to course, the measurement of attitude, instead of the magnetic compass mould being easily interfered
Block.
Undercarriage 9 is installed, undercarriage 9 is installed on the position of ventral 103 of fuselage 1 on fuselage 1, is supported from taking off when landing
Effect, its structure uses connect-disconnect structure commonly used in the art, can be easy to use with fast insert-pull.
The present invention further provided with emergency parachute, and positioned at the rear deck of fuselage 1, emergency parachute uses modularized design,
Used during using non-fuel cell dynamical system, be inserted directly into and use, its concrete structure and mounting means are more commonly used, ability
Field technique personnel can use for reference prior art, will not be repeated here.
Embodiment two
As shown in Figure 1, Figure 2 and Figure 3, the invention provides a kind of six rotor wing unmanned aerial vehicle, its structure is basic with embodiment one
Identical, its difference is that power source includes the lithium battery being arranged in the cabin 104 of fuselage 1, and it is tradition to be continued a journey using lithium battery
Technology, will not be repeated here.
Embodiment three
As shown in Figure 1, Figure 2 and Figure 4, the invention provides a kind of six rotor wing unmanned aerial vehicle, its structure is basic with embodiment one
Identical, its difference is that power source includes the hydrogen storage gas tank 11 being arranged in the cabin 104 of fuselage 1, has been mounted on carry bar 8
The fuel cell reaction pile 12 of connection hydrogen storage gas tank 11, the usual carry of fuel cell reaction pile 12 in the afterbody of carry bar 8,
Fuel cell reaction pile 12 is connected with anterior motor 5, middle part motor 4 and afterbody motor 6 respectively, has used emerging energy, enters
One step improves cruising ability, wherein, position of the fuel cell reaction pile 12 on carry bar 8 also can according to task carry and
The flexible carry of center of gravity requirement.
Example IV
As shown in Figure 1, Figure 2 with shown in Fig. 5, the invention provides a kind of six rotor wing unmanned aerial vehicle, its structure is basic with embodiment one
Identical, its difference is that power source includes the fuel tank 13 being arranged in the cabin 104 of fuselage 1, and connection has been mounted on carry bar 8
The dynamic generator 14 of the oil of fuel tank 13, the generally dynamic carry of generator 14 of oil in the afterbody of carry bar 8, the dynamic generator 14 of oil respectively with it is preceding
Portion's motor 5, middle part motor 4 and afterbody motor 6 are connected, and have used fuel power, further increase cruising ability, wherein, oil
Dynamic position of the generator 14 on carry bar 8 also can be according to task carry and the flexible carry of center of gravity requirement.
Although the present invention is described in detail above to have used general explanation and specific embodiment, at this
On the basis of invention, it can be made some modifications or improvements, this will be apparent to those skilled in the art.Therefore,
These modifications or improvements, belong to the scope of protection of present invention without departing from theon the basis of the spirit of the present invention.
Claims (10)
1. a kind of six rotor wing unmanned aerial vehicle, including fairshaped fuselage, it is characterised in that two sides are installed with the fuselage
Horn and two tail horns, two side horns are L-shaped, and each described side horn is located at the Handpiece Location of the fuselage
End is mounted on an anterior motor, and the lateral location that each described side horn is located at the fuselage is mounted on a middle part electricity
Machine, is mounted on an afterbody motor on each described tail horn, be respectively mounted on the anterior motor, middle part motor and afterbody motor
There are propeller, the plane of the center of gravity less than the propeller of the fuselage；The ventral of the fuselage is installed with carry bar, institute
Carry bar is stated to be extended to the tail direction of the fuselage from the heading of the fuselage；Power source is installed on the fuselage,
The power source connects anterior motor, middle part motor and afterbody motor respectively.
2. six rotor wing unmanned aerial vehicle as claimed in claim 1, it is characterised in that the anterior motor, middle part motor and afterbody electricity
Machine circularizes array arrangement, and mounting plane and the fuselage of the anterior motor, middle part motor and afterbody motor level
3 degree of angles are provided between face.
3. six rotor wing unmanned aerial vehicle as claimed in claim 1, it is characterised in that level of the side horn relative to the fuselage
Face has 8 degree and upwarps inclination angle.
4. six rotor wing unmanned aerial vehicle as claimed in claim 3, it is characterised in that the side horn has 3 degree with fuselage junction
Angle of sweep.
5. six rotor wing unmanned aerial vehicle as claimed in claim 1, it is characterised in that level of the tail horn relative to the fuselage
Face has 8 degree and upwarps inclination angle.
6. six rotor wing unmanned aerial vehicle as claimed in claim 1, it is characterised in that the Handpiece Location of the fuselage and the fuselage
Tail position is mounted on GPS module.
7. six rotor wing unmanned aerial vehicle as claimed in claim 1, it is characterised in that undercarriage, described are provided with the fuselage
The frame that falls is installed on the ventral position of the fuselage.
8. six rotor wing unmanned aerial vehicles as described in claim 1 to 7 any one claim, it is characterised in that the power source bag
Include the lithium battery being arranged in the cabin of the fuselage.
9. six rotor wing unmanned aerial vehicles as described in claim 1 to 7 any one claim, it is characterised in that the power source bag
The hydrogen storage gas tank being arranged in the cabin of the fuselage is included, the fuel electricity for connecting the hydrogen storage gas tank is mounted on the carry bar
Pond react pile, the fuel cell reaction pile respectively with the anterior motor, middle part motor and afterbody motor connection.
10. six rotor wing unmanned aerial vehicles as described in claim 1 to 7 any one claim, it is characterised in that the power source bag
The fuel tank being arranged in the cabin of the fuselage is included, the dynamic generator of oil for connecting the fuel tank, institute are mounted on the carry bar
State the dynamic generator of oil respectively with the anterior motor, middle part motor and afterbody motor connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710042478.4A CN106697274B (en) | 2017-01-20 | 2017-01-20 | Six rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710042478.4A CN106697274B (en) | 2017-01-20 | 2017-01-20 | Six rotor unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106697274A true CN106697274A (en) | 2017-05-24 |
| CN106697274B CN106697274B (en) | 2023-06-06 |
Family
ID=58910092
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710042478.4A Active CN106697274B (en) | 2017-01-20 | 2017-01-20 | Six rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106697274B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107284668A (en) * | 2017-07-20 | 2017-10-24 | 蜂巢航宇科技（北京）有限公司 | Multi-rotor unmanned aerial vehicle |
| CN107380458A (en) * | 2017-08-07 | 2017-11-24 | 雅各·维拉萨 | A kind of manned investigation single-blade list rotor craft of long endurance of hovering |
| CN107697280A (en) * | 2017-10-18 | 2018-02-16 | 沈阳旋飞航空技术有限公司 | A kind of load-carrying construction for electronic unmanned plane |
| CN108710145A (en) * | 2018-04-26 | 2018-10-26 | 武汉天图地信科技有限公司 | A kind of unmanned plane positioning system and method |
| CN109774948A (en) * | 2019-02-13 | 2019-05-21 | 山东蜂巢航空科技有限公司 | It is a kind of can a variety of load of carry oil electricity mixing multi-rotor unmanned aerial vehicle |
| WO2020217058A1 (en) * | 2019-04-23 | 2020-10-29 | Intelligent Energy Limited | Uav having configurable fuel cell power system |
| JP2022530875A (en) * | 2019-04-23 | 2022-07-04 | インテリジェント エナジー リミテッド | Unmanned aerial vehicle with configurable fuel cell power system |
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| CN107697280A (en) * | 2017-10-18 | 2018-02-16 | 沈阳旋飞航空技术有限公司 | A kind of load-carrying construction for electronic unmanned plane |
| CN107697280B (en) * | 2017-10-18 | 2023-11-07 | 沈阳旋飞航空技术有限公司 | A load-carrying structure for electric unmanned aerial vehicle |
| CN108710145A (en) * | 2018-04-26 | 2018-10-26 | 武汉天图地信科技有限公司 | A kind of unmanned plane positioning system and method |
| CN109774948A (en) * | 2019-02-13 | 2019-05-21 | 山东蜂巢航空科技有限公司 | It is a kind of can a variety of load of carry oil electricity mixing multi-rotor unmanned aerial vehicle |
| WO2020217058A1 (en) * | 2019-04-23 | 2020-10-29 | Intelligent Energy Limited | Uav having configurable fuel cell power system |
| JP2022530875A (en) * | 2019-04-23 | 2022-07-04 | インテリジェント エナジー リミテッド | Unmanned aerial vehicle with configurable fuel cell power system |
| JP7354286B2 (en) | 2019-04-23 | 2023-10-02 | インテリジェント エナジー リミテッド | Unmanned aerial vehicle with configurable fuel cell power system |
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