CN110294113A - A kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle - Google Patents
A kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN110294113A CN110294113A CN201910592916.3A CN201910592916A CN110294113A CN 110294113 A CN110294113 A CN 110294113A CN 201910592916 A CN201910592916 A CN 201910592916A CN 110294113 A CN110294113 A CN 110294113A
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- unmanned aerial
- aerial vehicle
- mixed dynamic
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- 239000000446 fuel Substances 0.000 claims abstract description 29
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims abstract description 23
- 229910052744 lithium Inorganic materials 0.000 claims abstract description 23
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 22
- 239000002828 fuel tank Substances 0.000 claims abstract description 14
- 239000003921 oil Substances 0.000 claims description 20
- 239000000463 material Substances 0.000 claims description 10
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 7
- 239000004917 carbon fiber Substances 0.000 claims description 7
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 7
- 239000000295 fuel oil Substances 0.000 claims description 6
- 238000010248 power generation Methods 0.000 claims description 4
- 241000771208 Buchanania arborescens Species 0.000 claims description 3
- 230000001133 acceleration Effects 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 claims description 3
- 108010066114 cabin-2 Proteins 0.000 description 4
- 230000005611 electricity Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
-
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- 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
-
- 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
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- 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
- B64U50/11—Propulsion using internal combustion piston engines
-
- 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
- B64U2201/10—UAVs characterised by their flight controls autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Hybrid Electric Vehicles (AREA)
Abstract
The invention discloses a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicles, it include: undercarriage (1), cabin (2), horn (3), flight control system (4) and sensor (5), further includes: big rotor (6), small rotor (7), fuel engines (8), fuel tank (10), generator (11), lithium battery (12), electrical power amplifier (13), gear set (9) and belt (14).After flight parameter is input to flight control system (4) after acquisition, realize that the flight attitude of unmanned plane controls by flight control system (4)；Flight control system (4) controls the rotation of big rotor (6) and the rotation of small rotor (7)；2 big rotor (6) provides the prevailing lift of unmanned plane, and the wheelbase between 2 big rotor (6) is smaller than the diameter of big rotor (6).Oil electric mixed dynamic multi-rotor unmanned aerial vehicle proposed by the present invention have it is small in size, control be easy, the flight time is long, and load capacity is strong, high reliability.
Description
Technical field
The present invention relates to a kind of multi-rotor unmanned aerial vehicle, especially a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle.
Background technique
Technical grade unmanned plane have it is widely used, easy to use, the advantages such as risk that efficiency-cost ratio is good and no one was injured are answered
It is very extensive with field.
There are three types of power modes for existing multi-rotor unmanned aerial vehicle: one is the energy using battery as unmanned plane, directly
Rotor is driven, this is that technology highly developed at present is typically only dozens of minutes, takes simultaneously the disadvantage is that the flight time is short
Carrying load ability is weak, generally within more than ten kilograms；Another mode is driven using fuel engines, although overcoming
Flight time is short and carries the weak disadvantage of load capacity, but new problem is that structure is complicated, high failure rate, and fuel engines drives
Dynamic speed regulation poor accuracy causes flight stability insufficient；Finally one is being generated electricity by fuel engines, the energy of fuel oil is turned
Electric energy is turned to, then electricity consumption directly drives unmanned plane again, and this mode stability, control performance and reliability improve, but
It is to carry load capacity or compare to have limitation, generally within tens kilograms, and energy conversion utilization rate is low.
Summary of the invention
The purpose of the present invention is to provide a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicles, and it is multiple to solve previous apparatus structure
Miscellaneous, high failure rate, fuel engines driving speed regulation poor accuracy causes flight stability insufficient, and finally one is sent out by fuel oil
Motivation power generation, converts electric energy for the energy of fuel oil, and then electricity consumption directly drives unmanned plane again, this mode stability, control
Performance And Reliability processed improves, but carrying load capacity, which still compares, limitation, generally within tens kilograms, and
The low problem of energy conversion utilization rate.
A kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle, comprising: undercarriage, cabin, horn, flight control system and sensing
Device, further includes: big rotor, small rotor, fuel engines, fuel tank, generator, lithium battery, electrical power amplifier, gear set and skin
Band.
Undercarriage is fixed with cabin lower part.Horn is uniformly fixed on cabin surrounding, and there is small rotor in the end of each horn.
Fuel engines, fuel tank, generator, lithium battery, electrical power amplifier, gear set, belt, flight control system and
Sensor is fixed on engine room inside.
Flight control system is connect with sensor, fuel engines, lithium battery, electrical power amplifier, generator respectively.
Fuel engines is connect with fuel tank, generator, gear set respectively, and the output shaft of fuel engines respectively drives gear
Group and generator.The output shaft of gear set is connect with big rotor.
Lithium battery is connect with generator.
Electrical power amplifier is connect with small rotor conducting wire.
Big rotor is 2, and 2 big rotor is laid out in staggered form, and big rotor is fixed with cabin top, the phase of 2 big rotor
Angle differs 90 degree.The revolving speed of 2 big rotor is identical, contrary.
Preferably, gear set drives big rotor by output shaft.
Preferably, the output shaft of gear set drives big rotor by belt transmission.
Preferably, the material of undercarriage is carbon fiber.
Preferably, the material of cabin and horn is carbon fiber.
Preferably, the material of big rotor and small rotor is carbon fiber.
Preferably, the material of big rotor and small rotor is light wood.
Preferably, horn is 3 to 8.
Preferably, horn is 4.
Preferably, when work, undercarriage takes off, lands and stores for unmanned plane.Cabin and horn are unmanned plane
Integrated support structure.
Sensor realize unmanned plane flight parameter acquisition, including speed, acceleration, height, magnetic heading, pitch angle,
Yaw angle and roll angle；
After flight parameter is input to flight control system after acquisition, the flight attitude of unmanned plane is realized by flight control system
Control；Flight control system controls the rotation of big rotor and the rotation of small rotor.2 big rotor provides the main liter of unmanned plane
Power, the wheelbase between 2 big rotor is smaller than the diameter of big rotor, is in crossing condition, rotation speed is identical, contrary, phase
Angle differs 90 degree.Small rotor realizes the gesture stability of unmanned plane, pitch attitude, yaw-position and rolling appearance including unmanned plane
State is driven by the electric energy of lithium battery.
Shaft power a part of fuel engines output is for driven generator power generation；Another part is used to drive gear
Group, the rotation of gear set output shaft drive belt rotation, finally drive big rotor rotational.
Generator is used to be converted to the part shaft power that engine exports electric energy, and charges to lithium battery.
Lithium battery is used to store the electric energy of generator, while by power output to electrical power amplifier.
The electric current of electrical power amplifier output drives small rotor rotational.
Fuel oil needed for fuel tank provides burning for fuel engines.
After adopting the above structure, the invention has the following beneficial effects: the more rotors of a kind of oil electric mixed dynamic of the present invention without
Man-machine, it drives the big rotor of two staggered form layouts to provide main lift using fuel engines, what two staggered forms were laid out
Big rotor reduces housing construction size；The rotation of small rotor is completed by power drive system, main realization unmanned plane
Gesture stability.This mode overcomes fuel engines driving malfunction rate height, and speed regulation poor accuracy causes flight stability insufficient
The shortcomings that, most critical is the flight time for improving oil electric mixed dynamic multi-rotor unmanned aerial vehicle, load weight, meanwhile, stability,
Control performance and reliability also improve.The present invention has the flight time long, and carrying load-carrying ability is strong, and structure is simple, reliability
The advantages that height, control performance is good.
Detailed description of the invention
Fig. 1 is a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle overall schematic；
Fig. 2 is a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle engine room inside schematic diagram；
Fig. 3 is a kind of big rotor wing rotation process schematic of two staggered forms of oil electric mixed dynamic multi-rotor unmanned aerial vehicle.
1. 2. cabin of undercarriage, 3. horn, 4. flight control system
5. 6. small 8. fuel engines of rotor of big rotor 7. of sensor
9. 10. fuel tank of gear set, 11. generator, 12. lithium battery
13. 14. belt of electrical power amplifier
Specific embodiment
The present invention is described in further detail below in conjunction with the drawings and specific embodiments, is wanted according to following explanation and right
Book is sought, advantages and features of the invention will become apparent from.It should be noted that attached drawing is all made of very simplified form and is applicable in
Non-accurate ratio, only for the purpose of facilitating and clarifying the purpose of the embodiments of the invention.
It should be noted that present invention spy is for multiple embodiments with further in order to clearly demonstrate the contents of the present invention
Illustrate different implementations of the invention, wherein multiple embodiment is enumeration and non-exhaustive.In addition, in order to illustrate
Succinctly, the content having been mentioned in preceding embodiment is often omitted in rear embodiment, therefore, unmentioned interior in rear embodiment
Appearance can accordingly refer to preceding embodiment.
Although the invention can modification in a variety of forms and replacement extend, also listed in specification some specific
Implement legend and is described in detail.It should be understood that the starting point of inventor is not that the invention is limited to illustrated spy
Determine embodiment, antithesis, the starting point of inventor is to protect in all spirit or scope given and defined by this rights statement
The improvement of progress, equivalent alterations and modifications.Same component number is likely to be used for all attached drawings to represent identical or class
As part.
Please refer to Fig. 1, Fig. 2 and Fig. 3, a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle, comprising: undercarriage 1, cabin 2, machine
Arm 3, flight control system 4 and sensor 5, further includes: big rotor 6, small rotor 7, fuel engines 8, fuel tank 10, generator
11, lithium battery 12, electrical power amplifier 13, gear set 9 and belt 14.
Undercarriage 1, cabin 2, horn 3, big rotor 6, small rotor 7 material be carbon fiber.Big rotor 6 and small rotor 7
Material is light wood.
Undercarriage 1 is fixed with 2 lower part of cabin.Horn 3 is 3 to 8, and horn 3 can be 4.Horn 3 is uniformly fixed on
There are small rotor 7 in 2 surrounding of cabin, the end of each horn 3.
Fuel engines 8, generator 11, lithium battery 12, electrical power amplifier 13, gear set 9, belt 14, flies at fuel tank 10
Row control system 4 and sensor 5 are fixed on inside cabin 2.
Flight control system 4 respectively with sensor 5, fuel engines 8, lithium battery 12, electrical power amplifier 13, generator
11 connections.
Fuel engines 8 is connect with fuel tank 10, generator 11, gear set 9 respectively, the output shaft difference of fuel engines 8
Drive gear set 9 and generator 11.The output shaft of gear set 9 is connect with big rotor 6.
Lithium battery 12 is connect with generator 11.
Electrical power amplifier 13 is connect with small 7 conducting wire of rotor.
Big rotor 6 is 2, and 2 big rotor 6 is laid out in staggered form, and big rotor 6 is fixed with 2 top of cabin, 2 big rotor 6
Phase angle differ 90 degree.The revolving speed of 2 big rotor 6 is identical, contrary.
Gear set 9 is driven by the output shaft that output shaft directly drives big rotor 6 or gear set 9 by the transmission of belt 14
Move big rotor 6.
When work, undercarriage 1 takes off, lands and stores for unmanned plane.Cabin 2 and horn 3 are the entirety of unmanned plane
Support construction.
Sensor 5 realize unmanned plane flight parameter acquisition, mainly include speed, acceleration, height, magnetic heading, bow
The elevation angle, yaw angle and roll angle；
After flight parameter is input to flight control system 4 after acquisition, the flight appearance of unmanned plane is realized by flight control system 4
State control；Flight control system 4 controls the rotation of big rotor 6 and the rotation of small rotor 7.2 big rotor 6 provides the master of unmanned plane
Lift is wanted, the wheelbase between 2 big rotor 6 is smaller than the diameter of big rotor 6, is in crossing condition, rotation speed is identical, direction phase
Instead, phase angle differs 90 degree.Small rotor 7 realizes the gesture stability of unmanned plane, pitch attitude, yaw-position and rolling including unmanned plane
It turns posture, is driven by the electric energy of lithium battery 12.
Shaft power a part that fuel engines 8 exports is for the power generation of driven generator 11；Another part is used to drive
Gear set 9, the rotation of 9 output shaft of gear set drive belt 14 to rotate, big rotor 6 are finally driven to rotate.
Generator 11 is used to be converted to the part shaft power that engine exports electric energy, and charges to lithium battery 12.
Lithium battery 12 is used to store the electric energy of generator 11, while by power output to electrical power amplifier 13.
Electrical power amplifier 13 exports tens amperes of electric current to drive small rotor 7 to rotate.
Fuel tank 10 is fuel oil needed for fuel engines 8 provides burning.
The present invention realizes following significant the utility model has the advantages that structure is simple, and small in size, control performance is good, and the flight time is long,
It is strong to carry load capacity, high reliability.
Technical solution and design according to the present invention can also have other any suitable changes.Skill common for this field
For art personnel, all these replacements, adjustment and improvement be should all belong to the protection domain of appended claims of the present invention.
Claims (10)
1. a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle, comprising: undercarriage (1), cabin (2), horn (3), flight control system
System (4) and sensor (5), which is characterized in that further include: big rotor (6), small rotor (7), fuel engines (8), fuel tank
(10), generator (11), lithium battery (12), electrical power amplifier (13), gear set (9) and belt (14)；
Undercarriage (1) is fixed with cabin (2) lower part；Horn (3) is uniformly fixed on cabin (2) surrounding, the end of each horn (3)
There are small rotor (7)；
Fuel engines (8), fuel tank (10), generator (11), lithium battery (12), electrical power amplifier (13), gear set (9),
It is internal that belt (14), flight control system (4) and sensor (5) are fixed on cabin (2)；
Flight control system (4) respectively with sensor (5), fuel engines (8), lithium battery (12), electrical power amplifier (13),
Generator (11) connection；
Fuel engines (8) is connect with fuel tank (10), generator (11), gear set (9) respectively, the output of fuel engines (8)
Axis respectively drives gear set (9) and generator (11)；The output shaft of gear set (9) is connect with big rotor (6)；
Lithium battery (12) is connect with generator (11)；
Electrical power amplifier (13) is connect with small rotor (7) conducting wire；
Big rotor (6) is 2, and 2 big rotor (6) is laid out in staggered form, and big rotor (6) is fixed with cabin (2) top, 2 big
The phase angle of rotor (6) differs 90 degree；The revolving speed of 2 big rotor (6) is identical, contrary.
2. a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that gear set (9) is logical
It crosses output shaft and drives big rotor (6).
3. a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that gear set (9)
Output shaft drives big rotor (6) by belt (14) transmission.
4. a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that undercarriage (1)
Material is carbon fiber.
5. a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that cabin (2) and machine
The material of arm (3) is carbon fiber.
6. a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle according to claim 1,2 or 3, which is characterized in that big rotor
(6) and the material of small rotor (7) is carbon fiber.
7. a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle according to claim 1,2 or 3, which is characterized in that big rotor
(6) and the material of small rotor (7) is light wood.
8. a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that horn (3) is 3
To 8.
9. a kind of according to claim 1, oil electric mixed dynamic multi-rotor unmanned aerial vehicle described in 5 or 8, which is characterized in that horn (3)
It is 4.
10. a kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that more rotors nobody
The action of machine are as follows:
Undercarriage (1) takes off, lands and stores for unmanned plane；Cabin (2) and horn (3) are the integrated support knot of unmanned plane
Structure；
Sensor (5) realize unmanned plane flight parameter acquisition, including speed, acceleration, height, magnetic heading, pitch angle, partially
Navigate angle and roll angle；
After flight parameter is input to flight control system (4) after acquisition, the flight appearance of unmanned plane is realized by flight control system (4)
State control；Flight control system (4) controls the rotation of big rotor (6) and the rotation of small rotor (7)；2 big rotor (6) provides nothing
Man-machine prevailing lift, the wheelbase between 2 big rotor (6) is smaller than the diameter of big rotor (6), is in crossing condition, rotation speed
Spend identical, contrary, 90 degree of phase angle difference；Small rotor (7) realizes the gesture stability of unmanned plane, the pitching appearance including unmanned plane
State, yaw-position and roll attitude are driven by the electric energy of lithium battery (12)；
Shaft power a part of fuel engines (8) output is for driven generator (11) power generation；Another part is used to drive
Gear set (9), the rotation of gear set (9) output shaft drive belt (14) rotation, big rotor (6) are finally driven to rotate；
Generator (11) is used to be converted to the part shaft power that engine exports electric energy, and charges to lithium battery (12)；
Lithium battery (12) is used to store the electric energy of generator (11), while by power output to electrical power amplifier (13)；
Electrical power amplifier (13) output electric current come drive small rotor (7) rotate；
Fuel tank (10) is fuel oil needed for fuel engines (8) provide burning.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910592916.3A CN110294113A (en) | 2019-07-03 | 2019-07-03 | A kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910592916.3A CN110294113A (en) | 2019-07-03 | 2019-07-03 | A kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110294113A true CN110294113A (en) | 2019-10-01 |
Family
ID=68030035
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910592916.3A Pending CN110294113A (en) | 2019-07-03 | 2019-07-03 | A kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle |
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| CN107444630A (en) * | 2017-09-15 | 2017-12-08 | 深圳市旗客智能技术有限公司 | Oil electric mixed dynamic unmanned plane |
| US20180009529A1 (en) * | 2014-11-14 | 2018-01-11 | Top Flight Technologies, Inc. | Micro hybrid generator system drone |
| CN207157521U (en) * | 2017-09-15 | 2018-03-30 | 深圳市旗客智能技术有限公司 | Oil electric mixed dynamic unmanned plane |
| WO2018076047A1 (en) * | 2016-10-24 | 2018-05-03 | Hybridskys Technology Pty Ltd | Hybrid aircraft |
| CN109677622A (en) * | 2019-01-11 | 2019-04-26 | 南京航空航天大学 | The hybrid power four-rotor helicopter system of multi-operation mode |
-
2019
- 2019-07-03 CN CN201910592916.3A patent/CN110294113A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180009529A1 (en) * | 2014-11-14 | 2018-01-11 | Top Flight Technologies, Inc. | Micro hybrid generator system drone |
| CN205602114U (en) * | 2016-04-15 | 2016-09-28 | 深圳市卓尔思科技有限公司 | Unmanned aerial vehicle with multiple rotor wings |
| WO2018076047A1 (en) * | 2016-10-24 | 2018-05-03 | Hybridskys Technology Pty Ltd | Hybrid aircraft |
| CN106927030A (en) * | 2017-03-15 | 2017-07-07 | 西北工业大学 | A kind of oil electric mixed dynamic multi-rotor aerocraft and its flight control method |
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