CN109502024A - A kind of aircraft and unmanned aerial vehicle - Google Patents
A kind of aircraft and unmanned aerial vehicle Download PDFInfo
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- CN109502024A CN109502024A CN201811223776.4A CN201811223776A CN109502024A CN 109502024 A CN109502024 A CN 109502024A CN 201811223776 A CN201811223776 A CN 201811223776A CN 109502024 A CN109502024 A CN 109502024A
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- 238000012545 processing Methods 0.000 claims description 26
- 230000005611 electricity Effects 0.000 claims description 24
- 238000004891 communication Methods 0.000 claims description 22
- 230000005540 biological transmission Effects 0.000 claims description 15
- 238000004146 energy storage Methods 0.000 claims description 8
- 229910001218 Gallium arsenide Inorganic materials 0.000 claims description 5
- JBRZTFJDHDCESZ-UHFFFAOYSA-N AsGa Chemical group [As]#[Ga] JBRZTFJDHDCESZ-UHFFFAOYSA-N 0.000 claims description 4
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 230000008901 benefit Effects 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 abstract description 2
- 230000008859 change Effects 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000004519 manufacturing process Methods 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
- 239000007787 solid Substances 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- 101000606504 Drosophila melanogaster Tyrosine-protein kinase-like otk Proteins 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
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- 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
-
- 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
- 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
- B64D27/30—Aircraft characterised by electric power plants
- B64D27/35—Arrangements for on-board electric energy production, distribution, recovery or storage
- B64D27/353—Arrangements for on-board electric energy production, distribution, recovery or storage using solar cells
-
- 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
- B64D47/08—Arrangements of cameras
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
-
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
-
- 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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The present invention relates to field of aerospace technology, more particularly to a kind of aircraft and unmanned aerial vehicle.A kind of aircraft, comprising: the first noumenon, the second ontology and engine, the first noumenon include first end and second end, and the second end is connect by the engine with second ontology；The main shaft of the engine is hollow shaft.Aircraft of the present invention at least has the advantage that having effectively achieved working cell setting improves the radiating efficiency of motor in aircraft front end thereby executing corresponding task.
Description
Technical field
The present invention relates to field of aerospace technology, more particularly to a kind of aircraft and unmanned aerial vehicle.
Background technique
Unmanned aerial vehicle is the unmanned vehicle automatically controlled, with self-navigation and execution special duty.It has whole day
Time, great depth operation, the ability quickly investigated.Now, it can't help unmanned aerial vehicle applied to military field, also obtained in civilian industry
Be widely applied, e.g., taking photo by plane, agricultural, plant protection, miniature self-timer, express transportation, disaster relief, observation wild animal, monitoring biography
It catches an illness, survey and draw, news report, electric inspection process, the disaster relief, movies-making, the application for manufacturing romance etc. field, greatly expanding
The purposes of unmanned plane itself.
Present unmanned aerial vehicle power arrangement mostly uses power prefixed form, and the unmanned aerial vehicle of this power prefixed form is led
Cause many tasks that can not execute, for example, detection aircraft tip dangerous situation, hits from preceding end-fire；Motor is using external rotor brushless electricity
Machine or inner-rotor brushless motor, solid shafting drive propeller rotational mode to generate pulling force, the heat dissipation ventilation at motor center position
Ineffective, motor transformation efficiency is lower.
Summary of the invention
It is a primary object of the present invention to provide a kind of new structural aircraft and unmanned aerial vehicle, skill to be solved
Art problem is that the unmanned aerial vehicle of power prefixed form causes many tasks that can not execute, and solid shafting drives propeller rotational mode to lead
The heat dissipation ventilation for sending a telegraph machine centre is ineffective, and motor transformation efficiency is lower.
The object of the invention to solve the technical problems adopts the following technical solutions to realize.It proposes according to the present invention
A kind of aircraft, comprising: the first noumenon, the second ontology and engine,
The first noumenon includes first end and second end, and the second end passes through the engine and second ontology
Connection；
The main shaft of the engine is hollow shaft.
The object of the invention to solve the technical problems also can be used following technical measures and further realize.
Preferably, aircraft above-mentioned, including working cell, the working cell includes at least a Working mould
Block, at least one described operational module are set to the first end.
Preferably, aircraft above-mentioned, including electricity energy harvester, the electricity energy harvester and the engine
Connection, for the energy of acquisition to be supplied to the engine.
Preferably, aircraft above-mentioned, operational module described in wherein at least one are image capture module.
Preferably, aircraft above-mentioned, wherein the engine is outer rotor motor, in the outer rotor motor
The outer surface of rotor is connected with screw blade.
Preferably, aircraft above-mentioned, wherein the first noumenon is connected with lift portion, which provides for aircraft
Lift；
The electricity energy harvester is connect with the lift portion.
Preferably, aircraft above-mentioned, wherein the electricity energy harvester is connected with the engine by energy storage device.
Preferably, aircraft above-mentioned, wherein the electricity energy harvester is connected with the engine by energy storage device.
Preferably, aircraft above-mentioned, wherein further include:
Control device, comprising:
Central control unit, comprising:
Processing module, prestores flying quality, and the working cell Xiang Suoshu sends instruction and receives what the working cell was sent
Information, and the confidence sent to the working cell received is calculated and is exported calculated result；
Drive module receives the flight directive that the processing module is sent；
Locating module, for obtaining location information and sending the processing module to；
Second communication module is used for the processing module and peripheral device communication；
Remote control unit, comprising:
First communication module, and the second communication module wireless telecommunications, for the remote control unit and it is described in
Centre control unit is communicated, and realizes data transmission；
Operation module is input operation instruction, and is sent and is instructed to the central control unit by first communication module；
Output module, output receive the information that the central control unit is sent by first communication module.
Preferably, aircraft above-mentioned is used for wherein the central control unit further includes transmission module by the work
The information that unit is sent sends the processing module to, and the transmission module includes data transmission module and image transmitting submodule
Block.
Also the following technical solution is employed for the object of the invention to solve the technical problems to realize.It proposes according to the present invention
A kind of unmanned aerial vehicle, the unmanned aerial vehicle be above-mentioned aircraft, the fuselage of unmanned plane includes the first noumenon and the second ontology.
The object of the invention to solve the technical problems also can be used following technical measures and further realize.
Preferably, wherein catapult-launching gear: unmanned aerial vehicle above-mentioned is set to the first noumenon；
Landing-gear, comprising:
Parachuting equipment is set to the top of the first noumenon；
Landing buffer equipment is set to the bottom of the first noumenon.
Preferably, unmanned aerial vehicle above-mentioned, wherein second ontology is connected with empennage.
Preferably, unmanned aerial vehicle above-mentioned, wherein the lift portion includes fixed-wing and movable wing, wherein the energy is adopted
Acquisition means are arranged on fixed-wing.
Preferably, unmanned aerial vehicle above-mentioned, wherein the electricity energy harvester is gallium arsenide film battery.
By above-mentioned technical proposal, aircraft of the present invention is at least had the advantage that
By the way that motor to be set to the middle part of aircraft, working cell is set to the front end of aircraft, in not shadow
On the basis of ringing aircraft power, working cell setting is had effectively achieved in aircraft front end, is appointed thereby executing corresponding
Business, is set as hollow shaft by the main shaft of motor, improves the radiating efficiency of motor.
The above description is only an overview of the technical scheme of the present invention, in order to better understand the technical means of the present invention,
And can be implemented in accordance with the contents of the specification, the following is a detailed description of the preferred embodiments of the present invention and the accompanying drawings.
Detailed description of the invention
Fig. 1 is the perspective view for the aircraft that the embodiment of the present invention provides；
Fig. 2 is the diagrammatic cross-section for the aircraft that the embodiment of the present invention provides；
Fig. 3 is the structural block diagram of the control device for the aircraft that the embodiment of the present invention provides.
Specific embodiment
It is of the invention to reach the technical means and efficacy that predetermined goal of the invention is taken further to illustrate, below in conjunction with
Attached drawing and preferred embodiment, to aircraft proposed according to the present invention and unmanned aerial vehicle its specific embodiment, structure, feature and
Its effect, detailed description is as follows.In the following description, what different " embodiment " or " embodiment " referred to is not necessarily same reality
Apply example.In addition, the special characteristic, structure or feature in one or more embodiments can be combined by any suitable form.
As illustrated in fig. 1 and 2, a kind of aircraft that one embodiment of the present of invention proposes comprising: the first noumenon 1, second
Ontology 2 and engine 3, the first noumenon 1 include first end and second end, and the second end passes through the engine 3 and institute
State the connection of the second ontology 2；The main shaft of the engine 3 is hollow shaft.
By the way that motor to be set to the middle part of aircraft, working cell is set to the end of the first end of aircraft,
On the basis of not influencing aircraft power, the end that aircraft first end is arranged in working cell is had effectively achieved, thus
Corresponding task is executed, hollow shaft is set as by the main shaft of motor, improves the radiating efficiency of motor.
It is preferred that the aircraft includes working cell 300, the working cell 300 includes at least a work
Make module, at least one described operational module is set to the first end.
Working cell is set to the end of the first end of aircraft, on the basis of not influencing aircraft power, effectively
Ground realizes the end that aircraft first end is arranged in working cell, thereby executing corresponding task.
It is preferred that the aircraft includes electricity energy harvester 4, the electricity energy harvester 4 starts with described
Machine 3 connects, for the energy of acquisition to be supplied to the engine 3.
Electric power is converted by collected energy by electricity energy harvester, the continuation of the journey to motor is realized, increases
The time of aircraft execution task.
It is preferred that at least one described operational module is image capture module.
Image capture module is set to the end of first end, can effectively acquire aircraft first end with flight
The image information in the opposite direction of device is e.g. arranged image capture module in the front end of former setting motor, motor is arranged
Between the first noumenon and the second ontology, the image in front can be collected by image capture module, solves front end presence
Image Acquisition dead-time problem.Other operational modules also can be set in the front end of aircraft, weapon is such as set, it can be cooperated
Target immediately ahead of his weapon strike, turns to without aircraft, and the movement such as overturning greatly facilitates the various work of aircraft
It carries out.
It is preferred that the engine 3 is outer rotor motor, in the appearance of the rotor of the outer rotor motor
Face is connected with screw blade 31.
Screw blade is connected in the outer surface of the rotor of outer rotor motor, has effectively achieved the drive to aircraft flight
It is dynamic.
It is preferred that the first noumenon 1 is connected with lift portion 5, which provides lift for aircraft；Institute
Electricity energy harvester 4 is stated to connect with the lift portion 5.
By the way that lift portion is arranged in the first noumenon, aircraft can take off and adjust flying height.Lift portion and first
Body connection, has fixed part, is additionally provided with movable part, by movable part by fixed part at least two parts, and passes through work
The adjusting change of flight height in dynamic portion.
It is preferred that the electricity energy harvester 4 is connect by energy storage device 6 with the engine 3.
Energy storage device is set in aircraft, for storing energy, provides energy needed for power for engine, passes through energy
Acquisition device acquires nature energy (e.g., solar energy), and is converted into energy needed for engine (e.g., electric energy) and is stored in energy storage dress
In setting, when engine power deficiency, power is provided for engine by energy storage device.
It is preferred that as shown in figure 3, the aircraft further include:
Control device, comprising:
Central control unit, comprising:
Processing module, prestores flying quality, and the working cell Xiang Suoshu 300 sends instruction and receives the working cell 300
The information of transmission, and the confidence sent to the working cell 300 received is calculated and is exported calculated result；
Drive module receives the flight directive that the processing module is sent；
Locating module, for obtaining location information and sending the processing module to；
Second communication module is used for the processing module and peripheral device communication；
Remote control unit, comprising:
First communication module, and the second communication module wireless telecommunications, for the remote control unit and it is described in
Centre control unit is communicated, and realizes data transmission；
Operation module is input operation instruction, and is sent and is instructed to the central control unit by first communication module；
Output module, output receive the information that the central control unit is sent by first communication module.
Aircraft is had effectively achieved by above-mentioned control device to fly according to the control information prestored, meanwhile, it can
It, when necessary can be with manual manipulation aircraft, in order to avoid the generation of various fortuitous events can be coped in time remotely to monitor.
Specifically, in advance by the control information of aircraft with there are in processing module, route, time including flight, speed
Degree, height and working cell execute the control information etc. to work accordingly.After starting engine, processing module is to drive module
According to the delivering driving instruction prestored, it is made to climb with command speed to specified height, if spiraling within the specified range
Dry circle, so as to ground staff can with the state of flight of observation flight device, meanwhile, processing module turns its speed, height, engine
The information such as number are detected, and such as detect exception, to stall by drive module driving, so that aircraft lands；If
Exception is not detected, processing module, according to Track fusion aircraft flight is prestored, starts work in designated place by drive module
Make unit and carries out relevant work, e.g., Image Acquisition etc..In order to which aircraft can pass through positioning accurately according to track flight is prestored
Module carries out positioning in real time to the position of aircraft, and sends location information to processing module, is compared with the track prestored
Right, if there is off-track the case where drives aircraft to correct the deviation of flight path in time.It is preferably fixed in the present embodiment
Position module is GPS positioning module.After completing task specified by working cell according to prestored instruction, by processing module according to
Prestored instruction controls aircraft by drive module and makes a return voyage, and lands in designated place.
While processing module controls aircraft flight according to the flight information prestored, it can also be arranged on ground long-range
Control unit artificially monitor and in time manually control aircraft to the flight of aircraft and work.Specifically, logical
First communication module of the second communication module and remote control unit of crossing central control unit in real time believes the flight of aircraft
Breath is transferred to the output module of remote control unit, such as monitor, the flight of observation flight device and the working condition of working cell,
When necessary, by operation module, such as operation handle issues control instruction, by the first communication module and the second communication module by hand
Dynamic control instruction is transmitted to processing module, and preferential basis is manually controlled instruction and drives aircraft by drive module by processing module
Flight, or control working cell work.
Above-mentioned control device has effectively achieved aircraft flight and carries out the intelligent control of relevant work, effectively protects
Control aircraft and working cell can be taken timely measure by having demonstrate,proved when fortuitous event occurs, and reduce the generation of accident.
Preferably, aircraft above-mentioned is used for wherein the central control unit further includes transmission module by the work
The information that unit is sent sends the processing module to, and the transmission module includes data transmission module and image transmitting submodule
Block.
In central control unit, setting transmission module can be effectively in processing module and drive module and working cell
Between carry out the transmission of data, image etc..
Another embodiment of the present invention proposes a kind of unmanned aerial vehicle, and as illustrated in fig. 1 and 2, the unmanned aerial vehicle is above-mentioned flies
Row device, the fuselage of unmanned plane include the first noumenon 1 and the second ontology 2.
Above-mentioned aircraft can be applied in various aerospace equipments, such as dirigible.It is in the present embodiment preferably nothing
People's aircraft.In the present embodiment, the first noumenon is from the head of unmanned aerial vehicle to motor portion, and wing is fixed on the first noumenon
Top, the second ontology be from motor to tail part, empennage is installed in drive end unit.
By the way that motor to be set to the middle part of unmanned aerial vehicle, working cell is set to the front end of unmanned aerial vehicle,
On the basis of not influencing unmanned aerial vehicle power, working cell setting is had effectively achieved in unmanned aerial vehicle front end, thereby executing
Corresponding task is set as hollow shaft by the main shaft of motor, improves the radiating efficiency of motor, passes through energy acquisition list
Collected energy is converted electric power by member, realizes the continuation of the journey to motor, increases the time that unmanned aerial vehicle executes task.
In the present embodiment, preferred energy acquisition device is solar battery chip, for acquiring solar energy, and by the sun
Electric energy can be converted into and be stored in energy storage device, that is, in battery, in case providing electric energy when necessary for motor.Solar energy is set
When battery chip, the damage of solar battery chip in order to prevent is positioned on the fixed part in lift portion of aircraft, that is,
The position in addition to aileron rudder face of aircraft wing, while the upper surface for being set to wing can be efficiently received the photograph of sunlight
It penetrates, improves the efficiency of acquisition solar energy.Solar battery chip can be easy to operate using sticking double faced adhesive tape on wing, at
This is low.The upper counterangle of wing is 4 °~9 °.
It is preferred that catapult-launching gear 9: being set to the first noumenon 1；
Landing-gear, comprising:
Parachuting equipment 7 is set to the top of the first noumenon 1；
Landing buffer equipment 8 is set to the bottom of the first noumenon 1.
Unmanned aerial vehicle, which takes off, to be taken many forms, and e.g., sliding rail takes off, take off etc., it uses in the present embodiment
The form of catapult-assisted take-off.Specifically, when taking off, rubber band is hung over ejection hanger in the fixed ejection hanger in the two sides of the first noumenon
On, the propeller starting motor of motor is rotated, unmanned aerial vehicle is discharged.When landing, parachuting equipment is controlled by processing module
Release parachute is subtracted with reducing the sinking speed of unmanned aerial vehicle by the landing buffer equipment being arranged in the bottom of unmanned aerial vehicle
Impact force suffered by light unmanned aerial vehicle, is effectively protected aircraft, reduces aircraft and break down, or even the possibility crashed
Property.
It is preferred that second ontology 2 is connected with empennage.
Empennage plays balanced action to unmanned aerial vehicle.
It is preferred that the lift portion 5 includes fixed-wing and movable wing, wherein the electricity energy harvester 4 is arranged
On fixed-wing.
When electricity energy harvester is set in lift portion, in order to not influence the adjusting of aircraft altitude, while energy acquisition
Device not will receive the active force from movable part, and so as to cause the damage of electricity energy harvester, electricity energy harvester is set
It is placed in fixed-wing.
It is preferred that the electricity energy harvester is gallium arsenide film battery.
Gallium arsenide film battery conversion efficiency reaches 34.5% (AM1.5G), is the current highest flexible thin of efficiency in the world
Film solar cell.The battery manufacturing cost reduces by 50% or more than traditional high efficiency gallium arsenide cells, can be air equipment, shifting
Dynamic electronic equipment, wearable device, internet of things equipment provide the sustainable energy power of best cost performance.
The above described is only a preferred embodiment of the present invention, be not intended to limit the present invention in any form, according to
According to technical spirit any simple modification, equivalent change and modification to the above embodiments of the invention, this hair is still fallen within
In the range of bright technical solution.
Claims (14)
1. a kind of aircraft characterized by comprising the first noumenon, the second ontology and engine,
The first noumenon includes first end and second end, and the second end is connected by the engine and second ontology
It connects；
The main shaft of the engine is hollow shaft.
2. aircraft as described in claim 1, which is characterized in that including working cell,
The working cell includes at least an operational module, at least one described operational module is set to the first end.
3. aircraft as described in claim 1, which is characterized in that including electricity energy harvester, the electricity energy harvester and institute
Engine connection is stated, for the energy of acquisition to be supplied to the engine.
4. aircraft according to claim 2, which is characterized in that
At least one described operational module is image capture module.
5. aircraft according to claim 1, which is characterized in that
The engine is outer rotor motor, is connected with screw blade in the outer surface of the rotor of the outer rotor motor.
6. aircraft according to claim 3, which is characterized in that
The first noumenon is connected with lift portion, which provides lift for aircraft；
The electricity energy harvester is connect with the lift portion.
7. aircraft according to claim 6, which is characterized in that
The electricity energy harvester is connected with the engine by energy storage device.
8. aircraft according to claim 7, which is characterized in that further include:
Control device, comprising:
Central control unit, comprising:
Processing module prestores flying quality, and the working cell Xiang Suoshu sends instruction and receives the information that the working cell is sent,
And the confidence sent to the working cell received is calculated and is exported calculated result；
Drive module receives the flight directive that the processing module is sent；
Locating module, for obtaining location information and sending the processing module to；
Second communication module is used for the processing module and peripheral device communication；
Remote control unit, comprising:
First communication module is controlled with the second communication module wireless telecommunications for the remote control unit and the center
Unit processed is communicated, and realizes data transmission；
Operation module is input operation instruction, and is sent and is instructed to the central control unit by first communication module；
Output module, output receive the information that the central control unit is sent by first communication module.
9. aircraft according to claim 8, which is characterized in that
The central control unit further includes transmission module, and the information for sending the working cell sends the processing to
Module, the transmission module include data transmission module and image transmitting submodule.
10. a kind of unmanned aerial vehicle, which is characterized in that the unmanned aerial vehicle is flight described in any one of claim 1-9
Device, the fuselage of unmanned plane include the first noumenon and the second ontology.
11. unmanned aerial vehicle according to claim 10, which is characterized in that
Further include:
Catapult-launching gear: it is set to the first noumenon；
Landing-gear, comprising:
Parachuting equipment is set to the top of the first noumenon；
Landing buffer equipment is set to the bottom of the first noumenon.
12. unmanned aerial vehicle according to claim 10, which is characterized in that second ontology is connected with empennage.
13. unmanned aerial vehicle according to claim 10, which is characterized in that the lift portion includes fixed-wing and movable wing,
Wherein the electricity energy harvester is arranged on fixed-wing.
14. unmanned aerial vehicle according to claim 10, which is characterized in that the electricity energy harvester is gallium arsenide film electricity
Pond.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811223776.4A CN109502024A (en) | 2018-10-19 | 2018-10-19 | A kind of aircraft and unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811223776.4A CN109502024A (en) | 2018-10-19 | 2018-10-19 | A kind of aircraft and unmanned aerial vehicle |
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| CN109502024A true CN109502024A (en) | 2019-03-22 |
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| CN201811223776.4A Pending CN109502024A (en) | 2018-10-19 | 2018-10-19 | A kind of aircraft and unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2795548A1 (en) * | 2019-05-23 | 2020-11-23 | Inst Tecnologico Y De Energias Renovables S A | Remotely piloted solar plane with great autonomy for conducting inspection and surveillance missions (Machine-translation by Google Translate, not legally binding) |
| WO2021023712A1 (en) * | 2019-08-05 | 2021-02-11 | Conseil Et Technique | Aircraft |
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| WO2021023712A1 (en) * | 2019-08-05 | 2021-02-11 | Conseil Et Technique | Aircraft |
| FR3099752A1 (en) * | 2019-08-05 | 2021-02-12 | Conseil Et Technique | AIRCRAFT ENGINE AND AIRCRAFT EQUIPPED WITH SUCH ENGINE |
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