CN105882946B - A kind of unmanned plane with self-powered ability - Google Patents
A kind of unmanned plane with self-powered ability Download PDFInfo
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- CN105882946B CN105882946B CN201610222539.0A CN201610222539A CN105882946B CN 105882946 B CN105882946 B CN 105882946B CN 201610222539 A CN201610222539 A CN 201610222539A CN 105882946 B CN105882946 B CN 105882946B
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- transformer
- unmanned plane
- self
- triode
- housing
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- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims abstract description 16
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 16
- 239000010703 silicon Substances 0.000 claims abstract description 16
- 229920000742 Cotton Polymers 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 1
- 229910052799 carbon Inorganic materials 0.000 claims 1
- 238000009434 installation Methods 0.000 claims 1
- 238000006243 chemical reaction Methods 0.000 abstract description 8
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 230000003139 buffering effect Effects 0.000 abstract description 4
- 238000010276 construction Methods 0.000 abstract description 4
- 230000001771 impaired effect Effects 0.000 abstract description 4
- 238000002955 isolation Methods 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 5
- 238000010248 power generation Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000005622 photoelectricity Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
-
- 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
- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Photovoltaic Devices (AREA)
- Catching Or Destruction (AREA)
Abstract
The present invention relates to a kind of unmanned plane with self-powered ability,Including body,The TRT and aviation mechanism being arranged on above body,It is arranged on the supporting mechanism and range sensor of body bottom portion,The body is provided with indicator lamp,This has in the solar-electricity source circuit of the unmanned plane of self-powered ability,Voltage is converted solar energy into by silicon photocell,Drive the conducting of triode,Isolation conversion is carried out by transformer again,Then realize the conversion and collection to solar energy,Conventional component is employed in the circuit,It is and simple in construction,Its production cost is also reduced while ensure that performance,Improve the market competitiveness of unmanned plane,Moreover,First-level buffer is made to air bag inflator using the micro air pump in buffer gear,Simultaneously by spring to being made level 2 buffering by the upward elastic force of generation of raming,Improve safety coefficient,Greatly reduce possibility impaired during its landing.
Description
Technical field
The present invention relates to a kind of unmanned plane with self-powered ability.
Background technology
Develop with the technology of automation field, in recent years, unmanned plane with its simple structure, convenient operation and
The features such as autonomous operation, is more and more paid attention to, and unmanned plane is exhibited one's skill to the full in all trades and professions, progresses into ordinary consumption
In the production management of the daily life of person, work entertainment and enterprise.
In existing unmanned plane, most of is all using storage battery power supply by the way of, but working as unmanned plane needs to perform
When the time of work is longer, because accumulator capacity is limited, task can not be often completed.And part unmanned plane employs the sun
The mode that can be generated electricity improves the working time of unmanned plane, but because its solar power generation circuit structure is complicated, technique is excessive,
The production cost of unmanned plane is substantially increased, reduces its market competitiveness, while unmanned plane lacks corresponding safeguard measure, makes
Its in descent easily because decrease speed is too fast etc. reason causes unmanned plane lands when by huge impulsive force, cause nothing
Man-machine breaking-up, it reduce further the safety coefficient of unmanned plane.
The content of the invention
The technical problem to be solved in the present invention is：In order to overcome, electrification structure complexity cost is high in the prior art and safety is
The relatively low deficiencies of number, there is provided a kind of solar power generation simple in structure and low in cost and safety coefficient it is higher there is self-powered ability
Unmanned plane.
The technical solution adopted for the present invention to solve the technical problems is：A kind of unmanned plane with self-powered ability, bag
Include body, the TRT being arranged on above body and aviation mechanism, be arranged on the supporting mechanism and Distance-sensing of body bottom portion
Device, the body are provided with indicator lamp；
The supporting mechanism includes support frame and some vertically arranged buffer structures, the buffer structure are arranged on support
The lower section of frame, the buffer structure include housing, are arranged on the air inlet of housing side and are ramed, and are provided with the housing slow
Block, airbag and two springs are rushed, the buffer stopper is fixedly installed on the top of enclosure interior, and the airbag is arranged on the interior of housing
Portion and positioned at the lower section of buffer stopper, is provided with micro air pump in the airbag, the airbag connects with air inlet, described to be ramed
Vertical cross-section is I shapes, and the upper end ramed is located at the inside of housing, and the lower end ramed is located at the outside of housing,
Two springs are arranged at the inside of housing and positioned at the both sides ramed, and one end of the spring is fixed on the bottom of enclosure interior
Portion, the other end of the spring are fixed on the bottom by upper end of raming；
Central processing unit is provided with the body, the range sensor and micro air pump are electrically connected with central processing unit
Connect；
The TRT includes solar-electricity source module, and the solar-electricity source module includes solar-electricity source circuit,
The solar-electricity source circuit include silicon photocell, the first electric capacity, the second electric capacity, the 3rd electric capacity, first resistor, second resistance,
Adjustable resistance, transformer, triode, the first diode and voltage-regulator diode, the transformer are provided with two-way input side, and two-way is defeated
It is respectively first via input side and the second road input side to enter side, the first via input side of the transformer be provided with first input end and
Second input, the second road input side of the transformer are provided with the 3rd input and the 4th input, and the of the transformer
The parallel circuit and the base stage of triode that the first input end of input side is made up of adjustable resistance and the second electric capacity all the way connect,
The base stage of the triode respectively with the second input of the first via input side of transformer and the second road input side of transformer
The connection of the 3rd input, the colelctor electrode of the 4th input of the second road input side of the transformer and triode connects, institute
The emitter stage for stating triode is connected by the base stage of silicon photocell and triode, and the silicon photocell is in parallel with the first electric capacity, institute
State transformer and be provided with outlet side all the way, the outlet side all the way of the transformer is provided with the first output end and the second output end, described
First output end of the outlet side all the way of transformer is connected with the anode of the first diode, the negative electrode difference of first diode
It is connected with first resistor and second resistance, the first output end of the outlet side all the way of the transformer passes through the first diode and
The series circuit of three electric capacity composition is connected with the second output end of outlet side all the way, the anode and transformer of the voltage-regulator diode
Outlet side all the way the connection of the second output end, the negative electrode of the voltage-regulator diode passes through second resistance and the moon of the first diode
Pole connects.
Preferably, in order to ensure unmanned plane can stabilized flight, the aviation mechanism includes four flying units, described
Flying unit is circumferentially evenly distributed on the periphery of body, and the flying unit includes support and flight component, and the one of the support
End is fixed on body, and the other end and the flight component of the support are fixed, and the flight component is included positioned at support both sides
And the motor being vertically arranged, some blades are circumferentially uniformly provided with the drive shaft of the motor.
Preferably, using DC motor Driver power it is strong the characteristics of, it is winged to improve in order to improve the driving force of motor
Row ability, the motor are direct current generator.
Preferably, in order to reduce influence of the temperature to solar-electricity source circuit, the first resistor and second resistance
Temperature drift coefficient is 5%ppm.
Preferably, the triode is NPN type triode.
Preferably, in order to ensure the solar power generation of unmanned plane, the TRT includes solar panels.
Preferably, the characteristics of and stability strong using CNT spring is high, in order to ensure that buffer structure is stable
Buffer capacity, the spring is CNT spring.
Preferably, the characteristics of being unlikely to deform by force using rubber cotton elasticity, in order to strengthen the cushioning effect of buffer structure, institute
It is rubber cotton to state buffer stopper.
The invention has the advantages that should have in the solar-electricity source circuit of unmanned plane of self-powered ability, pass through silicon
Photocell converts solar energy into voltage, drives the conducting of triode, then carries out isolation conversion by transformer, then realizes
Conversion and collection to solar energy, conventional component is employed in the circuit, and it is simple in construction, while ensure that performance
Its production cost is also reduced, improves the market competitiveness of unmanned plane, moreover, utilizes the micro air pump in buffer gear
Make first-level buffer to air bag inflator, while safe system is improved to being made level 2 buffering by the upward elastic force of generation of raming by spring
Number, greatly reduce possibility impaired during its landing.
Brief description of the drawings
The present invention is further described with reference to the accompanying drawings and examples.
Fig. 1 is the structural representation of the unmanned plane with self-powered ability of the present invention；
Fig. 2 is the structural representation of the unmanned plane with self-powered ability of the present invention；
Fig. 3 is the structural representation of the buffer structure of the unmanned plane with self-powered ability of the present invention；
Fig. 4 is the circuit theory diagrams of the solar-electricity source circuit of the unmanned plane with self-powered ability of the present invention；
In figure：1. TRT, 2. bodies, 3. blades, 4. supports, 5. support frames, 6. motors, 7. Distance-sensings
Device, 8. indicator lamps, 9. buffer structures, 10. buffer stoppers, 11. airbags, 12. air inlets, 13. housings, 14. springs, 15. miniature gas
Pump, 16. are ramed, EC. silicon photocells, the electric capacity of C1. first, the electric capacity of C2. second, the electric capacity of C3. the 3rd, R1. first resistors, R2.
Second resistance, RP1. adjustable resistances, T1. transformers, Q1. triodes, the diodes of D1. first, D2. voltage-regulator diodes.
Embodiment
In conjunction with the accompanying drawings, the present invention is further explained in detail.These accompanying drawings are simplified schematic diagram, only with
Illustration illustrates the basic structure of the present invention, therefore it only shows the composition relevant with the present invention.
As Figure 1-Figure 4, a kind of unmanned plane with self-powered ability, including body 2, it is arranged on the top of body 2
TRT 1 and aviation mechanism, the supporting mechanism and range sensor 7 that are arranged on the bottom of body 2, the body 2, which is provided with, to be referred to
Show lamp 8；
The supporting mechanism includes support frame 5 and some vertically arranged buffer structures 9, the buffer structure 9 are arranged on
The lower section of support frame 5, the buffer structure 9 include housing 13, are arranged on the air inlet 12 of the side of housing 13 and are ramed 16, institute
State in housing 13 and be provided with buffer stopper 10, airbag 11 and two springs 14, the buffer stopper 10 is fixedly installed on inside housing 13
Top, the airbag 11 are arranged on the inside of housing 13 and are provided with miniature gas in the lower section of buffer stopper 10, the airbag 11
Pump 15, the airbag 11 are connected with air inlet 12, and described by 16 vertical cross-section of raming is I shapes, it is described by ram 16 upper end
Positioned at the inside of housing 13, described to be located at the outside of housing 13 by 16 lower end of raming, two springs 14 are arranged at housing 13
Inside and positioned at by ram 16 both sides, one end of the spring 14 is fixed on the bottom inside housing 13, the spring 14
The other end be fixed on bottom by 16 upper ends of raming；
Central processing unit is provided with the body 2, the range sensor 7 and micro air pump 15 are electric with central processing unit
Connection；
The solar-electricity source module includes solar-electricity source circuit, and the solar-electricity source circuit includes silicon photocell
EC, the first electric capacity C1, the second electric capacity C2, the 3rd electric capacity C3, first resistor R1, second resistance R2, adjustable resistance RP1, transformer
T1, triode Q1, the first diode D1 and voltage-regulator diode D2, the transformer T1 are provided with two-way input side, two-way input side
Respectively first via input side and the second road input side, the first via input side of the transformer T1 are provided with first input end and the
Two inputs, the second road input side of the transformer T1 are provided with the 3rd input and the 4th input, the transformer T1's
The first input end of first via input side is by the parallel circuit that adjustable resistance RP1 and the second electric capacity C2 is formed with triode Q1's
Base stage connects, the base stage of the triode Q1 the second input and transformer T1 with transformer T1 first via input side respectively
The second road input side the 3rd input connection, the 4th input and triode of the second road input side of the transformer T1
Q1 colelctor electrode connection, the emitter stage of the triode Q1 are connected by silicon photocell EC with triode Q1 base stage, the silicon
Photocell EC is in parallel with the first electric capacity C1, and the transformer T1 is provided with outlet side all the way, the outlet side all the way of the transformer T1
Provided with the first output end and the second output end, the first output end of the outlet side all the way of the transformer T1 and the first diode D1
Anode connection, the negative electrode of the first diode D1 is connected with first resistor R1 and second resistance R2 respectively, the transformer
First output end of T1 outlet side all the way by the series circuit that the first diode D1 and the 3rd electric capacity C3 are formed with it is defeated all the way
Go out the second output end connection of side, the second output end of the anode of the voltage-regulator diode D2 and transformer T1 outlet side all the way
Connection, the negative electrode of the voltage-regulator diode D2 are connected by second resistance R2 with the first diode D1 negative electrode.
Preferably, in order to ensure unmanned plane can stabilized flight, the aviation mechanism includes four flying units, described
Flying unit is circumferentially evenly distributed on the periphery of body 2, and the flying unit includes support 4 and flight component, the support 4
One end is fixed on body 2, and the other end and the flight component of the support 4 are fixed, and the flight component includes being located at 4 liang of support
Side and the motor 6 that is vertically arranged, be circumferentially uniformly provided with some blades 3 in the drive shaft of the motor 6.
Preferably, using DC motor Driver power it is strong the characteristics of, it is winged to improve in order to improve the driving force of motor 6
Row ability, the motor 6 are direct current generator.
Preferably, in order to reduce influence of the temperature to solar-electricity source circuit, the first resistor R1 and second resistance
R2 temperature drift coefficient is 5%ppm.
Preferably, the triode Q1 is NPN type triode.
Preferably, in order to ensure the solar power generation of unmanned plane, the TRT 1 includes solar panels.
Preferably, the characteristics of and stability strong using CNT spring is high, in order to ensure the stabilization of buffer structure 9
Buffer capacity, the spring 14 is CNT spring.
Preferably, the characteristics of being unlikely to deform by force using rubber cotton elasticity, in order to strengthen the cushioning effect of buffer structure 9,
The buffer stopper 10 is rubber cotton.
During the unmanned plane during flying, the required energy is persistently provided by the solar panels in TRT 1, will in solar panels
When luminous energy changes into electric energy, the sun-generated electric power modular circuit continuous service inside TRT 1, in solar-electricity source module
In, the mode that electric energy acquisition is carried out to silicon photocell EC is employed in solar-electricity source circuit, wherein silicon photocell EC is a kind of
The physical battery of electric energy can directly be converted light energy into, have body it is small, it is in light weight, easy to use and storage, it is anti-to temperature change
The features such as small is answered, so as to greatly reduce the volume of solar-electricity source circuit, improves that its is realisation, and its service life
It is almost permanent, typically at least also in ten or twenty more than year, so as to improve the service life of the circuit, improve unmanned plane
Service life.Moreover, conventional component is employed in the circuit, and it is simple in construction, while ensure that performance
Its production cost is also reduced, improves the market competitiveness of unmanned plane.The operation principle of the circuit is：Silicon photocell EC will too
Sun can be converted into voltage, then drive triode Q1 conducting, then carry out isolation conversion by transformer T1, pass through the first electricity
The voltage storage that R1 and second resistance R2 carries out multiscale is hindered, realizes the conversion and collection to solar energy.Wherein, adjustable resistance
RP1 and the second electric capacity C2 is used for adjusting triode Q1 ON time and sensitivity, so as to serve triode Q1 soft starts
Effect, prevent triode Q1 from reducing service life due to long-term switch.
When unmanned plane needs landing, the height and position of unmanned plane is monitored by range sensor 7, and transfer data to this
Central processing unit in body 2, after in the range of certain altitude, buffer gear 9 is started working, internal micro air pump 15 from
Air inlet 12 makes airbag 11 expand after sucking air, facilitates unmanned plane to make corresponding cushioning effect when contacting ground, meanwhile, in order to
Cushion effect is improved, behind 16 contact ground of being ramed, the spring 14 of the inside bottom side of housing 13 of buffer structure 9 deforms upon, right
Upward elastic force is produced by raming, further makees buffering and uses, safety coefficient during unmanned plane landing is improved, greatly reduces
Impaired possibility when it lands.
Compared with prior art, should have in the solar-electricity source circuit of unmanned plane of self-powered ability, and pass through silicon photoelectricity
Pond EC converts solar energy into voltage, driving triode Q1 conducting, then carries out isolation conversion by transformer T1, then realizes
Conversion and collection to solar energy, conventional component is employed in the circuit, and it is simple in construction, it ensure that the same of performance
When also reduce its production cost, the market competitiveness of unmanned plane is improved, moreover, using miniature in buffer gear 9
Air pump 15 makees first-level buffer to the inflation of airbag 11, while by spring 14 to being made level 2 buffering by the upward elastic force of 16 generations of raming,
Safety coefficient is improved, greatly reduces possibility impaired during its landing.
It is complete by above-mentioned description, relevant staff using the above-mentioned desirable embodiment according to the present invention as enlightenment
Various changes and amendments can be carried out without departing from the scope of the technological thought of the present invention' entirely.The technology of this invention
Property scope is not limited to the content on specification, it is necessary to determines its technical scope according to right.
Claims (8)
1. a kind of unmanned plane with self-powered ability, it is characterised in that including body (2), the hair being arranged on above body (2)
Electric installation (1) and aviation mechanism, the supporting mechanism and range sensor (7) that are arranged on body (2) bottom, on the body (2)
Provided with indicator lamp (8)；
The supporting mechanism includes support frame (5) and some vertically arranged buffer structures (9), and the buffer structure (9) is set
In the lower section of support frame (5), the buffer structure (9) includes housing (13), is arranged on the air inlet (12) of housing (13) side
With ramed (16), the housing (13) is interior to be provided with buffer stopper (10), airbag (11) and two springs (14), the buffer stopper
(10) the internal top of housing (13) is fixedly installed on, the airbag (11) is arranged on the inside of housing (13) and is located at buffer stopper
(10) lower section, is provided with micro air pump (15) in the airbag (11), the airbag (11) connects with air inlet (12), it is described by
The vertical cross-section of (16) of raming is I shapes, and the upper end for being ramed (16) is located at the inside of housing (13), described to be ramed (16)
Lower end be located at the outside of housing (13), two springs (14) are arranged at the inside of housing (13) and positioned at being ramed (16)
Both sides, one end of the spring (14) are fixed on the internal bottom of housing (13), the other end of the spring (14) be fixed on by
Ram the bottom of (16) upper end；
It is provided with central processing unit in the body (2), the range sensor (7) and micro air pump (15) are and central processing unit
Electrical connection；
The TRT (1) includes solar-electricity source module, and the solar-electricity source module includes solar-electricity source circuit, institute
Stating solar-electricity source circuit includes silicon photocell (EC), the first electric capacity (C1), the second electric capacity (C2), the 3rd electric capacity (C3), first
Resistance (R1), second resistance (R2), adjustable resistance (RP1), transformer (T1), triode (Q1), the first diode (D1) and steady
Diode (D2) is pressed, the transformer (T1) is provided with two-way input side, and two-way input side is respectively first via input side and second
Road input side, the first via input side of the transformer (T1) are provided with first input end and the second input, the transformer
(T1) the second road input side is provided with the 3rd input and the 4th input, and the of the first via input side of the transformer (T1)
The parallel circuit that one input is made up of adjustable resistance (RP1) and the second electric capacity (C2) is connected with the base stage of triode (Q1),
The base stage of the triode (Q1) respectively with the second input of the first via input side of transformer (T1) and transformer (T1)
The 3rd input connection of second road input side, the 4th input and triode of the second road input side of the transformer (T1)
(Q1) colelctor electrode connection, the emitter stage of the triode (Q1) are connected by the base stage of silicon photocell (EC) and triode (Q1)
Connect, the silicon photocell (EC) is in parallel with the first electric capacity (C1), and the transformer (T1) is provided with outlet side all the way, the transformer
(T1) outlet side all the way is provided with the first output end and the second output end, and the first of the outlet side all the way of the transformer (T1) is defeated
Go out end to be connected with the anode of the first diode (D1), the negative electrode of first diode (D1) respectively with first resistor (R1) and the
Two resistance (R2) connect, and the first output end of the outlet side all the way of the transformer (T1) passes through the first diode (D1) and the 3rd
Electric capacity (C3) composition series circuit be connected with the second output end of outlet side all the way, the anode of the voltage-regulator diode (D2) and
The second output end connection of the outlet side all the way of transformer (T1), the negative electrode of the voltage-regulator diode (D2) pass through second resistance
(R2) negative electrode with the first diode (D1) is connected.
2. there is the unmanned plane of self-powered ability as claimed in claim 1, it is characterised in that the aviation mechanism includes four
Flying unit, the flying unit are circumferentially evenly distributed on the periphery of body (2), and the flying unit includes support (4) and flown
Row component, one end of the support (4) are fixed on body (2), and the other end of the support (4) is fixed with flight component, institute
Stating flight component includes motor (6) that is positioned at support (4) both sides and being vertically arranged, the driving of the motor (6)
Some blades (3) are circumferentially uniformly provided with axle.
3. there is the unmanned plane of self-powered ability as claimed in claim 2, it is characterised in that the motor (6) is straight
Flow motor.
4. there is the unmanned plane of self-powered ability as claimed in claim 1, it is characterised in that the first resistor (R1) and the
The temperature drift coefficient of two resistance (R2) is 5%ppm.
5. there is the unmanned plane of self-powered ability as claimed in claim 1, it is characterised in that the triode (Q1) is NPN
Type triode.
6. there is the unmanned plane of self-powered ability as claimed in claim 1, it is characterised in that the TRT (1) includes
Solar panels.
7. there is the unmanned plane of self-powered ability as claimed in claim 1, it is characterised in that the spring (14) is carbon nanometer
Pipe spring.
8. there is the unmanned plane of self-powered ability as claimed in claim 1, it is characterised in that the buffer stopper (10) is rubber
Cotton.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610222539.0A CN105882946B (en) | 2016-04-12 | 2016-04-12 | A kind of unmanned plane with self-powered ability |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610222539.0A CN105882946B (en) | 2016-04-12 | 2016-04-12 | A kind of unmanned plane with self-powered ability |
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| CN105882946A CN105882946A (en) | 2016-08-24 |
| CN105882946B true CN105882946B (en) | 2018-01-05 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628159B (en) * | 2016-09-22 | 2018-11-06 | 安徽百舸争流农业科技有限公司 | A kind of unmanned plane for agricultural production based on Internet of Things |
| CN107140210A (en) * | 2017-05-06 | 2017-09-08 | 深圳市雷凌广通技术研发有限公司 | A kind of Intelligent unattended machine with remote monitoring ability |
| CN107264785A (en) * | 2017-06-05 | 2017-10-20 | 深圳市雷凌广通技术研发有限公司 | A kind of Intelligent unattended machine for express transportation |
| CN108163186A (en) * | 2018-01-16 | 2018-06-15 | 安徽翼讯飞行安全技术有限公司 | A kind of unmanned plane landing damping device |
| CN108263599B (en) * | 2018-04-02 | 2019-08-20 | 赵学明 | Unmanned aerial vehicle, unmanned aerial vehicle descending buffer device |
| CN109263865B (en) * | 2018-10-08 | 2020-06-26 | 东阳市天齐科技有限公司 | Many rotor unmanned aerial vehicle's activity undercarriage |
| CN109334983A (en) * | 2018-12-01 | 2019-02-15 | 江苏云端智能科技有限公司 | A kind of novel unmanned plane |
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| US5237233A (en) * | 1989-03-03 | 1993-08-17 | E. F. Johnson Company | Optoelectronic active circuit element |
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| CN105882946A (en) | 2016-08-24 |
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