CN105882946A - Novel UAV (unmanned aerial vehicle) having self-powering capacity - Google Patents
Novel UAV (unmanned aerial vehicle) having self-powering capacity Download PDFInfo
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- CN105882946A CN105882946A CN201610222539.0A CN201610222539A CN105882946A CN 105882946 A CN105882946 A CN 105882946A CN 201610222539 A CN201610222539 A CN 201610222539A CN 105882946 A CN105882946 A CN 105882946A
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- transformator
- self
- unmanned plane
- resistance
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Classifications
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- 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; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, 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
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- 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
Abstract
The invention relates to a novel UAV (unmanned aerial vehicle) having self-powering capacity. The UAV comprises a body, a power generation device and a flying mechanism which are arranged above the body as well as a supporting mechanism and a range sensor which are arranged at the bottom of the body, wherein an indicating lamp is arranged on the body. In a solar power supply circuit of the novel UAV having the self-powering capacity, solar energy is converted into voltage by the aid of a silicon photocell, a triode is driven to be connected, isolated conversion is performed by the aid of a transformer, and then solar energy is converted and collected; the circuit adopts conventional components and is simple in structure, the production cost of the circuit is reduced while the performance is guaranteed, the market competitiveness of the UAV is improved, moreover, air bags are inflated by micro air pumps in buffer mechanisms for primary buffering, meanwhile, upward elastic force is produced on impacted heads by the aid of springs for secondary buffering, so that the safety coefficient is increased, and the probability of damage to the UAV during landing is greatly reduced.
Description
Technical field
The present invention relates to a kind of novel unmanned plane with self-powered ability.
Background technology
Along with the technology of automation field develops, in recent years, unmanned plane with its simple structure, easily
The features such as operation and autonomous operation are more and more paid attention to, and unmanned plane is exhibited one's skill to the full in all trades and professions,
Progress in the production management of the daily life of ordinary consumer, work entertainment and enterprise.
In existing unmanned plane, great majority are all the battery-driven modes that uses, but when unmanned plane needs
When the time of work to be performed is longer, owing to accumulator capacity is limited, task often cannot be completed.And portion
Point unmanned plane have employed the mode of solar electrical energy generation to improve the working time of unmanned plane, but due to its sun
Energy electricity-generating circuit structure is complicated, and technique is too much, substantially increases the production cost of unmanned plane, reduces its city
Competitiveness, unmanned plane lacks corresponding protective measure simultaneously so that it is in descent easily because of under reduction of speed
Spending the reason such as fast causes unmanned plane to suffer huge impulsive force when landing, and causes unmanned plane to damage, further
Reduce the safety coefficient of unmanned plane.
Summary of the invention
The technical problem to be solved in the present invention is: in order to overcome in prior art electrification structure complexity cost high and
The deficiency that safety coefficient is relatively low, it is provided that a kind of solar electrical energy generation simple in structure and low in cost and safety coefficient are higher
The novel unmanned plane with self-powered ability.
The technical solution adopted for the present invention to solve the technical problems is: a kind of have the novel of self-powered ability
Unmanned plane, including body, is arranged on the TRT above body and aviation mechanism, is arranged on body bottom portion
Supporting mechanism and range sensor, described body is provided with display lamp；
Described supporting mechanism includes bracing frame and some vertically arranged buffer structures, and described buffer structure is arranged
In the lower section of bracing frame, described buffer structure includes housing, the air inlet being arranged on housing side and is ramed,
Being provided with buffer stopper, airbag and two springs in described housing, described buffer stopper is fixedly installed on enclosure interior
Top, described airbag is arranged on the inside of housing and is positioned at the lower section of buffer stopper, being provided with miniature in described airbag
Air pump, described airbag connects with air inlet, the described vertical cross-section ramed is I shape, described is ramed
Upper end is positioned at the inside of housing, and the described lower end ramed is positioned at the outside of housing, and two springs are arranged at
The inside of housing and be positioned at the both sides ramed, one end of described spring is fixed on the bottom of enclosure interior, institute
The other end stating spring is fixed on the bottom by upper end of raming；
Described the internal central processing unit that is provided with, described range sensor and micro air pump are all and central processing unit
Electrical connection；
Described solar-electricity source module includes that solar-electricity source circuit, described solar-electricity source circuit include silicon light
Battery, the first electric capacity, the second electric capacity, the 3rd electric capacity, the first resistance, the second resistance, adjustable resistance, change
Depressor, audion, the first diode and Zener diode, described transformator is provided with two-way input side, two-way
Input side is respectively first via input side and the second road input side, and the first via input side of described transformator is provided with
First input end and the second input, the second road input side of described transformator is provided with the 3rd input and the 4th
Input, the first input end of the first via input side of described transformator passes through adjustable resistance and the second capacitance group
The parallel circuit become is connected with the base stage of audion, the base stage of described audion respectively with the first via of transformator
3rd input of the second input of input side and the second road input side of transformator connects, described transformator
The four-input terminal of the second road input side be connected with the colelctor electrode of audion, the emitter stage of described audion leads to
Crossing silicon cell to be connected with the base stage of audion, described silicon cell and the first electric capacity are in parallel, described transformator
Being provided with a road outlet side, a road outlet side of described transformator is provided with the first outfan and the second outfan, institute
The anode of the first outfan and the first diode of stating a road outlet side of transformator connects, described one or two pole
The negative electrode of pipe is connected with the first resistance and the second resistance respectively, and the first of a road outlet side of described transformator is defeated
Go out end by the second outfan of the first diode and the series circuit of the 3rd electric capacity composition and a road outlet side even
Connecing, the anode of described Zener diode is connected with the second outfan of a road outlet side of transformator, described surely
The negative electrode of pressure diode is connected by the negative electrode of the second resistance and the first diode.
As preferably, in order to ensure unmanned plane can stabilized flight, described aviation mechanism includes that four flights are single
Unit, described flying unit circumference is evenly distributed on the periphery of body, and described flying unit includes support and flight
Assembly, one end of described support is fixed on body, and the other end of described support is fixed with flight assembly, institute
State flight assembly and include driving motor that is that be positioned at support both sides and that be vertically arranged, the driving of described driving motor
On axle, circumference is uniformly provided with some blades.
As preferably, utilize the feature that DC motor Driver power is strong, in order to improve drive motor driving force with
Improving flight performance, described driving motor is direct current generator.
As preferably, in order to reduce the temperature impact on solar-electricity source circuit, described first resistance and second
The temperature drift coefficient of resistance is 5%ppm.
As preferably, described audion is NPN type triode.
As preferably, in order to ensure the solar electrical energy generation of unmanned plane, described TRT includes solar panels.
As preferably, utilize the feature that CNT spring is strong and stability is high, in order to ensure buffering knot
The buffer capacity that structure is stable, described spring is CNT spring.
As preferably, utilize the elastic strong on-deformable feature of rubber cotton, in order to strengthen the buffering of buffer structure
Effect, described buffer stopper is rubber cotton.
The invention has the beneficial effects as follows, this has the solar-electricity source circuit of novel unmanned plane of self-powered ability
In, convert solar energy into voltage by silicon cell, drive the conducting of audion, then entered by transformator
Row isolation conversion, achieves the conversion to solar energy and collection subsequently, have employed first device of routine in this circuit
Part, and simple in construction, it is ensured that also reduce its production cost while performance, improve unmanned plane
The market competitiveness, moreover, utilizes the micro air pump in buffer gear that air bag inflator is made first-level buffer,
Made level 2 buffering by spring to by the elastic force produced upwards of raming simultaneously, improve safety coefficient, be substantially reduced
Probability impaired when it lands.
Accompanying drawing explanation
The present invention is further described with embodiment below in conjunction with the accompanying drawings.
Fig. 1 is the structural representation of the novel unmanned plane with self-powered ability of the present invention；
Fig. 2 is the structural representation of the novel unmanned plane with self-powered ability of the present invention；
Fig. 3 is the structural representation of the buffer structure of the novel unmanned plane with self-powered ability of the present invention；
Fig. 4 is that the circuit of the solar-electricity source circuit of the novel unmanned plane with self-powered ability of the present invention is former
Reason figure；
In figure: 1. TRT, 2. body, 3. blade, 4. support, 5. bracing frame, 6. drive motor,
7. range sensor, 8. display lamp, 9. buffer structure, 10. buffer stopper, 11. airbags, 12. air inlets, 13.
Housing, 14. springs, 15. micro air pumps, 16. are ramed, EC. silicon cell, C1. the first electric capacity, C2.
Second electric capacity, C3. the 3rd electric capacity, R1. the first resistance, R2. the second resistance, RP1. adjustable resistance, T1. becomes
Depressor, Q1. audion, D1. the first diode, D2. Zener diode.
Detailed description of the invention
In conjunction with the accompanying drawings, the present invention is further detailed explanation.These accompanying drawings are the schematic diagram of simplification,
The basic structure of the present invention is described the most in a schematic way, and therefore it only shows the composition relevant with the present invention.
As Figure 1-Figure 4, a kind of novel unmanned plane with self-powered ability, including body 2, arrange
TRT 1 and aviation mechanism above body 2, it is arranged on the supporting mechanism bottom body 2 and distance
Sensor 7, described body 2 is provided with display lamp 8；
Described supporting mechanism includes bracing frame 5 and some vertically arranged buffer structures 9, described buffer structure 9
Being arranged on the lower section of bracing frame 5, described buffer structure 9 includes housing 13, is arranged on entering of housing 13 side
QI KOU 12 and ramed 16, is provided with buffer stopper 10, airbag 11 and two springs 14 in described housing 13,
Described buffer stopper 10 is fixedly installed on the top within housing 13, and described airbag 11 is arranged on housing 13
Internal and be positioned at the lower section of buffer stopper 10, be provided with micro air pump 15 in described airbag 11, described airbag 11 with
Air inlet 12 connects, described by ram 16 vertical cross-section be I shape, described by ram 16 upper end be positioned at
The inside of housing 13, described by ram 16 lower end be positioned at the outside of housing 13, two springs 14 are all provided with
Put the inside of housing 13 and be positioned at by ram 16 both sides, one end of described spring 14 is fixed on housing 13
Internal bottom, the other end of described spring 14 is fixed on the bottom by 16 upper ends of raming；
Being provided with central processing unit in described body 2, described range sensor 7 and micro air pump 15 are all with central
Processor electrically connects；
Described solar-electricity source module includes that solar-electricity source circuit, described solar-electricity source circuit include silicon light
Battery EC, the first electric capacity C1, the second electric capacity C2, the 3rd electric capacity C3, the first resistance R1, the second resistance R2,
Adjustable resistance RP1, transformator T1, audion Q1, the first diode D1 and Zener diode D2, described
Transformator T1 is provided with two-way input side, and two-way input side is respectively first via input side and the second road input side,
The first via input side of described transformator T1 is provided with first input end and the second input, described transformator T1
The second road input side be provided with the 3rd input and four-input terminal, the first via input side of described transformator T1
First input end by parallel circuit and the audion Q1 of adjustable resistance RP1 and the second electric capacity C2 composition
Base stage connects, the base stage of described audion Q1 respectively with the second input of the first via input side of transformator T1
3rd input of the second road input side of end and transformator T1 connects, and second tunnel of described transformator T1 is defeated
The colelctor electrode of the four-input terminal and audion Q1 that enter side is connected, and the emitter stage of described audion Q1 passes through silicon
Light cell EC is connected with the base stage of audion Q1, and described silicon cell EC and the first electric capacity C1 is in parallel, institute
State transformator T1 and be provided with a road outlet side, a road outlet side of described transformator T1 be provided with the first outfan and
Second outfan, the first outfan of a road outlet side of described transformator T1 and the sun of the first diode D1
Pole connects, and the negative electrode of described first diode D1 is connected with the first resistance R1 and the second resistance R2 respectively, institute
First outfan of the road outlet side stating transformator T1 consists of the first diode D1 and the 3rd electric capacity C3
Series circuit and a road outlet side second outfan connect, the anode of described Zener diode D2 and transformation
Second outfan of the one road outlet side of device T1 connects, and the negative electrode of described Zener diode D2 is by the second electricity
The negative electrode of resistance R2 and the first diode D1 connects.
As preferably, in order to ensure unmanned plane can stabilized flight, described aviation mechanism includes that four flights are single
Unit, described flying unit circumference is evenly distributed on the periphery of body 2, and described flying unit includes support 4 He
Flight assembly, one end of described support 4 is fixed on body 2, the other end of described support 4 and flight crew
Part is fixed, and described flight assembly includes driving motor 6 that is that be positioned at support 4 both sides and that be vertically arranged, described in drive
In the drive shaft of galvanic electricity machine 6, circumference is uniformly provided with some blades 3.
As preferably, utilize the feature that DC motor Driver power is strong, in order to improve the driving force driving motor 6
To improve flight performance, described driving motor 6 is direct current generator.
As preferably, in order to reduce the temperature impact on solar-electricity source circuit, described first resistance R1 and
The temperature drift coefficient of two resistance R2 is 5%ppm.
As preferably, described audion Q1 is NPN type triode.
As preferably, in order to ensure the solar electrical energy generation of unmanned plane, described TRT 1 includes solar panels.
As preferably, utilize the feature that CNT spring is strong and stability is high, in order to ensure buffering knot
The buffer capacity that structure 9 is stable, described spring 14 is CNT spring.
As preferably, utilize the elastic strong on-deformable feature of rubber cotton, in order to strengthen the slow of buffer structure 9
Punching effect, described buffer stopper 10 is rubber cotton.
During this unmanned plane during flying, the required energy is persistently provided by the solar panels in TRT 1, too
When luminous energy is changed into electric energy by sun energy plate, the sun-generated electric power modular circuit continuous service within TRT 1,
In solar-electricity source module, solar-electricity source circuit have employed silicon cell EC is carried out electric energy acquisition
Mode, wherein silicon cell EC is a kind of physical battery that can directly convert light energy into electric energy, have body little,
Lightweight, be easy to use and storage, to the variations in temperature reaction feature such as little, thus greatly reduce solar energy
The volume of power circuit, improves that it is realisation, and its service life is the most permanent, the most extremely
Few also more than ten or twenty year, thus improve the service life of this circuit, improve the use longevity of unmanned plane
Life.Moreover, this circuit have employed the components and parts of routine, and simple in construction, it is ensured that performance
Also reduce its production cost simultaneously, improve the market competitiveness of unmanned plane.The operation principle of this circuit is:
Silicon cell EC converts solar energy into voltage, with the conducting of rear drive audion Q1, passes through transformation subsequently
Device T1 carries out isolation conversion, and the voltage being carried out multiscale by the first resistance R1 and the second resistance R2 is stored,
Achieve the conversion to solar energy and collection.Wherein, adjustable resistance RP1 and the second electric capacity C2 is used for regulating three
The ON time of pole pipe Q1 and sensitivity, thus serve the effect of audion Q1 soft start, prevent three poles
Pipe Q1 reduces service life due to long-term switch.
When unmanned plane needs landing, range sensor 7 monitor the height and position of unmanned plane, and by data
Sending the central processing unit in body 2 to, after being positioned in the range of certain altitude, buffer gear 9 starts work
Making, internal micro air pump 15 makes airbag 11 expand after air inlet 12 sucks air, facilitates unmanned plane to connect
Corresponding cushioning effect is made during tread surface, meanwhile, in order to improve cushion effect, behind 16 contact ground of being ramed,
The spring 14 of the internal bottom side of the housing 13 of buffer structure 9 deforms upon, to the elastic force produced by raming upwards,
Make buffering further to use, improve safety coefficient during unmanned plane landing, greatly reduce when it lands and be subject to
The probability damaged.
Compared with prior art, in the solar-electricity source circuit of this novel unmanned plane with self-powered ability,
Convert solar energy into voltage by silicon cell EC, drive the conducting of audion Q1, then pass through transformator
T1 carries out isolation conversion, achieves the conversion to solar energy and collection subsequently, have employed routine in this circuit
Components and parts, and simple in construction, it is ensured that also reduce its production cost while performance, improve unmanned
The market competitiveness of machine, moreover, utilizes the micro air pump 15 in buffer gear 9 to inflate airbag 11
Make first-level buffer, made level 2 buffering by spring 14 to by 16 generations elastic force upwards of raming simultaneously, improve
Safety coefficient, greatly reduces probability impaired when it lands.
With the above-mentioned desirable embodiment according to the present invention for enlightenment, by above-mentioned description, related work
Personnel can carry out various change and amendment completely in the range of without departing from this invention technological thought.
The content that the technical scope of this invention is not limited in description, it is necessary to according to right
Determine its technical scope.
Claims (8)
1. a novel unmanned plane with self-powered ability, it is characterised in that include body (2), arrange
TRT (1) and aviation mechanism in body (2) top, it is arranged on the support machine bottom body (2)
Structure and range sensor (7), described body (2) is provided with display lamp (8)；
Described supporting mechanism includes bracing frame (5) and some vertically arranged buffer structures (9), described buffering
Structure (9) is arranged on the lower section of bracing frame (5), and described buffer structure (9) includes housing (13), sets
Put the air inlet (12) in housing (13) side and ramed (16), be provided with slow in described housing (13)
Rushing block (10), airbag (11) and two springs (14), described buffer stopper (10) is fixedly installed on housing
(13) internal top, described airbag (11) is arranged on the inside of housing (13) and is positioned at buffer stopper (10)
Lower section, be provided with micro air pump (15) in described airbag (11), described airbag (11) and air inlet (12)
Connection, the vertical cross-section of described ramed (16) is I shape, and the described upper end being ramed (16) is positioned at shell
The inside of body (13), the described lower end being ramed (16) is positioned at the outside of housing (13), two springs
(14) it is arranged at the inside of housing (13) and is positioned at the both sides of ramed (16), described spring (14)
One end be fixed on the bottom that housing (13) is internal, the other end of described spring (14) is fixed on is ramed
(16) bottom of upper end；
Central processing unit, described range sensor (7) and micro air pump (15) it is provided with in described body (2)
All electrically connect with central processing unit；
Described solar-electricity source module includes that solar-electricity source circuit, described solar-electricity source circuit include silicon light
Battery (EC), the first electric capacity (C1), the second electric capacity (C2), the 3rd electric capacity (C3), the first resistance (R1),
Second resistance (R2), adjustable resistance (RP1), transformator (T1), audion (Q1), the first diode (D1)
With Zener diode (D2), described transformator (T1) is provided with two-way input side, and two-way input side is respectively
One road input side and the second road input side, the first via input side of described transformator (T1) is provided with the first input
End and the second input, the second road input side of described transformator (T1) is provided with the 3rd input and the 4th defeated
Enter end, the first input end of the first via input side of described transformator (T1) by adjustable resistance (RP1) and
The parallel circuit that second electric capacity (C2) forms is connected with the base stage of audion (Q1), described audion (Q1)
Base stage respectively with second input and the of transformator (T1) of the first via input side of transformator (T1)
3rd input of two road input sides connects, the 4th input of the second road input side of described transformator (T1)
End is connected with the colelctor electrode of audion (Q1), and the emitter stage of described audion (Q1) passes through silicon cell (EC)
Being connected with the base stage of audion (Q1), described silicon cell (EC) is in parallel with the first electric capacity (C1), institute
Stating transformator (T1) and be provided with a road outlet side, it is defeated that a road outlet side of described transformator (T1) is provided with first
Go out end and the second outfan, the first outfan of a road outlet side of described transformator (T1) and the one or two pole
Pipe (D1) anode connect, the negative electrode of described first diode (D1) respectively with the first resistance (R1) and
Second resistance (R2) connects, and the first outfan of a road outlet side of described transformator (T1) passes through first
Series circuit and the second outfan of a road outlet side that diode (D1) and the 3rd electric capacity (C3) form connect
Connect, the second outfan of a road outlet side of the anode of described Zener diode (D2) and transformator (T1)
Connecting, the negative electrode of described Zener diode (D2) is by the second resistance (R2) and the first diode (D1)
Negative electrode connect.
There is the novel unmanned plane of self-powered ability the most as claimed in claim 1, it is characterised in that described
Aviation mechanism includes four flying unit, and described flying unit circumference is evenly distributed on the periphery of body (2),
Described flying unit includes that support (4) and flight assembly, one end of described support (4) are fixed on body (2)
On, the other end of described support (4) is fixed with flight assembly, and described flight assembly includes being positioned at support (4)
Both sides and the driving motor (6) that is vertically arranged, in the drive shaft of described driving motor (6), circumference uniformly sets
There are some blades (3).
There is the novel unmanned plane of self-powered ability the most as claimed in claim 1, it is characterised in that described
Driving motor (6) is direct current generator.
There is the novel unmanned plane of self-powered ability the most as claimed in claim 1, it is characterised in that described
The temperature drift coefficient of the first resistance (R1) and the second resistance (R2) is 5%ppm.
There is the novel unmanned plane of self-powered ability the most as claimed in claim 1, it is characterised in that described
Audion (Q1) is NPN type triode.
There is the novel unmanned plane of self-powered ability the most as claimed in claim 1, it is characterised in that described
TRT (1) includes solar panels.
There is the novel unmanned plane of self-powered ability the most as claimed in claim 1, it is characterised in that described
Spring (14) is CNT spring.
There is the novel unmanned plane of self-powered ability the most as claimed in claim 1, it is characterised in that described
Buffer stopper (10) is rubber cotton.
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| CN201610222539.0A CN105882946B (en) | 2016-04-12 | 2016-04-12 | A kind of unmanned plane with self-powered ability |
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| CN106628159A (en) * | 2016-09-22 | 2017-05-10 | 广州市婵昕生物科技有限责任公司 | Unmanned plane based on Internet of Things and used for agricultural production |
| 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 |
| CN108263599A (en) * | 2018-04-02 | 2018-07-10 | 刘志舟 | Unmanned aerial vehicle, unmanned aerial vehicle descending buffer device |
| CN109263865A (en) * | 2018-10-08 | 2019-01-25 | 东阳市天齐科技有限公司 | The movable undercarriage of multi-rotor unmanned aerial vehicle |
| 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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