CN207166136U - A kind of aircraft energizer car - Google Patents
A kind of aircraft energizer car Download PDFInfo
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- CN207166136U CN207166136U CN201721203318.5U CN201721203318U CN207166136U CN 207166136 U CN207166136 U CN 207166136U CN 201721203318 U CN201721203318 U CN 201721203318U CN 207166136 U CN207166136 U CN 207166136U
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- aviation
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- power
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- 238000010248 power generation Methods 0.000 claims abstract description 11
- 238000004804 winding Methods 0.000 claims abstract description 6
- 239000003990 capacitor Substances 0.000 claims description 11
- 239000000178 monomer Substances 0.000 claims description 9
- 230000005611 electricity Effects 0.000 claims description 4
- 238000000034 method Methods 0.000 abstract description 3
- 238000010276 construction Methods 0.000 abstract description 2
- 230000007774 longterm Effects 0.000 abstract description 2
- 238000012544 monitoring process Methods 0.000 abstract description 2
- 230000007812 deficiency Effects 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 description 1
- QSNQXZYQEIKDPU-UHFFFAOYSA-N [Li].[Fe] Chemical compound [Li].[Fe] QSNQXZYQEIKDPU-UHFFFAOYSA-N 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 229910052698 phosphorus Inorganic materials 0.000 description 1
- 239000011574 phosphorus Substances 0.000 description 1
- 238000012876 topography Methods 0.000 description 1
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- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
It the utility model is related to a kind of aircraft energizer car,Including taking force power generation system,Power distribution cabinet,Switch board,Aviation dc source,Taking force power generation system,Power distribution cabinet and aviation dc source are sequentially connected,Power distribution cabinet and aviation dc source are connected to switch board,The supply vehicle also includes the charger being sequentially connected with power distribution cabinet,Super capacitance cell module and reversely charging protection device,With the sensing system of aviation dc source series winding,Recoil protection device is connected to the output end of aviation dc source,Charger,Super capacitance cell module,Reversely charging protection device and sensing system are connected to switch board,Supply vehicle described in the utility model is simple in construction,It is good that operability is installed,Power output can be doubled the above,Meet the requirement to input power when all helicopter types start,The demand of long-term combat duty has been ensured simultaneously,The output of power supply can also be controlled in addition,Whole process monitoring supply voltage and electric current,Ensure safety when aircraft starts.
Description
Technical field
The utility model belongs to field of power supplies, and in particular to a kind of aircraft energizer car.
Background technology
Aircraft floor supports power supply and is also referred to as aero-ground power, and it, which is acted on, mainly two aspects：First, opened for aircraft
It is dynamic that ground power supply is provided；Required power supply is provided second, being powered and checking for aircraft floor.Aero-ground power should be able to meet this two
The requirement of aspect, it can just smoothly complete ground safeguard task.At present, Chinese Helicopter power supply mode mainly has two ways：Ground
Face supply vehicle power supply and the power supply of portable field power supply, wherein supply vehicle power supply are divided into the power supply of AC power car, dc source car
Power supply, the power supply of ac-dc dual power supply car, at present supply vehicle use more：Electrical power generators are driven by gearbox power taking, it is converted
Aviation power supply is given afterwards；Vehicle-mounted independent high-power diesel electrical power generators, aviation power supply is given after converted.
However, there is power output deficiency in the first supply vehicle power supply mode, it is difficult to the shortcomings that meeting institute's organic type, second
The shortcomings of volume is big, noise is big, mobility is slightly poor be present in kind supply vehicle power supply mode.And portable field power supply is a kind of energy storage
Device, can only limited number of time startup aircraft, it is necessary to charged after electric energy is discharged, therefore there is limitation, can only be used as should
Urgent telegram source uses.
For example, China Patent No. 201610464999.4 discloses a kind of aircraft surface startup power supply.It is by module group
Box-like vehicle frame, three battery core modules, control module, output cable composition.The battery core module, control module and module combined type
Vehicle frame connects, and the output cable connects with control module.The advantages of the utility model：Domestic initiation uses phosphorus at battery core position
Sour lithium iron battery group substitutes 7-HK-182 lead-acid accumulators, and reliability is high；Profile uses optimization design, and build is compact, and charging is complete
Intellectuality, increase substantially the service life of equipment；Startup power supply is using modularized design especially suitable for a varied topography, emergent
The aircraft of the scenes such as rescue starts and energization Inspection；Battery capacity be it is maximum in the existing same type equipment in home and abroad, can
To realize the demand for task of working continuously for a long time；Equipment can meet the ground of all kinds of middle-size and small-size fixed wing aircrafts and helicopter
Startup and energization Inspection.But the invention is battery energy storage device, need to charge after discharging electric energy, have to startup aircraft secondary
Number limitation, has certain limitation.
Utility model content
The purpose of this utility model is in view of the shortcomings of the prior art, there is provided a kind of aircraft energizer car, Neng Gouzeng
Add power output, meet various aircraft power demands, while monitor supply voltage, electric current, ensure aircraft safety.
The technical scheme that the utility model solves above-mentioned technical problem is as follows：
The supply vehicle, including taking force power generation system, power distribution cabinet, switch board, aviation dc source, taking force power generation system,
Power distribution cabinet and aviation dc source are sequentially connected, and power distribution cabinet and aviation dc source are connected to switch board, the supply vehicle
Also include charger, super capacitance cell module and the reversely charging protection device being sequentially connected with power distribution cabinet, with aviation dc source
The sensing system of series winding, recoil protection device are connected to the output end of aviation dc source, charger, super capacitance cell mould
Group, reversely charging protection device and sensing system are connected to switch board.
Further, super capacitance cell module includes capacitor batteries monomer and control board, and capacitor batteries monomer leads to
The mode for crossing series winding and/or parallel connection is connected and is connected with control board, and the positive pole of capacitor batteries monomer is connected to form total positive pole
Terminal, the negative pole of capacitor batteries monomer are connected to form total negative terminal.
Further, sensing system includes current sensor and voltage sensor, for detect aviation dc source with
Output current and voltage after super capacitance cell modules in parallel.
Further, reversely charging protection device is diode, the one-way flow for control electric current.
Further, aviation dc source includes rectifier and transformer, and rectifier is used to alternating current being changed into direct current
Electricity, transformer are used to adjust output voltage values.
Supply vehicle described in the utility model has the beneficial effect that：
1st, power output can be doubled the above by supply vehicle described in the utility model, disclosure satisfy that various aircrafts start
Demand.
2nd, supply vehicle described in the utility model possesses generalization, miniaturization and intellectuality, meets that all helicopter types open
Requirement when dynamic to input power, while ensured the demand of long-term combat duty.
3rd, supply vehicle described in the utility model can control the exporting of power supply, whole monitoring supply voltage and electric current, ensure
Safety when aircraft starts.
4. supply vehicle output performance described in the utility model is good, simple in construction, installation operability is good, applied widely,
It disclosure satisfy that the power supply safeguard work of all kinds of aircrafts.
Brief description of the drawings
Fig. 1 is the composition structural representation of supply vehicle described in the utility model.
Shown in figure：
1- taking force power generation systems；2- power distribution cabinets；3- switch boards；4- aviation dc sources；5- chargers；6- super capacitors electricity
Pond module；7- reversely charging protection devices；8- sensing systems；9- is loaded.
Embodiment
With reference to Figure of description, the technical scheme of supply vehicle described in the utility model is clearly and completely retouched
State.
As shown in figure 1, the supply vehicle includes taking force power generation system 1, power distribution cabinet 2, switch board 3, aviation dc source 4,
Taking force power generation system 1, power distribution cabinet 2 and aviation dc source 4 are sequentially connected, and power distribution cabinet 2 and aviation dc source 4 are connected to
Switch board 3, the charger 5, super capacitance cell module 6 and reversely charging that the supply vehicle also includes being sequentially connected with power distribution cabinet 2 are protected
Protection unit 7, the sensing system 8 contacted with aviation dc source 4, reversely charging protection device 7 are connected to the defeated of aviation dc source 4
Go out end, charger 5, super capacitance cell module 6, reversely charging protection device 7 and sensing system 8 are connected to switch board 3, pass
Sensor system 8 is connected to load 9.
Taking force power generation system 1 be by the power takeoff on vehicle chassis gear-box side power taking mouth from vehicle chassis
Power is obtained, the power of engine is delivered to by the generator on vehicle chassis by cross power transmission shaft, passes through control
The rotating speed of engine, so that generator obtains stable high quality power supply.
Further, super capacitance cell module 6 includes capacitor batteries monomer and control board (not shown), electric capacity
Battery cell is connected by way of series winding and/or parallel connection and is connected with control board, and the positive pole of capacitor batteries monomer is connected
Total positive terminal is formed, the negative pole of capacitor batteries monomer is connected to form total negative terminal.
Further, sensing system 8 includes current sensor and voltage sensor, for detecting aviation dc source 4
Output voltage and electric current after in parallel with super capacitance cell module 6, and the data collected are sent to switch board 3, ensure
The safety of aircraft.
Further, reversely charging protection device 7 is diode, for the one-way flow of control electric current, prevents aviation direct current
Reverse charge is carried out to super capacitance cell module when source 4 is in parallel with super capacitance cell module 6, when aircraft starts inside increase
Power is consumed, causes the overall output deficiency of supply vehicle.
Further, aviation dc source 4 includes rectifier and transformer, and rectifier is used to alternating current being changed into direct current
Electricity, transformer are used to adjust output voltage values.
The process for using of supply vehicle described in the utility model is as follows：
By the control of engine speed to taking force power generation system 1, so as to obtain stable high quality power supply, pass through switch board
3 control, power input power distribution cabinet 2 is simultaneously sent to aviation dc source 4 and charger 5 respectively, when starting aircraft, switch board 3
Control aviation dc source 4 is output to simultaneously with super capacitance cell module 6 by reversely charging protection device 7 and sensing system 8
Load 9, because the internal resistance of super capacitance cell module 6 is far smaller than the internal resistance of aviation dc source 4, therefore started in aircraft
Cheng Zhong, super capacitance cell module 6 can provide momentary high power compensation, after momentary high power output procedure terminates, control
Cabinet 3 controls charger 5 to be charged to super capacitance cell module 6, while helicopter typically has 2 to 3 engines, each engine
Start at intervals of 30S, within this interval time, charger 5 is fully charged by super capacitance cell module 6, you can continue to start separately
One engine, and so on circulation are charged.
The utility model is not limited to above-mentioned embodiment, in the case of without departing substantially from the utility model in essence content, this
Any deformation, improvement, the replacement that art personnel are contemplated that each fall within the scope of protection of the utility model.
Claims (5)
1. a kind of aircraft energizer car, including taking force power generation system (1), power distribution cabinet (2), switch board (3), aviation dc source
(4), taking force power generation system (1), power distribution cabinet (2) and aviation dc source (4) are sequentially connected, power distribution cabinet (2) and aviation direct current
Source (4) is connected to switch board (3), it is characterised in that the supply vehicle also includes the charging being sequentially connected with power distribution cabinet (2)
Machine (5), super capacitance cell module (6) and reversely charging protection device (7), the sensing system with aviation dc source (4) series winding
(8), reversely charging protection device (7) is connected to the output end of aviation dc source (4), charger (5), super capacitance cell module
(6), reversely charging protection device (7) and sensing system (8) are connected to switch board (3).
2. supply vehicle according to claim 1, it is characterised in that super capacitance cell module (6) includes capacitor batteries list
Body and control board, capacitor batteries monomer are connected by way of series winding and/or parallel connection and are connected with control board, electric capacity
The positive pole of battery cell is connected to form total positive terminal, and the negative pole of capacitor batteries monomer is connected to form total negative terminal.
3. supply vehicle according to claim 1, it is characterised in that sensing system (8) includes current sensor and voltage
Sensor, for detect aviation dc source (4) it is in parallel with super capacitance cell module (6) after output voltage and electric current.
4. supply vehicle according to claim 1, it is characterised in that reversely charging protection device (7) is diode, for controlling electricity
The one-way flow of stream.
5. supply vehicle according to claim 1, it is characterised in that aviation dc source (4) includes rectifier and transformer,
Rectifier is used to alternating current being changed into direct current, and transformer is used to adjust output voltage values.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721203318.5U CN207166136U (en) | 2017-09-20 | 2017-09-20 | A kind of aircraft energizer car |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721203318.5U CN207166136U (en) | 2017-09-20 | 2017-09-20 | A kind of aircraft energizer car |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207166136U true CN207166136U (en) | 2018-03-30 |
Family
ID=61722605
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721203318.5U Active CN207166136U (en) | 2017-09-20 | 2017-09-20 | A kind of aircraft energizer car |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207166136U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107508276A (en) * | 2017-09-20 | 2017-12-22 | 北京安达维尔测控技术有限公司 | A kind of aircraft energizer car |
-
2017
- 2017-09-20 CN CN201721203318.5U patent/CN207166136U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107508276A (en) * | 2017-09-20 | 2017-12-22 | 北京安达维尔测控技术有限公司 | A kind of aircraft energizer car |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 101300, Beijing, Shunyi District Renhe Town Du Yang North Street, No. 1, 19, 4 Patentee after: Beijing andaville Intelligent Technology Co.,Ltd. Address before: 101300, Beijing, Shunyi District Renhe Town Du Yang North Street, No. 1, 19, 4 Patentee before: BEIJING ANDAWELL MEASUREMENT & CONTROL TECHNOLOGY Co.,Ltd. |
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| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 101300 4th floor, building 1, No. 19, duyang North Street, Renhe Town, Shunyi District, Beijing Patentee after: Beijing Tianpu Situo Intelligent Technology Co.,Ltd. Address before: 101300 4th floor, building 1, No. 19, duyang North Street, Renhe Town, Shunyi District, Beijing Patentee before: Beijing andaville Intelligent Technology Co.,Ltd. |