CN206283278U - A kind of airborne startup power supply of aircraft engine - Google Patents
A kind of airborne startup power supply of aircraft engine Download PDFInfo
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- CN206283278U CN206283278U CN201621321888.XU CN201621321888U CN206283278U CN 206283278 U CN206283278 U CN 206283278U CN 201621321888 U CN201621321888 U CN 201621321888U CN 206283278 U CN206283278 U CN 206283278U
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Abstract
The utility model is related to a kind of airborne startup power supply of aircraft engine, including super-capacitor module, charging module, relay, charging, control interface and electric discharge interface；Charge, 28V direct currents are connected to charging module input by control interface through the normally-closed contact of relay, and the control level of flight-control computer is connected into the coil of relay；When flight-control computer is when controlling level for 28V, super-capacitor module provides electric energy for starting-motor of engine；When flight-control computer is when controlling level for 0V, the charged module of super-capacitor module is charged by airborne 28V dc bus.The utility model startup power supply has that power density is high, the charging interval is short, has extended cycle life, good environmental adaptability, non-maintaining, small volume, lightweight, excellent performance, good environmental adaptability, long lifespan, low cost and other advantages, can be used instead of chemical cell as the airborne startup power supply of unmanned vehicle engine.
Description
Technical field
The utility model is related to a kind of airborne startup power supply of aircraft engine, particularly a kind of to be used suitable for unmanned plane
Light airborne startup power supply, belongs to Power Management Design field.
Background technology
Electrically activating for unmanned vehicle engine is typically realized by aircraft exterior startup power supply or airborne startup power supply.Outside starts
Power supply is in the unmanned aerial vehicle preparatory stage for engine start provides electric energy；Airborne startup power supply prepares and flies in unmanned aerial vehicle
Row order section provides electric energy for engine start.
Most of unmanned planes start engine using outside startup power supply.Start engine need ground crew to aircraft and
Ground installation is operated, and operating process has potential safety hazard.Meanwhile, the noise of engine operating generation, waste gas are unfavorable for ground
The occupational health of diligent personnel.Flight operation personnel are needed to enter with ground crew additionally, starting engine using outside startup power supply
Row is linked up and interaction, is unfavorable for that the quick of UAS sets out.
Part unmanned plane and manned aircraft start engine using airborne startup power supply.Airborne startup power supply is generally lead
The chemical cells such as sour battery, ickel-cadmium cell, lithium ion battery.Discharge capability under the adverse circumstances such as chemical cell low temperature environment is general
All over poor, make activation system cannot normally high-power operating, this is that Aircraft Air startup is unacceptable.Meanwhile, chemical cell
Long-term heavy-current discharge can make its degradation, the lost of life, and the chemical cell need periodic maintenance and replacing, and this improves and is
System operation and maintenance cost.Additionally, when chemical cell is used as startup power supply, its power density is relatively low, installation weight is larger.
At present, the startup power supply based on ultracapacitor is used for the ground startup of aircraft engine, ultracapacitor
Small volume, lightweight, strong environmental adaptability, long lifespan, low cost, are suitable as startup power supply.But the technology is only limitted to ground
Face uses, and is not used for aircraft airborne equipment.How to realize supercapacitor applications in the airborne startup electricity of unmanned vehicle engine
Source, is this area technical problem urgently to be resolved hurrily.
Utility model content
The purpose of this utility model is the above-mentioned deficiency for overcoming prior art, there is provided a kind of airborne startup of aircraft engine
Power supply, for electrically activating for unmanned vehicle engine, while being also applied for manned aircraft.
Above-mentioned purpose of the present utility model is achieved by following technical solution：
There is provided a kind of aircraft engine airborne startup power supply, including super-capacitor module, charging module, relay, charge,
Control interface and electric discharge interface；
Charge, control interface connects airborne 28V dc bus, and 28V direct currents are connected through the normally-closed contact of relay
To charging module input；Charge, control interface connection flight-control computer, and by the control level of flight-control computer
It is connected to the coil of relay；
Super-capacitor module is connected to electric discharge interface through the normally opened contact of relay；
Electric discharge interface is connected to starting-motor of engine；
When flight-control computer is when controlling level for 28V, relay normally open contact closure, normally-closed contact disconnects, and surpasses
Level capacitance module is through the interface that discharges for starting-motor of engine provides electric energy；When the level that controls of flight-control computer is 0V
When, relay normally open contact disconnects, and normally-closed contact closure, the charged module of super-capacitor module passes through airborne 28V dc bus
Charged.
Preferably, the charging module includes DC/DC modules, filtration module and detection control module；DC/DC modules pass through
Charge, control interface receives 28V direct currents, exported to filtration module after adjustment voltage；Filtration module is delivered to after being filtered
Super-capacitor module；Detection control module detects the output current of DC/DC modules, when the output current of DC/DC modules is more than 2A
When, reduce the output voltage of DC/DC modules.
Preferably, the super-capacitor module operating voltage range is 11V~15V, is 1500F's by 6 rated capacities
Ultracapacitor is composed in series.
The utility model beneficial effect compared with prior art is：
(1) the utility model startup power supply is adopted compared with the airborne startup power supply of the unmanned vehicle engine based on chemical cell
With ultracapacitor as startup power supply energy storage units, with power density it is high, the charging interval is short, have extended cycle life,
Good environmental adaptability, non-maintaining, small volume, lightweight, excellent performance, good environmental adaptability, long lifespan, low cost and other advantages,
Can be used instead of chemical cell as the airborne startup power supply of unmanned vehicle engine, it is also possible to effectively solve ground startup power supply
Inconvenience in use.
(2) the utility model startup power supply is compared with the unmanned vehicle engine ground startup power supply based on ultracapacitor,
The utility model is unmanned aerial vehicle onboard equipment, can realize electrically activating for engine, automaticity by remote control and stored program control system
Height, quick beneficial to UAS sets out.Engine start is operated without ground crew, non-hazardous occupational health hidden danger, peace
Quan Xinggao.
(3) startup power supply is also applied for manned aircraft, and the startup power supply directly as manned aircraft is used, should
Wide with scope, adaptability is good.
Brief description of the drawings
Fig. 1 is startup power supply principle schematic of the present utility model；
Fig. 2 is startup power supply charging module principle schematic of the present utility model.
Specific embodiment
The utility model is described in further detail with specific embodiment below in conjunction with the accompanying drawings：
As shown in figure 1, the startup power supply that the utility model is introduced is by super-capacitor module, charging module, relay fills
Electricity, control interface and electric discharge interface composition.The normally-closed contact of relay is connected in the incoming line of charging module, and control is charged
The opening and closing of module；The normally opened contact of relay is connected in the discharge line of super-capacitor module, controls super capacitor
The electric discharge of module；Relay is by charging, the control instruction of control interface reception flight-control computer, controls contact break-make；
Charge, control interface is used to connect airborne 28V dc bus and flight-control computer；Electric discharge interface is connected to engine start
Motor.
As shown in figure 1, startup power supply inside sets a relay, the relay is calculated by the flight control on unmanned plane
Machine is controlled, and is responsible for performing the switching action of charging and discharging loop.The relay has auxiliary contact, can realize charging and putting
The mutual exclusion of electric two states.
After flight-control computer sends 28V control signals to startup power supply, the normally opened master of startup power supply internal relay
The closing of contact, startup power supply provides electric energy for engine start；Meanwhile, the normally closed auxiliary contact of relay disconnects, startup power supply
Interior charging module stops charging super-capacitor module.
After the control signal that flight-control computer is sent to startup power supply disappears, startup power supply internal relay it is normally opened
Main contacts disconnects, and startup power supply stops providing electric energy for engine start；Meanwhile, the normally closed auxiliary contact closure of relay is opened
Charging module in dynamic power supply starts to charge super-capacitor module, the electric energy of supplement super-capacitor module loss.
(1) super-capacitor module
The rated power of certain unmanned vehicle engine starter is 0.6kW/12V, and single started the time for 5 seconds.Super capacitor
The capacity of module should be able to meet three energy requirements of startup of engine under -40 DEG C~+60 DEG C environmental conditions.Engine
Energy needed for starting for three times is 9000J.
The utility model super-capacitor module is by 6 rated capacities for the ultracapacitor of 1500F is composed in series, and work is electric
Pressure scope is 11V~15V, meets and starts voltage requirements.Capacity of the ultracapacitor under high temperature and low temperature environment and internal resistance with
Normal temperature value is variant.Energy of the super-capacitor module under normal temperature, -40 DEG C and+60 DEG C of environmental conditions be respectively 12585J,
11635J and 13170J, can meet three energy requirements of startup of engine under condition of different temperatures.
(2) charging module
As shown in figure 1, airborne startup power supply has been internally integrated charging module, without being equipped with external charger.Charging module
It is airborne 28V direct current supplys, super-capacitor module is charged with constant current-constant voltage mode.Charging module designs maximum charge
Electric current is 2A, is ensureing that the charging interval on the premise of tolerance interval, alleviates the weight of charging module.
The structure of charging module receives airborne 28V power inputs as shown in Fig. 2 passing through charging, control interface, by DC/
DC modules adjust output voltage, realize the constant-current charge of 2A under the control of detection control module, and filtration module is by DC/DC modules
Output filtering after be delivered to super-capacitor module.Detection control module adjusts DC/ by detecting the output current of DC/DC modules
The output voltage of DC modules, when the output current of DC/DC modules is more than 2A, reduces output voltage.
The utility model realizes ultracapacitor in unmanned vehicle engine airstart side by hardware design and optimization
The application in face, makes UAS possess the function of remote control and program control startup engine.In actual applications, the startup power supply
Function and performance meet design requirement, matched well with UAS.
The above, the only optimal specific embodiment of utility model, but protection domain of the present utility model not office
It is limited to this, any one skilled in the art can readily occur in the technical scope that the utility model is disclosed
Change or replacement, should all cover within protection domain of the present utility model.
The content not being described in detail in the utility model specification belongs to the known technology of professional and technical personnel in the field.
Claims (3)
1. the airborne startup power supply of a kind of aircraft engine, it is characterised in that including super-capacitor module, charging module, relay,
Charging, control interface and electric discharge interface；
Charge, control interface connects airborne 28V dc bus, and 28V direct currents are connected to through the normally-closed contact of relay fill
Electric module input；Charge, control interface connects flight-control computer, and the control level of flight-control computer is connected
To the coil of relay；
Super-capacitor module is connected to electric discharge interface through the normally opened contact of relay；
Electric discharge interface is connected to starting-motor of engine；
When flight-control computer is when controlling level for 28V, relay normally open contact closure, normally-closed contact disconnects, super electricity
Molar block is through the interface that discharges for starting-motor of engine provides electric energy；When flight-control computer is when controlling level for 0V, after
Electrical equipment normally opened contact is disconnected, and normally-closed contact closure, the charged module of super-capacitor module is filled by airborne 28V dc bus
Electricity.
2. the airborne startup power supply of aircraft engine as claimed in claim 1, it is characterised in that the charging module includes DC/
DC modules, filtration module and detection control module；DC/DC modules are by charging, control interface receives 28V direct currents, adjustment electricity
Exported after pressure to filtration module；Filtration module is delivered to super-capacitor module after being filtered；Detection control module detection DC/DC
The output current of module, when the output current of DC/DC modules is more than 2A, reduces the output voltage of DC/DC modules.
3. the airborne startup power supply of aircraft engine as claimed in claim 1, it is characterised in that the super-capacitor module work
Voltage range is 11V~15V, by 6 rated capacities for the ultracapacitor of 1500F is composed in series.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621321888.XU CN206283278U (en) | 2016-12-02 | 2016-12-02 | A kind of airborne startup power supply of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621321888.XU CN206283278U (en) | 2016-12-02 | 2016-12-02 | A kind of airborne startup power supply of aircraft engine |
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| CN206283278U true CN206283278U (en) | 2017-06-27 |
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ID=59075318
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| Application Number | Title | Priority Date | Filing Date |
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| CN201621321888.XU Active CN206283278U (en) | 2016-12-02 | 2016-12-02 | A kind of airborne startup power supply of aircraft engine |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20190003398A1 (en) * | 2017-06-28 | 2019-01-03 | General Electric Company | Systems and methods for starting a turbine engine |
| CN109556588A (en) * | 2018-11-28 | 2019-04-02 | 中国人民解放军火箭军工程大学 | A kind of sensitive part device of gyro and detection method of long-life independently-powered formula |
| CN111380078A (en) * | 2020-03-16 | 2020-07-07 | 大连理工大学 | Electric heating type afterburner and working method |
| CN112277710A (en) * | 2020-11-06 | 2021-01-29 | 宇能电气有限公司 | Helicopter field emergency starting system |
-
2016
- 2016-12-02 CN CN201621321888.XU patent/CN206283278U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20190003398A1 (en) * | 2017-06-28 | 2019-01-03 | General Electric Company | Systems and methods for starting a turbine engine |
| US10823078B2 (en) * | 2017-06-28 | 2020-11-03 | General Electric Company | Systems and methods for starting a turbine engine |
| CN109556588A (en) * | 2018-11-28 | 2019-04-02 | 中国人民解放军火箭军工程大学 | A kind of sensitive part device of gyro and detection method of long-life independently-powered formula |
| CN111380078A (en) * | 2020-03-16 | 2020-07-07 | 大连理工大学 | Electric heating type afterburner and working method |
| CN111380078B (en) * | 2020-03-16 | 2021-04-20 | 大连理工大学 | Electric heating type afterburner and working method |
| CN112277710A (en) * | 2020-11-06 | 2021-01-29 | 宇能电气有限公司 | Helicopter field emergency starting system |
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