CN109941442A - A kind of electric pulse heat-mechanical aircraft deicing method and system combined - Google Patents
A kind of electric pulse heat-mechanical aircraft deicing method and system combined Download PDFInfo
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- CN109941442A CN109941442A CN201910179457.6A CN201910179457A CN109941442A CN 109941442 A CN109941442 A CN 109941442A CN 201910179457 A CN201910179457 A CN 201910179457A CN 109941442 A CN109941442 A CN 109941442A
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Abstract
The present invention provides a kind of electric pulse heat-mechanical aircraft deicing method and system combined, comprising: S1: monitoring aircraft ice condition；When detecting icing, charged according to ice condition to storage capacitor；S2: determine whether storage capacitor charging reaches predetermined voltage threshold；Reach predetermined voltage threshold when storage capacitor charges, opens power switch, form discharge pulse current on pulsed coil；Electromagnetic eddy field is formed on aircraft metal skin, is generated Transient Electromagnetic power, is led to the metal skin fast vibration；S3: receiving electric impulse signal, and induction coil generates the alternating magnetic field of cutting heater, and heater heats the aircraft metal skin.The aircraft metal skin mechanical shock that electric pulse generates is used for deicing；Electric pulse induces alternating magnetic field in induction coil, is heated by heater to aircraft metal skin, induction heating assists mechanical vibrating deicing, while playing the purpose of aircraft anti-icing.
Description
Technical field
The invention belongs to aircraft deicing field more particularly to a kind of electric pulse heat-mechanical aircraft deicing methods combined
And system.
Background technique
The phenomenon that aircraft icing refers to aircraft the water-setting on its surface forms water under specific meteorological condition, aircraft icing phenomenon
It can all occur in flight or holding process, be a kind of very universal phenomenon.Aircraft icing can cause aircraft safety very big
Threat.According to statistics, aircraft awing causes the probability of air crash to be more than 15% because of ice formation issues.And from 21 generation
Since discipline, because the caused aircraft accident of aircraft icing is in rising trend.According to statistics, aircraft icing accident rises in aircraft
Fly, respectively account for 1/3 in flight and descent.And the icing accident 27% in take-off process belongs on airframe and has covered
Have ice and snow frost and cause.Icing accident in flight course may be made because In-Flight Performance is reduced because of icing
Highly automated decline is obtained, and causes aircraft stall, if encountering the barriers such as high mountain on the way just will increase the probability of air crash.Landed
Icing accident in journey increases stalling speed, and aircraft is in the runway of icing mainly because icing reduces engine power
Also landing accident was easy to happen when upper.
Electro-impulse deicing system is with a wide range of applications in aircraft deicing.But current electro-impulse deicing system
Although the significant effect in terms of deicing, has many advantages, such as that deicing is efficient, stable and energy saving, more owed in terms of aircraft anti-icing
It lacks.
Summary of the invention
Electric pulse in the prior art aiming at the problem that being more short of in terms of aircraft anti-icing, the present invention provides a kind of electric pulse
De-icing method and system, the method and system are based on electric pulse heat-machinery and combine, and achieve the purpose that ice-removing and ice-preventing.
To reach this purpose, electric pulse heat-mechanical de-icing method combined in the present invention, comprising:
S1: monitoring aircraft ice condition；When detecting icing, charged according to ice condition to storage capacitor；
S2: determine whether storage capacitor charging reaches predetermined voltage threshold；When storage capacitor charging reaches predeterminated voltage threshold
Value opens power switch, forms discharge pulse current on pulsed coil；Electromagnetic eddy field is formed on aircraft metal skin, is generated
Transient Electromagnetic power leads to the metal skin fast vibration；
S3: receiving electric impulse signal, and induction coil generates the alternating magnetic field of cutting heater, and heater is to the aircraft gold
Belong to covering heating.
Preferably, in the step S2, after storage capacitor completes primary electric discharge；Aircraft ice condition is monitored, when detecting
When icing, charge again to storage capacitor.
Preferably, before storage capacitor charging, whether detection circuit overloads；Overload then opens overload protection arrangement, and circuit is just
Chang Ze charges to storage capacitor.
A kind of electric pulse heat-mechanical deicing system combined, comprising: control module, icing detector, charging module,
Discharge module, induction heating module；
Icing detector, charging module, discharge module, induction heating module are separately connected control module；
Icing detector monitors aircraft ice condition；When detecting icing, control module is according to ice condition to charging
Module charging；
Control module determines whether storage capacitor charging reaches predetermined voltage threshold；When storage capacitor charging reaches default electricity
Threshold value is pressed, discharge module is opened, forms discharge pulse current on discharge module；Electromagnetic eddy field is formed on aircraft metal skin,
Transient Electromagnetic power is generated, the metal skin fast vibration is caused；
Control module controls induction heating module simultaneously and receives electric impulse signal, and induction heating module generates cutting heater
Alternating magnetic field, heater to aircraft metal skin heat.
Preferably, after charging module completes primary electric discharge, icing detector monitors aircraft ice condition, freezes when detecting
When, control module control charging module charges again.
Preferably, before charging module charging, whether control module detection circuit overloads；Overload then opens overload protection dress
It sets, circuit normally then charges to charging module.
Preferably, charging module includes: storage capacitor, charge switch, voltage regulator；
Storage capacitor is connected by charge switch, voltage regulator and charge power supply, control module respectively with control module
Connection；Control module controls the start and stop of storage capacitor charging by charge switch, controls storage capacitor by voltage regulator
Charging voltage.
Preferably, induction heating module includes: electric impulse signal receiver, induction coil, heater；
Electric impulse signal receiver is connect with induction coil, and induction coil generates the alternating magnetic field of cutting heater, heating
Device heats the aircraft metal skin.
The beneficial effects of the present invention are,
The present invention is based on mechanical combine of electric pulse heat-to achieve the purpose that aircraft deicing is anti-icing, the aircraft that electric pulse generates
Metal skin mechanical shock is used for deicing；Electric pulse induces alternating magnetic field in induction coil, by heater to aircraft gold
Belong to covering heating, induction heating assists mechanical vibrating deicing, while playing the purpose of aircraft anti-icing.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, for those of ordinary skill in the art
Speech, without creative efforts, is also possible to obtain other drawings based on these drawings.
Fig. 1 is principle schematic diagram of the present invention.
Specific embodiment
Technical solution in order to enable those skilled in the art to better understand the present invention, below in conjunction with of the invention real
The attached drawing in example is applied, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described implementation
Example is only a part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, this field is common
Technical staff's every other embodiment obtained without making creative work, all should belong to protection of the present invention
Range.
The present embodiment achievees the purpose that aircraft deicing is anti-icing based on mechanical combine of electric pulse heat-, and what electric pulse generated flies
Machine metal skin mechanical shock is used for deicing；Electric pulse induces alternating magnetic field in induction coil, by heater to aircraft
Metal skin heating, induction heating assists mechanical vibrating deicing, while playing the purpose of aircraft anti-icing.Electric pulse heat-mechanical phase
In conjunction with de-icing method specifically include:
S1: monitoring aircraft ice condition；When detecting icing, charged according to ice condition to storage capacitor；
S2: determine whether storage capacitor charging reaches predetermined voltage threshold；When storage capacitor charging reaches predeterminated voltage threshold
Value opens power switch, forms discharge pulse current on pulsed coil；Electromagnetic eddy field is formed on aircraft metal skin, is generated
Transient Electromagnetic power leads to the metal skin fast vibration；
S3: electric impulse signal receiver receives electric impulse signal, and induction coil generates the alternating magnetic field of cutting heater, adds
Hot device heats the aircraft metal skin.
Wherein, after storage capacitor completes primary electric discharge in step S2；Aircraft ice condition is monitored, when detecting icing,
It charges again to storage capacitor.
Before storage capacitor charging, whether detection circuit overloads；Overload then opens overload protection arrangement, and circuit is normally then to storage
Energy capacitor charges.
It is specifically included based on electric pulse heat-mechanical deicing system combined: control module, icing detector, charging mould
Block, discharge module, induction heating module；
Icing detector, charging module, discharge module, induction heating module are separately connected control module；
Icing detector monitors aircraft ice condition；When detecting icing, control module is according to ice condition to charging
Module charging；
Control module determines whether storage capacitor charging reaches predetermined voltage threshold；When storage capacitor charging reaches default electricity
Threshold value is pressed, discharge module is opened, forms discharge pulse current on discharge module；Electromagnetic eddy field is formed on aircraft metal skin,
Transient Electromagnetic power is generated, the metal skin fast vibration is caused；
Control module controls induction heating module simultaneously and receives electric impulse signal, and induction heating module generates cutting heater
Alternating magnetic field, heater to aircraft metal skin heat.
After charging module completes primary electric discharge, icing detector monitors aircraft ice condition, when detecting icing, control
Module control charging module charges again.
Before charging module charging, whether control module detection circuit overloads；Overload then opens overload protection arrangement, and circuit is just
Chang Ze charges to charging module.
Charging module includes: storage capacitor, charge switch, voltage regulator；
Storage capacitor is connected by charge switch, voltage regulator and charge power supply, control module respectively with control module
Connection；Control module controls the start and stop of storage capacitor charging by charge switch, controls storage capacitor by voltage regulator
Charging voltage.
Induction heating module includes: electric impulse signal receiver, induction coil, heater；
Electric impulse signal receiver is connect with induction coil, and induction coil generates the alternating magnetic field of cutting heater, heating
Device heats the aircraft metal skin.
Although by reference to attached drawing and combining the mode of preferred embodiment to the present invention have been described in detail, the present invention
It is not limited to this.Without departing from the spirit and substance of the premise in the present invention, those of ordinary skill in the art can be to the present invention
Embodiment carry out various equivalent modifications or substitutions, and these modifications or substitutions all should in covering scope of the invention/appoint
What those familiar with the art in the technical scope disclosed by the present invention, can easily think of the change or the replacement, answer
It is included within the scope of the present invention.Therefore, protection scope of the present invention is answered described is with scope of protection of the claims
It is quasi-.
Claims (8)
1. a kind of electric pulse heat-mechanical aircraft deicing method combined characterized by comprising
S1: monitoring aircraft ice condition；When detecting icing, charged according to ice condition to storage capacitor；
S2: determine whether storage capacitor charging reaches predetermined voltage threshold；Reach predetermined voltage threshold when storage capacitor charges, beats
Power switch is opened, forms discharge pulse current on pulsed coil；Electromagnetic eddy field is formed on aircraft metal skin, generates transient state electricity
Magnetic force leads to the metal skin fast vibration；
S3: electric impulse signal receiver receives electric impulse signal, and induction coil generates the alternating magnetic field of cutting heater, heater
The aircraft metal skin is heated.
2. the electric pulse heat according to claim 1-mechanical aircraft deicing method combined, which is characterized in that the step
In rapid S2,
After storage capacitor completes primary electric discharge；Monitoring aircraft ice condition again fills storage capacitor when detecting icing
Electricity.
3. the electric pulse heat according to claim 1 or 2-mechanical aircraft deicing method combined, which is characterized in that
Before storage capacitor charging, whether detection circuit overloads；Overload then opens overload protection arrangement, and circuit is normally then to energy storage electricity
Appearance charges.
4. a kind of electric pulse heat-mechanical aircraft de-icing systems combined characterized by comprising control module, icing detection
Device, charging module, discharge module, induction heating module；
Icing detector, charging module, discharge module, induction heating module are separately connected control module；
Icing detector monitors aircraft ice condition；When detecting icing, control module is according to ice condition to charging module
Charging；
Control module determines whether storage capacitor charging reaches predetermined voltage threshold；When storage capacitor charging reaches predeterminated voltage threshold
Value opens discharge module, forms discharge pulse current on discharge module；Electromagnetic eddy field is formed on aircraft metal skin, is generated
Transient Electromagnetic power leads to the metal skin fast vibration；
Control module controls induction heating module simultaneously and receives electric impulse signal, and induction heating module generates the friendship of cutting heater
Varying magnetic field, heater heat aircraft metal skin.
5. the electric pulse heat according to claim 4-mechanical aircraft de-icing systems combined, which is characterized in that
After charging module completes primary electric discharge, icing detector monitors aircraft ice condition, when detecting icing, control module
Control charging module charges again.
6. the electric pulse heat according to claim 4 or 5-mechanical aircraft de-icing systems combined, which is characterized in that
Before charging module charging, whether control module detection circuit overloads；Overload then opens overload protection arrangement, and circuit is normally then
It charges to charging module.
7. the electric pulse heat according to claim 4-mechanical aircraft de-icing systems combined, which is characterized in that
Charging module includes: storage capacitor, charge switch, voltage regulator；
Storage capacitor is connected by charge switch, voltage regulator and charge power supply, and control module is connect with control module respectively；
Control module controls the start and stop of storage capacitor charging by charge switch, and the charging electricity of storage capacitor is controlled by voltage regulator
Pressure.
8. the electric pulse heat according to claim 4-mechanical aircraft de-icing systems combined, which is characterized in that
Induction heating module includes: electric impulse signal receiver, induction coil, heater；
Electric impulse signal receiver is connect with induction coil, and induction coil generates the alternating magnetic field of cutting heater, heater pair
The aircraft metal skin heating.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910179457.6A CN109941442A (en) | 2019-03-11 | 2019-03-11 | A kind of electric pulse heat-mechanical aircraft deicing method and system combined |
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| CN201910179457.6A CN109941442A (en) | 2019-03-11 | 2019-03-11 | A kind of electric pulse heat-mechanical aircraft deicing method and system combined |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110606208A (en) * | 2019-09-26 | 2019-12-24 | 山东大学 | Giant magnetostrictive material aircraft wing ice preventing and removing device and control system and application thereof |
| CN113064223A (en) * | 2021-04-29 | 2021-07-02 | 重庆电力设计院有限责任公司 | Ice collector capable of automatically removing ice |
| CN114001670A (en) * | 2021-11-17 | 2022-02-01 | 上海工程技术大学 | Infrared thermal wave ice shape detection method based on electric pulse deicing |
| CN116280213A (en) * | 2023-05-18 | 2023-06-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing thermal coupling deicing device and method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110606208A (en) * | 2019-09-26 | 2019-12-24 | 山东大学 | Giant magnetostrictive material aircraft wing ice preventing and removing device and control system and application thereof |
| CN110606208B (en) * | 2019-09-26 | 2020-12-18 | 山东大学 | Giant magnetostrictive material aircraft wing ice preventing and removing device and control system and application thereof |
| CN113064223A (en) * | 2021-04-29 | 2021-07-02 | 重庆电力设计院有限责任公司 | Ice collector capable of automatically removing ice |
| CN114001670A (en) * | 2021-11-17 | 2022-02-01 | 上海工程技术大学 | Infrared thermal wave ice shape detection method based on electric pulse deicing |
| CN114001670B (en) * | 2021-11-17 | 2023-06-02 | 上海工程技术大学 | Infrared thermal wave ice shape detection method based on electric pulse deicing |
| CN116280213A (en) * | 2023-05-18 | 2023-06-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing thermal coupling deicing device and method |
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Application publication date: 20190628 |
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