CN101695959A - Ice preventing and removing device for helicopter rotors - Google Patents
Ice preventing and removing device for helicopter rotors Download PDFInfo
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- CN101695959A CN101695959A CN200910236462A CN200910236462A CN101695959A CN 101695959 A CN101695959 A CN 101695959A CN 200910236462 A CN200910236462 A CN 200910236462A CN 200910236462 A CN200910236462 A CN 200910236462A CN 101695959 A CN101695959 A CN 101695959A
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- deicing
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- empennage
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Abstract
The invention discloses an ice preventing and removing device for helicopter rotors. The device comprises an icing detector, an icing speed solver, an atmospheric temperature sensor, an ice preventing and removing control panel, a digital type ice preventing and removing controller, a main rotor distributor, an empennage distributor, a main rotor ice removing component, an empennage ice removing component, an No.1 AC power supply and an No.2 AC power supply, wherein the icing detector and the icing speed solver transfer liquid water content signals and atmospheric temperature signals to the digital type ice preventing and removing controller respectively, the digital type ice preventing and removing controller carries out computation according to the ice preventing and removing control panel and the input signals to output the control signals of the main rotor distributor and the control signals of the empennage distributor, and the main rotor distributor and the empennage distributor control the main rotor ice removing component and the empennage ice removing component to remove ice. By the ice preventing and removing device, the helicopter can safely fly under server weather conditions, and the safety accidents due to the icing of the rotors and the bad influence of pneumatic configuration caused by too low ambient temperature or too high water content are avoided.
Description
Technical field
The present invention relates to a kind of ice preventing and removing device for helicopter rotors, belong to Helicopter Safety guard technology field.
Background technology
The flying height many places of helicopter in this altitude range, run into inclement weathers such as sleet frost through regular meeting below 6000m, the aqueous water content in the atmosphere is also higher, and these all can make helicopter meet with the danger of freezing in mission period.The rotor of helicopter is a lift member, also bearing simultaneously radical functions such as manipulation, blade surface freezes will directly threaten the safety of helicopter, must take safeguard procedures to it, see: Fu Jianping. the anti-icing technical study of helicopter. flight mechanics, 2005 and Wang Zongyan. the anti-ice problem of helicopter. helicopter technology, 2001.
In order to prevent icing the having a strong impact on of bringing of rotor blade, two measures are arranged: the one, adopt ice control to make super-cooling waterdrop on rotor blade, not congeal into ice; The one, adopt the measure of deicing, in ice detachment, allow knot certain thickness icing, deicing then.The anti-deicing method of helicopter rotor blade mainly contains pneumatic de-icing, hot gas deicing, microwave deicing, liquid is anti-icing and de-icing method such as electro-thermal deicing.Electro-thermal deicing is to arrange electro heat deicing element in the rotor blade leading edge, see Ai Jianbo, Deng Jinghui, Liu Dajing. Deicing Structure Design of Helicopter Rotor Blade. the helicopter technology, 2005, electro-thermal deicing adopts periodic energising type of heating to remove the icing of rotor blade leading edge, this method maturation, simple in structure, period of service is unrestricted.
People such as Ai Jianbo have introduced structure, material and the arrangement on rotor thereof of helicopter deicing heating component in its paper, discussed also that the deicing assembly is quiet to rotor blade, the influence of dynamic characteristic and intensity.People such as Chang Shinan are at Chang Shinan, Liu Dajing, Yuan Xiugan. helicopter rotor blade is prevented/research of ice removal system protective range. the aviation power journal, pass through to analyze surperficial every hot-fluid in 2007, the limit critical speed of state of freezing when the gauging surface temperature is zero, determined the blade exhibition to icing protective range for along opening up to from the wing root to the wing tip 0～95%; Adopt and analyze the Lagrangian method calculating droplets impact its characteristic that water droplet moves in airflow field, determine that chord of blade is a upper surface 12% to icing protective range, lower surface 33%.People such as Liu Zhengjiang are at Liu Zhengjiang, and Gu Han wears golden flower; Liu Fuhua; Li Xinmin. the warm characteristic test technical study of blade deicing carbon fiber heating component. observation and control technology, the warm characteristic of blade deicing carbon fiber heating component has been carried out experimental study in 2009, obtained first hand test figures.
Domestic anti-deicing systematic research concentrates on structure, performance and the layout of deicing heating component about helicopter, all fails to provide the scheme of a whole set of anti-deicing system.The deicing heating component is the execution unit of the anti-deicing system of lifting airscrew, needs and control corresponding system and switching arrangement match, and forms the anti-deicing system of lifting airscrew jointly, carries out rotor and prevents the deicing task.
Summary of the invention
The objective of the invention is to propose a kind of ice preventing and removing device for helicopter rotors in order to address the above problem.
Ice preventing and removing device for helicopter rotors of the present invention comprises icing detector, icing speed solver, atmosphere temperature transducer, anti-deicing control panel, digital anti-deicing controller, main rotor distributor, empennage distributor, main rotor deicing assembly, empennage deicing assembly, a source of AC and No. two source of ACs;
Icing detector is installed in the main rotor front side, be used to survey the icing degree of main rotor, icing detector is by the icing speed solver of cable connection, speed solver and digital anti-deicing controller cable connection freeze, the speed solver that freezes provides pumping signal and heating power supply to icing detector, the icing degree signal that the speed solver that freezes is surveyed according to icing detector, calculate the cont signal of the icing middle aqueous water of main rotor this moment, and the aqueous water cont signal is sent to digital anti-deicing controller;
Atmosphere temperature transducer is installed on the helicopter head, by the digital anti-deicing controller of cable connection, will measure to such an extent that the ambient-air temperature signal sends digital anti-deicing controller to;
Anti-deicing control panel is by the digital anti-deicing controller of cable connection, the startup of anti-deicing control panel control ice preventing and removing device for helicopter rotors, stops and mode of operation, to digital anti-deicing controller output switching signal and mode of operation signal;
The main rotor distributor control signal and the empennage distributor control signal of digital anti-deicing controller output are input to main rotor distributor and empennage distributor respectively;
The main rotor distributor connects main rotor deicing assembly, and the empennage distributor connects empennage deicing assembly, and the main rotor distributor connects a source of AC, and the empennage distributor connects No. two source of ACs.
The invention has the advantages that:
Ice preventing and removing device for helicopter rotors described in the present invention guarantees helicopter safe flight under severe weather conditions, and avoiding influences the pneumatic external form of rotor because external temperature is crossed low or the too high initiation rotor of liquid water content freezes, and causes safety misadventure.
Description of drawings
Fig. 1 is an ice preventing and removing device for helicopter rotors connection diagram of the present invention;
Fig. 2 is the connection diagram of digital anti-deicing controller of the present invention;
Fig. 3 is the connection diagram of main rotor distributor of the present invention.
Among the figure:
The anti-deicing control panel of the icing speed solver 3-atmosphere temperature transducer 4-of 1-icing detector 2-
A source of AC 7-of the digital anti-deicing control 6-of 5-main rotor distributor 8-empennage distributor
Device
No. two source of AC 10-of 9-main rotor deicing assembly 11-empennage deicing assembly 12-solid-state relay A
The anti-deicing control of 13-sampling hold circuit 14-A/D conv 15-solid-state relay B 16-monolithic
Machine
17-memory device 18-main rotor control signal 19-empennage control signal light 20-solid-state relay C
The photoelectric isolating circuit electric isolating circuit
The outlet of 21-three plase alternating current inlet 22-three plase alternating current
The specific embodiment
The present invention is described in further detail below in conjunction with drawings and Examples.
The present invention is a kind of ice preventing and removing device for helicopter rotors, as shown in Figure 1, comprise icing detector 1, the speed solver 2 that freezes, atmosphere temperature transducer 3, anti-deicing control panel 4, digital anti-deicing controller 5, main rotor distributor 7, empennage distributor 8, main rotor deicing assembly 10, empennage deicing assembly 11, a source of AC 6 and No. two source of ACs 9.
Anti-deicing control panel 4 is by the digital anti-deicing controller 5 of cable connection, the startup of anti-deicing control panel 4 control ice preventing and removing device for helicopter rotors, stops and mode of operation, to digital anti-deicing controller 5 output switching signals and mode of operation signal.
The main rotor distributor control signal and the empennage distributor control signal of digital anti-deicing controller 5 outputs are input to main rotor distributor 7 and empennage distributor 8 respectively.
Digital anti-deicing controller 5 comprises sampling hold circuit 13, A/D converter 14, anti-deicing control single chip computer 16, main rotor control signal photoelectric isolating circuit 18 and empennage control signal photoelectric isolating circuit 19 as shown in Figure 2.
The ambient-air temperature signal of atmosphere temperature transducer 3 output and 2 outputs of icing speed solver the aqueous water cont signal input to sampling hold circuit 13,13 pairs of two incoming signals of sampling hold circuit carry out noise reduction process, transfer to A/D converter 14 behind the signal stabilization, ambient-air temperature signal and aqueous water cont signal are converted into digital signal by A/D converter 14, with two anti-deicing control single chip computers 16 of digital signal input, anti-4 pairs of anti-deicing control single chip computer 16 output switching signals of deicing control panel and mode of operation signal, anti-deicing control single chip computer 16 resolves back transmission main rotor through control law and controls signal to main rotor control signal photoelectric isolating circuit 18, send empennage and control signal to empennage control signal photoelectric isolating circuit 19, main rotor control signal and empennage control signal are converted into main rotor distributor control signal and empennage distributor control signal after isolating through photoelectricity.Anti-deicing control single chip computer 16 is gone back connected storage 17, and anti-deicing micro controller system 16 periodically will deposit memory device 17 in by ambient-air temperature signal and the aqueous water cont signal that A/D converter 14 obtains.
The main rotor distributor comprises three plase alternating current inlet 21 as shown in Figure 3, solid-state relay A12, solid-state relay B15, solid-state relay C20 and three plase alternating current outlet 22.Three plase alternating current inlet 21 connects a source of AC 6, No. one source of AC 6 provides three-phase alternating-current supply for main rotor distributor 7, main rotor distributor control signal inputs to solid-state relay A12, solid-state relay B15, solid-state relay C20, when main rotor distributor control signal is high level, three solid-state relay closures, three plase alternating current inlet 21 exports 22 conductings with three plase alternating current, and the 10 energising work of main rotor deicing assembly are heated main rotor; When main rotor distributor control signal was low level, three solid-state relay were opened, and turn-offed between three plase alternating current inlet 21 and the three plase alternating current outlet 22, and main rotor deicing assembly 10 stops heating work.The three plase alternating current inlet of empennage distributor 8 connects No. two source of ACs 9, No. two source of AC 9 provides three-phase alternating-current supply for empennage distributor 8, empennage distributor 8 incoming signal be empennage distributor control signal, 11 work of control empennage deicing assembly are with main rotor distributor 7.
Main rotor deicing assembly 10 is identical with empennage deicing assembly 11, main rotor deicing assembly 10 comprises interior isolation layer, heating resistance element and outer isolation layer, main rotor deicing assembly 10 is installed between main rotor coating iron at the leading edge and the outer skin, interior isolation layer is a thermal insulating material, outer isolation layer is an insulating material, heating resistance element answer resistance stable and can bear bigger reverse stress.Empennage deicing assembly 11 is between empennage coating iron at the leading edge and outer skin.
The mode of operation of anti-deicing control panel 4 control ice preventing and removing device for helicopter rotors, described mode of operation comprises automatic de-icing and S. A. deicing.
When ice preventing and removing device for helicopter rotors is the automatic de-icing mode, digital anti-deicing controller 5 is periodically gathered aqueous water content and the ambient-air temperature signal that freeze speed solver 2 and atmosphere temperature transducer 3 provide, resolve time of heat and the turn-off time that obtains main rotor deicing assembly 10 and empennage deicing assembly 11 through the internal piloting rule, drive the break-make of main rotor distributor 7 and empennage distributor 8 then respectively.When main rotor distributor 7 closures, No. one source of AC 6 is connected with main rotor deicing assembly 10, and the heater element heating in the main rotor deicing assembly 10 is carried out deicing to main rotor.When empennage distributor 8 closures, No. two source of AC 9 is connected with empennage deicing assembly 11, and the heater element heating in the empennage deicing assembly 11 is carried out deicing to empennage.
When ice preventing and removing device for helicopter rotors is the S. A. mode, the aqueous water cont signal of digital anti-deicing controller 5 inputs is set by anti-deicing control panel 4, digital anti-deicing controller 5 is periodically gathered the ambient-air temperature signal that atmosphere temperature transducer 3 provides, resolve time of heat and the turn-off time that obtains main rotor deicing assembly 10 and empennage deicing assembly 11 through the internal piloting rule, drive the break-make of main rotor distributor 7 and empennage distributor 8 then respectively.When main rotor distributor 7 closures, No. one source of AC 6 is connected with main rotor deicing assembly 10, and the heater element heating in the main rotor deicing assembly 10 is carried out deicing to main rotor.When empennage distributor 8 closures, No. two source of AC 9 is connected with empennage deicing assembly 11, and the heater element heating in the empennage deicing assembly 11 is carried out deicing to empennage.
Claims (7)
1. ice preventing and removing device for helicopter rotors, it is characterized in that, comprise icing detector, icing speed solver, atmosphere temperature transducer, anti-deicing control panel, digital anti-deicing controller, main rotor distributor, empennage distributor, main rotor deicing assembly, empennage deicing assembly, a source of AC and No. two source of ACs;
Icing detector is installed in the main rotor front side, be used to survey the icing degree of main rotor, icing detector is by the icing speed solver of cable connection, speed solver and digital anti-deicing controller cable connection freeze, the speed solver that freezes provides pumping signal and heating power supply to icing detector, the icing degree signal that the speed solver that freezes is surveyed according to icing detector, calculate the cont signal of the icing middle aqueous water of main rotor this moment, and the aqueous water cont signal is sent to digital anti-deicing controller;
Atmosphere temperature transducer is installed on the helicopter head, by the digital anti-deicing controller of cable connection, will measure to such an extent that the ambient-air temperature signal sends digital anti-deicing controller to;
Anti-deicing control panel is by the digital anti-deicing controller of cable connection, the startup of anti-deicing control panel control ice preventing and removing device for helicopter rotors, stops and mode of operation, to digital anti-deicing controller output switching signal and mode of operation signal;
The main rotor distributor control signal and the empennage distributor control signal of digital anti-deicing controller output are input to main rotor distributor and empennage distributor respectively;
The main rotor distributor connects main rotor deicing assembly, and the empennage distributor connects empennage deicing assembly, and the main rotor distributor connects a source of AC, and the empennage distributor connects No. two source of ACs.
2. ice preventing and removing device for helicopter rotors according to claim 1 is characterized in that, described atmosphere temperature transducer is triumphant dress platinum resistance.
3. ice preventing and removing device for helicopter rotors according to claim 1, it is characterized in that described digital anti-deicing controller comprises sampling hold circuit, A/D converter, anti-deicing control single chip computer, main rotor control signal photoelectric isolating circuit and empennage control signal photoelectric isolating circuit;
The ambient-air temperature signal of atmosphere temperature transducer output and the output of icing speed solver the aqueous water cont signal input to sampling hold circuit, sampling hold circuit carries out noise reduction process to two incoming signals, transfer to A/D converter behind the signal stabilization, ambient-air temperature signal and aqueous water cont signal are converted into digital signal by A/D converter, with two anti-deicing control single chip computers of digital signal input, anti-deicing control panel is to anti-deicing control single chip computer output switching signal and mode of operation signal, the process control law of anti-deicing micro controller system resolves back transmission main rotor and controls signal to main rotor control signal photoelectric isolating circuit, send empennage and control signal to empennage control signal photoelectric isolating circuit, main rotor control signal and empennage control signal are converted into main rotor distributor control signal and empennage distributor control signal after isolating through photoelectricity.
4. ice preventing and removing device for helicopter rotors according to claim 3 is characterized in that, anti-deicing micro controller system connected storage, and anti-deicing micro controller system periodically will deposit memory device in by ambient-air temperature signal and the aqueous water cont signal that A/D converter obtains.
5. ice preventing and removing device for helicopter rotors according to claim 1, it is characterized in that, the main rotor distributor is identical with the empennage distributor, the main rotor distributor connects main rotor deicing assembly, the empennage distributor connects empennage deicing assembly, the main rotor distributor comprises the three plase alternating current inlet, solid-state relay A, solid-state relay B, solid-state relay C and three plase alternating current outlet; The three plase alternating current inlet connects a source of AC, No. one source of AC provides three-phase alternating-current supply for the main rotor distributor, main rotor distributor control signal inputs to solid-state relay A, solid-state relay B, solid-state relay C, when main rotor distributor control signal is high level, three solid-state relay closures, three plase alternating current inlet and three plase alternating current outlet conducting, main rotor deicing assembly energising work is heated main rotor; When main rotor distributor control signal was low level, three solid-state relay were opened, and turn-offed between three plase alternating current inlet and the three plase alternating current outlet, and main rotor deicing assembly stops heating work; The three plase alternating current inlet of empennage distributor connects No. two source of ACs, No. two source of AC provides three-phase alternating-current supply for the empennage distributor, the empennage distributor incoming signal be empennage distributor control signal, the work of control empennage deicing assembly is with the main rotor distributor.
6. ice preventing and removing device for helicopter rotors according to claim 1, it is characterized in that, described main rotor deicing assembly is identical with empennage deicing assembly, main rotor deicing assembly comprises interior isolation layer, heating resistance element and outer isolation layer, and main rotor deicing assembly is installed between main rotor coating iron at the leading edge and the outer skin; Empennage deicing assembly is between empennage coating iron at the leading edge and outer skin, and the interior isolation layer of main rotor deicing assembly and empennage deicing assembly is a thermal insulating material, and outer isolation layer is an insulating material, heating resistance element answer resistance stable and can bear reverse stress.
7. ice preventing and removing device for helicopter rotors according to claim 1, it is characterized in that, the mode of operation of described anti-deicing control panel control ice preventing and removing device for helicopter rotors is, when ice preventing and removing device for helicopter rotors is the automatic de-icing mode, aqueous water content and ambient-air temperature signal that icing speed solver of digital anti-deicing controller cycle ground collection and atmosphere temperature transducer provide; When ice preventing and removing device for helicopter rotors is the S. A. mode, the aqueous water cont signal of digital anti-deicing controller input is set by anti-deicing control panel, and the ambient-air temperature signal that atmosphere temperature transducer provides is gathered on digital anti-deicing controller cycle ground.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102364622A CN101695959B (en) | 2009-10-22 | 2009-10-22 | Ice preventing and removing device for helicopter rotors |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102364622A CN101695959B (en) | 2009-10-22 | 2009-10-22 | Ice preventing and removing device for helicopter rotors |
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| Publication Number | Publication Date |
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| CN101695959A true CN101695959A (en) | 2010-04-21 |
| CN101695959B CN101695959B (en) | 2012-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2009102364622A Expired - Fee Related CN101695959B (en) | 2009-10-22 | 2009-10-22 | Ice preventing and removing device for helicopter rotors |
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Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102263442A (en) * | 2010-05-28 | 2011-11-30 | 尤洛考普特公司 | Electrical power supply and control device for equipment of a rotor, and an aircraft fitted with such a device |
| CN102682144A (en) * | 2011-11-30 | 2012-09-19 | 天津空中代码工程应用软件开发有限公司 | Flight icing numerical value simulation method of helicopter rotor wing |
| CN103448912A (en) * | 2012-04-27 | 2013-12-18 | 古德里奇公司 | Aircraft ice protection optimization based on ice-detection input |
| CN103693199A (en) * | 2012-07-31 | 2014-04-02 | 古德里奇公司 | Ice protection system |
| CN104369868A (en) * | 2014-10-24 | 2015-02-25 | 苏州德鲁森自动化系统有限公司 | Automatic detection icebreaking device |
| CN104369869A (en) * | 2014-10-24 | 2015-02-25 | 苏州德鲁森自动化系统有限公司 | Automatic detection type ice breaking device with improved sampling circuit |
| CN104443397A (en) * | 2014-10-24 | 2015-03-25 | 苏州德鲁森自动化系统有限公司 | Detecting and icebreaking device based on signal conditioning circuit |
| CN104570792A (en) * | 2014-10-24 | 2015-04-29 | 苏州德鲁森自动化系统有限公司 | Icebreaking device based on relay automatic control |
| CN105857620A (en) * | 2016-05-06 | 2016-08-17 | 武汉航空仪表有限责任公司 | Main paddle distributor for rotor wing anti-icing/deicing system |
| CN105882978A (en) * | 2016-06-24 | 2016-08-24 | 北京航空航天大学 | Helicopter rotor ice preventing/removing method for spraying freezing condensation nucleuses and deicing liquid through injector heads |
| CN105882980A (en) * | 2016-05-18 | 2016-08-24 | 中国航空工业集团公司西安飞机设计研究所 | Automatic electric heating and deicing system |
| CN106240828A (en) * | 2016-07-27 | 2016-12-21 | 北京航空航天大学 | A kind of lifting airscrew magnetizing super-cooling waterdrop prevents/deicer |
| CN108482683A (en) * | 2018-03-20 | 2018-09-04 | 西安理工大学 | A kind of system and method using the anti-deicing of sliding discharge plasma |
| CN109552644A (en) * | 2018-11-24 | 2019-04-02 | 中国人民解放军空军工程大学 | A kind of netted plasma heat knife |
| CN109733617A (en) * | 2018-12-29 | 2019-05-10 | 中航电测仪器股份有限公司 | A kind of airplane windscreen warm temperature control box |
| CN110481795A (en) * | 2019-09-11 | 2019-11-22 | 山东大学 | A kind of graphene composite material ice preventing and removing device for helicopter rotors and production method |
| CN111301708A (en) * | 2020-03-02 | 2020-06-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Control law electrical heating ice prevention/removal control system |
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| CN111553084A (en) * | 2020-04-30 | 2020-08-18 | 中国直升机设计研究所 | Helicopter icing detection position optimization method, electronic product and storage device |
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| CN102263442A (en) * | 2010-05-28 | 2011-11-30 | 尤洛考普特公司 | Electrical power supply and control device for equipment of a rotor, and an aircraft fitted with such a device |
| CN102682144A (en) * | 2011-11-30 | 2012-09-19 | 天津空中代码工程应用软件开发有限公司 | Flight icing numerical value simulation method of helicopter rotor wing |
| CN102682144B (en) * | 2011-11-30 | 2014-02-19 | 天津空中代码工程应用软件开发有限公司 | Flight icing numerical value simulation method of helicopter rotor wing |
| CN103448912A (en) * | 2012-04-27 | 2013-12-18 | 古德里奇公司 | Aircraft ice protection optimization based on ice-detection input |
| US9555894B2 (en) | 2012-04-27 | 2017-01-31 | Goodrich Corporation | Aircraft ice protection optimization based on ice-detection input |
| CN103693199A (en) * | 2012-07-31 | 2014-04-02 | 古德里奇公司 | Ice protection system |
| CN104369869A (en) * | 2014-10-24 | 2015-02-25 | 苏州德鲁森自动化系统有限公司 | Automatic detection type ice breaking device with improved sampling circuit |
| CN104443397A (en) * | 2014-10-24 | 2015-03-25 | 苏州德鲁森自动化系统有限公司 | Detecting and icebreaking device based on signal conditioning circuit |
| CN104570792A (en) * | 2014-10-24 | 2015-04-29 | 苏州德鲁森自动化系统有限公司 | Icebreaking device based on relay automatic control |
| CN104369868A (en) * | 2014-10-24 | 2015-02-25 | 苏州德鲁森自动化系统有限公司 | Automatic detection icebreaking device |
| CN105857620A (en) * | 2016-05-06 | 2016-08-17 | 武汉航空仪表有限责任公司 | Main paddle distributor for rotor wing anti-icing/deicing system |
| CN105882980A (en) * | 2016-05-18 | 2016-08-24 | 中国航空工业集团公司西安飞机设计研究所 | Automatic electric heating and deicing system |
| CN105882978A (en) * | 2016-06-24 | 2016-08-24 | 北京航空航天大学 | Helicopter rotor ice preventing/removing method for spraying freezing condensation nucleuses and deicing liquid through injector heads |
| CN105882978B (en) * | 2016-06-24 | 2017-10-13 | 北京航空航天大学 | A kind of lifting airscrew of the use injector head injection icing nuclei of condensation and deicing liquid prevents/de-icing method |
| CN106240828A (en) * | 2016-07-27 | 2016-12-21 | 北京航空航天大学 | A kind of lifting airscrew magnetizing super-cooling waterdrop prevents/deicer |
| CN108482683A (en) * | 2018-03-20 | 2018-09-04 | 西安理工大学 | A kind of system and method using the anti-deicing of sliding discharge plasma |
| CN109552644A (en) * | 2018-11-24 | 2019-04-02 | 中国人民解放军空军工程大学 | A kind of netted plasma heat knife |
| CN109733617A (en) * | 2018-12-29 | 2019-05-10 | 中航电测仪器股份有限公司 | A kind of airplane windscreen warm temperature control box |
| CN109733617B (en) * | 2018-12-29 | 2021-12-10 | 中航电测仪器股份有限公司 | Heating temperature control box for airplane windshield glass |
| CN110481795A (en) * | 2019-09-11 | 2019-11-22 | 山东大学 | A kind of graphene composite material ice preventing and removing device for helicopter rotors and production method |
| CN111301708A (en) * | 2020-03-02 | 2020-06-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Control law electrical heating ice prevention/removal control system |
| CN111301708B (en) * | 2020-03-02 | 2021-11-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Control law electrical heating ice prevention/removal control system |
| CN111488027A (en) * | 2020-03-25 | 2020-08-04 | 天津航空机电有限公司 | Control method for 230V alternating current heating load of aircraft anti-icing system |
| CN111553084A (en) * | 2020-04-30 | 2020-08-18 | 中国直升机设计研究所 | Helicopter icing detection position optimization method, electronic product and storage device |
| CN111795796A (en) * | 2020-09-08 | 2020-10-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing wind tunnel ice prevention and removal test method and system |
| CN112731036A (en) * | 2020-12-25 | 2021-04-30 | 武汉航空仪表有限责任公司 | System and method for detecting heating fault of main rotor of rotor wing deicing and preventing system |
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