CN105416593A - Aircraft deicing system - Google Patents
Aircraft deicing system Download PDFInfo
- Publication number
- CN105416593A CN105416593A CN201510922490.5A CN201510922490A CN105416593A CN 105416593 A CN105416593 A CN 105416593A CN 201510922490 A CN201510922490 A CN 201510922490A CN 105416593 A CN105416593 A CN 105416593A
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- Prior art keywords
- heating elements
- electrical heating
- aircraft
- icing
- ice
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- 238000010438 heat treatment Methods 0.000 claims description 119
- 230000001680 brushing effect Effects 0.000 claims description 7
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000005485 electric heating Methods 0.000 abstract 4
- 239000010410 layer Substances 0.000 abstract 1
- 239000002344 surface layer Substances 0.000 abstract 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 19
- 238000007710 freezing Methods 0.000 description 3
- 230000008014 freezing Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- IWEDIXLBFLAXBO-UHFFFAOYSA-N dicamba Chemical compound COC1=C(Cl)C=CC(Cl)=C1C(O)=O IWEDIXLBFLAXBO-UHFFFAOYSA-N 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012512 characterization method Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000021715 photosynthesis, light harvesting Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000004781 supercooling Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Resistance Heating (AREA)
Abstract
The invention discloses an aircraft deicing system and relates to the technical field of aircraft deicing. The aircraft deicing system comprises electric heating elements, icing thickness detectors and a deicing control device. The electric heating elements are arranged on the inner sides of windward surface icing regions of an aircraft. The icing thickness detectors are arranged on the windward surface icing regions of the aircraft. After the icing thickness detectors detect that the windward surfaces are iced, icing thickness information is transmitted to the deicing control device, the deicing control device controls the electric heating elements to heat the windward surfaces according to the icing thickness, the bonding force between ice layers and the windward surfaces of the aircraft is eliminated, and after ice attached to the surface layers of the aircraft is melted, the ice is blown through pneumatic power to be separated from the windward surfaces of the aircraft. The aircraft deicing system has the beneficial effects that the deicing control device can control the electric heating elements to heat the icing regions according to the icing thickness information of the windward surfaces of the aircraft, the energy of the aircraft is saved, and the deicing thickness range is wide.
Description
Technical field
The present invention relates to aircraft clearing ice technology field, be specifically related to a kind of aircraft ice removal system.
Background technology
When aircraft enters icing meteorology condition in flight course, surface (such as the leading edge of a wing) there will be accumulated ice and affects flight safety windward.In existing airplane in transportation category airworthiness requirement, the diameter of icing super-cooling waterdrop is caused to be no more than 50 μm.The diameter crossing cold large water droplet (SLD) has exceeded 50 μm, compares conventional little water droplet and freezes, its icing wide range on aerofoil, is the serious special ice-formation condition of one of harm.Cross the icing seaworthiness that all the time do not enter of cold large water droplet and authorize requirement, the anti-ice removal system of existing routine mainly designs for little water droplet, can not cover the icing scope of large water droplet completely.On November 3rd, 2014 FAA formally issued amendment 25-140, require that transport plane should cross safe operation under cold large water droplet ice-formation condition.
Because the impingement area crossing cold large water droplet is wider, need the region of heating larger.If mentality of designing conveniently, heat is covered the ice field being cold large water droplet, can meet the deicing demand of cold large water droplet, but the actual deicing provided adds heat much larger than demand electricity under the cold little water droplet icing condition of mistake, causes aircraft energy dissipation.Therefore, need to seek a kind of protective system that can adapt to cold large water droplet and freeze, and can avoid when little water droplet freezes heating on a large scale, reduce the waste of energy.
Summary of the invention
The object of this invention is to provide a kind of aircraft ice removal system, with the problem at least one place solved or existing at least alleviating in background technology.
Technical scheme of the present invention is: provide a kind of aircraft ice removal system, and comprise electrical heating elements, freeze caliper detector and deicing control setup, wherein, described electrical heating elements is arranged on the inner side of the surperficial windward icing area of aircraft; Described icing caliper detector is arranged on the surperficial windward icing area of aircraft; Icing caliper detector detect windward surface freeze after, icing thickness information is transferred to deicing control setup, deicing control setup is according to icing THICKNESS CONTROL electrical heating elements heating surface windward, eliminate ice sheet and the binding force of aircraft windward between surface, after the ice that aircraft top layer is adhered to dissolves, under the brushing of aerodynamic force, disengaging aircraft is surperficial windward.
Preferably, described electrical heating elements is arranged on the leading edge of a wing, and multiple to being provided with along airfoil chord.
Preferably, described electrical heating elements airfoil chord to each part correspondence be provided with icing caliper detector.
Preferably, described multiple electrical heating elements can relatively independent work.
Preferably, the leading edge stationary point place of described wing is provided with electrical heating elements, is disposed with 4 electrical heating elements, the airfoil outer surface that each electrical heating elements is corresponding is provided with icing caliper detector at airfoil chord to away from direction, leading edge stationary point; When aircraft flies into ice field, the electrical heating elements energising at the leading edge stationary point place of described wing, and start periodical duty according to predetermined period, when aircraft surface freeze thickness exceed setting value time, start working at the electrical heating elements of respective regions to 4 electrical heating elements set gradually away from direction, leading edge stationary point at airfoil chord.
Preferably, the predetermined period of the electrical heating elements at the leading edge stationary point place of described wing is, often heats after 3 minutes and stops 5 minutes.
Preferably, the described aircraft surface setting value Main Basis of the thickness thickness that freezes that freezes causes icing power to wing, and icing power should be less than the tolerance value of wing.
Preferably, when starting working to one or more in 4 electrical heating elements set gradually away from direction, leading edge stationary point at airfoil chord, corresponding surface temperature is heated to exceed zero temperature, after the ice that wing skins adheres to dissolves, detachment machine wing surface under the brushing of aerodynamic force.
Preferably, after aircraft flies away from icing area, all electrical heating elements work 3 minutes, to eliminate all accumulated ice, then closes ice removal system.
Preferably, described ice removal system comprises Non-follow control and automatically controls two kinds of patterns.
Beneficial effect of the present invention: aircraft ice removal system of the present invention is provided with electrical heating elements, freeze caliper detector and deicing control setup, deicing control setup the icing thickness information surperficial windward according to aircraft can control electrical heating elements heating icing area, saved the energy of aircraft, and deicing thickness range is wide.
Electrical heating elements is arranged on the leading edge of a wing, and it is multiple to being provided with along airfoil chord, multiple electrical heating elements can relatively independent work, electrical heating elements airfoil chord to each part correspondence be provided with icing caliper detector, refinement ice field, different according to the thickness of icing area, the heat that electrical heating elements provides is also different, saves the aircraft energy.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of an embodiment of aircraft ice removal system of the present invention;
Fig. 2 is that electrical heating elements embodiment illustrated in fig. 1 arranges schematic diagram.
Wherein, 1, electrical heating elements, 1-1, electrical heating elements, 1-2, electrical heating elements, 1-3, electrical heating elements, 1-4, electrical heating elements, 1-5, electrical heating elements, 2, freeze caliper detector, 2-1, icing caliper detector, 2-2, icing caliper detector, 2-3, icing caliper detector, 2-4, freeze caliper detector, and 3, deicing control setup.
Detailed description of the invention
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
As shown in Figure 1 and Figure 2, a kind of aircraft ice removal system, comprise electrical heating elements 1, freeze caliper detector 2 and deicing control setup 3, wherein, electrical heating elements 1 is arranged on the inner side of the surperficial windward icing area of aircraft; The caliper detector 2 that freezes is arranged on the surperficial windward icing area of aircraft; Freeze caliper detector 2 detect windward surface freeze after, icing thickness information is transferred to deicing control setup 3, deicing control setup 3 heats surface windward according to icing THICKNESS CONTROL electrical heating elements 1, eliminate ice sheet and the binding force of aircraft windward between surface, after the ice that aircraft top layer is adhered to dissolves, under the brushing of aerodynamic force, disengaging aircraft is surperficial windward.
Aircraft ice removal system of the present invention is provided with electrical heating elements, freeze caliper detector and deicing control setup, deicing control setup the icing thickness information surperficial windward according to aircraft can control electrical heating elements heating icing area, saved the energy of aircraft, and deicing thickness range is wide.
In the present embodiment, described ice removal system is used aboard, and electrical heating elements 1 is arranged on the leading edge of a wing, and multiple to being provided with along airfoil chord.At the tangential of wing, the leading edge of a wing is divided into multiple part, electrical heating elements 1 airfoil chord to each part correspondence be provided with icing caliper detector 2.Multiple electrical heating elements 1 can relatively independent work.
Electrical heating elements is arranged on the leading edge of a wing, and it is multiple to being provided with along airfoil chord, multiple electrical heating elements can relatively independent work, electrical heating elements airfoil chord to each part correspondence be provided with icing caliper detector, refinement ice field, different according to the thickness of icing area, the heat that electrical heating elements provides is also different, saves the aircraft energy.
In the present embodiment, the leading edge stationary point place of wing is provided with electrical heating elements 1-1, electrical heating elements 1-2 is disposed with to away from direction, leading edge stationary point at airfoil chord, electrical heating elements 1-3, electrical heating elements 1-4 and electrical heating elements 1-5, the airfoil outer surface that electrical heating elements 1-2 is corresponding is provided with icing caliper detector 2-1, the airfoil outer surface that electrical heating elements 1-3 is corresponding is provided with icing caliper detector 2-2, the airfoil outer surface that electrical heating elements 1-4 is corresponding is provided with icing caliper detector 2-3, the airfoil outer surface that electrical heating elements 1-5 is corresponding is provided with icing caliper detector 2-4, when aircraft flies into ice field, electrical heating elements 1-1 is energized, and start periodical duty according to predetermined period, when aircraft surface freeze thickness exceed setting value time, electrical heating elements 1-2, electrical heating elements 1-3, the electrical heating elements 1-4 and electrical heating elements 1-5 of respective regions start working.
Be understandable that, electrical heating elements 1-2, electrical heating elements 1-3, electrical heating elements 1-4 and electrical heating elements 1-5 can work simultaneously, also can work independently.
In the present embodiment, at airfoil chord to the electrical heating elements 1-2 set gradually away from direction, leading edge stationary point, electrical heating elements 1-3, the scope of the icing area that electrical heating elements 1-4 and electrical heating elements 1-5 covers strengthens successively, namely the tangential of wing that be arranged in of electrical heating elements arranges that near leading edge stationary point place density is larger, to away from direction, leading edge stationary point, the layout density of electrical heating elements can be amplified relatively, its advantage is, owing to freezing the most serious at close leading edge of a wing stationary point place, icing thickness is larger, by arranging that the electrical heating elements strengthening density can improve the degree of utilization of electrical heating elements, thus save the energy of aircraft.
In the present embodiment, the predetermined period of electrical heating elements 1-1 is, often heats after 3 minutes and stops 5 minutes.Its advantage is, electrical heating elements 1-1 heats three minutes, is enough to the layers of ice crossing cold little water droplet to melt, and again can heat, be conducive to saving the aircraft energy after being separated by 5 minutes.
The described aircraft surface setting value Main Basis of the thickness thickness that freezes that freezes causes icing power to wing, and icing power should be less than the tolerance value of wing.Be conducive to the protection protecting aircraft icing area.
Under icing meteorology condition, first the electrical heating elements 1-1 at most leading edge stationary point place enters the heated condition of energising, starts working according to the deicing cycle of design.In remaining electrical heating elements region, respectively the caliper detector 2 that freezes is installed, measures the icing thickness of wing zones of different in real time, and icing thickness information is passed to deicing control setup 3.After the icing thickness measuring certain region exceedes the wing tolerance value of setting, deicing control setup 3 sends signal, corresponding electrical heating elements electrified regulation.
When one or more in electrical heating elements 1-2, electrical heating elements 1-3, electrical heating elements 1-4 and electrical heating elements 1-5 start working, corresponding surface temperature is heated to exceed zero temperature, after the ice that wing skins adheres to dissolves, under the brushing of aerodynamic force, detachment machine wing surface, reaches the object of deicing.
Under little water droplet ice-formation condition, less heater element just can meet deicing demand, and under large water droplet ice-formation condition, multiple heater element is electrified regulation simultaneously, meets the deicing needs of scope of freezing more greatly.
After aircraft flies away from icing area, all electrical heating elements work 3 minutes, to eliminate all accumulated ice, then closes ice removal system.
Ice removal system comprises Non-follow control and automatically controls two kinds of patterns.Automatic control is as preferred mode, and after autonomous cruise speed system breaks down, system sends chimes of doom or warning indication lamp lights, and reminds navigating mate manual manipulation.Automatic control mode saves the energy of power aviator, is conducive to the driving of aviator, arranges MANUAL CONTROL mode for subsequent use simultaneously, improve the deicing safety factor of aircraft.
The reason that the present invention adapted to cold large water droplet icing is: traditional electrical heating deicing system designs according to common little water droplet ice field, and when aircraft enters icing area, after system unlatching work, all electrical heating elements heated according to certain cycle.Feature of the present invention is that the leading edge of a wing is divided into different regions, electrical heating elements and icing caliper detector is arranged at regional, Real-time Obtaining freezes thickness, according to the icing thickness information detected, control the energising of zones of different electrical heating elements and power-off, under little water droplet condition, the electrical heating elements of non-ice field just need not be opened, and has saved the energy.
Principle of work of the present invention is: the surface windward of aircraft is divided into different regions, and the icing situation according to surperficial zones of different windward regulates the opening and closing of respective regions electrical heating elements in real time, automatically adapts to the deicing demand under large/little water droplet condition.In the present embodiment, when aircraft enters icing, open electrical heating deicing system, electrical heating elements 1-1 is energized, according to the cycle heating deicing designed in advance, all the other electrical heating elements (1-2,1-3,1-4,1-5) are according to the concrete situation work of freezing of its region.The icing caliper detector (2-1,2-2,2-3,2-4) being arranged on the leading edge of a wing measures wing icing thickness in real time, and icing thickness information is passed to deicing control setup 3.When measuring after the corresponding thickness that freezes exceedes the wing tolerance value of setting, deicing control setup 3 sends signal, and corresponding electrical heating elements enters heated condition, by the attachment ice-out of wing skins, and detachment machine wing surface under the brushing of aerodynamic force.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (10)
1. an aircraft ice removal system, is characterized in that: comprise electrical heating elements (1), freeze caliper detector (2) and deicing control setup (3), wherein,
Described electrical heating elements (1) is arranged on the inner side of the surperficial windward icing area of aircraft;
Described icing caliper detector (2) is arranged on the surperficial windward icing area of aircraft; Freeze caliper detector (2) detect windward surface freeze after, icing thickness information is transferred to deicing control setup (3), deicing control setup (3) is according to THICKNESS CONTROL electrical heating elements (1) the heating surface windward that freezes, eliminate ice sheet and the binding force of aircraft windward between surface, after the ice that aircraft top layer is adhered to dissolves, under the brushing of aerodynamic force, disengaging aircraft is surperficial windward.
2. aircraft ice removal system as claimed in claim 1, is characterized in that: described electrical heating elements (1) is arranged on the leading edge of a wing, and multiple to being provided with along airfoil chord.
3. aircraft ice removal system as claimed in claim 2, is characterized in that: described electrical heating elements (1) airfoil chord to each part correspondence be provided with icing caliper detector (2).
4. aircraft ice removal system as claimed in claim 3, is characterized in that: described multiple electrical heating elements (1) can relatively independent work.
5. aircraft ice removal system as claimed in claim 4, it is characterized in that: the leading edge stationary point place of described wing is provided with electrical heating elements (1-1), electrical heating elements (1-2) is disposed with to away from direction, leading edge stationary point at airfoil chord, electrical heating elements (1-3), electrical heating elements (1-4) and electrical heating elements (1-5), the airfoil outer surface corresponding at electrical heating elements (1-2) is provided with icing caliper detector (2-1), the airfoil outer surface corresponding at electrical heating elements (1-3) is provided with icing caliper detector (2-2), the airfoil outer surface corresponding at electrical heating elements (1-4) is provided with icing caliper detector (2-3), the airfoil outer surface corresponding at electrical heating elements (1-5) is provided with icing caliper detector (2-4), when aircraft flies into ice field, electrical heating elements (1-1) is energized, and start periodical duty according to predetermined period, when aircraft surface freeze thickness exceed setting value time, the electrical heating elements (1-2) of respective regions, electrical heating elements (1-3), electrical heating elements (1-4) and electrical heating elements (1-5) are started working.
6. aircraft ice removal system as claimed in claim 5, is characterized in that: the predetermined period of described electrical heating elements (1-1) is, often heats after 3 minutes and stops 5 minutes.
7. aircraft ice removal system as claimed in claim 5, is characterized in that: the described aircraft surface setting value Main Basis of the thickness thickness that freezes that freezes causes icing power to wing, and icing power should be less than the tolerance value of wing.
8. aircraft ice removal system as claimed in claim 5, it is characterized in that: when one or more in electrical heating elements (1-2), electrical heating elements (1-3), electrical heating elements (1-4) and electrical heating elements (1-5) start working, corresponding surface temperature is heated to exceed zero temperature, after the ice that wing skins adheres to dissolves, detachment machine wing surface under the brushing of aerodynamic force.
9. aircraft ice removal system as claimed in claim 5, it is characterized in that: after aircraft flies away from icing area, all electrical heating elements work 3 minutes, to eliminate all accumulated ice, then closes ice removal system.
10. the aircraft ice removal system as described in claim 1 to 9 any one, is characterized in that: described ice removal system comprises Non-follow control and automatically controls two kinds of patterns.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510922490.5A CN105416593A (en) | 2015-12-11 | 2015-12-11 | Aircraft deicing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510922490.5A CN105416593A (en) | 2015-12-11 | 2015-12-11 | Aircraft deicing system |
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| CN105416593A true CN105416593A (en) | 2016-03-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510922490.5A Pending CN105416593A (en) | 2015-12-11 | 2015-12-11 | Aircraft deicing system |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106184768A (en) * | 2016-07-22 | 2016-12-07 | 中国航空工业集团公司西安飞机设计研究所 | A kind of adaptive wing steam deicing system |
| CN106741968A (en) * | 2016-12-29 | 2017-05-31 | 华中科技大学 | A kind of combined type deicing system based on the detection of ice sheet skin-surface bonding state |
| CN109625291A (en) * | 2018-12-04 | 2019-04-16 | 石家庄飞机工业有限责任公司 | A kind of biplane ice-detector system |
| CN109641663A (en) * | 2016-09-08 | 2019-04-16 | 通用电气航空***有限责任公司 | For the deicing module of aircraft and for the method for deicing |
| CN110481793A (en) * | 2019-07-12 | 2019-11-22 | 中国人民解放军空军工程大学 | A kind of new electrically heating ice shape regulation method and anti-freeze type aircraft |
| CN110606209A (en) * | 2019-09-10 | 2019-12-24 | 中国商用飞机有限责任公司 | Icing detector |
| CN111114793A (en) * | 2019-12-13 | 2020-05-08 | 武汉航空仪表有限责任公司 | Icing detection system capable of detecting large supercooled water drops |
| CN111268142A (en) * | 2020-03-16 | 2020-06-12 | 中国电子科技集团公司第三十八研究所 | Anti-icing structure of unmanned aerial vehicle wing |
| CN111452979A (en) * | 2020-04-27 | 2020-07-28 | 西北工业大学 | Deicing device and unmanned aerial vehicle |
| CN111680256A (en) * | 2020-06-16 | 2020-09-18 | 中国空气动力研究与发展中心计算空气动力研究所 | Method for calculating icing density of airplane |
| CN113236406A (en) * | 2021-06-30 | 2021-08-10 | 奇瑞汽车股份有限公司 | Heating device of exhaust system, exhaust system and automobile |
| CN113286391A (en) * | 2021-05-31 | 2021-08-20 | 华中科技大学 | Ice detecting and removing device and method |
| CN113815869A (en) * | 2021-09-24 | 2021-12-21 | 中国航空工业集团公司西安飞机设计研究所 | Icing state aircraft angle of attack protection control method |
| CN114104300A (en) * | 2022-01-27 | 2022-03-01 | 成都凯天电子股份有限公司 | Deicing device and deicing method thereof |
| EP4147975A1 (en) * | 2021-09-08 | 2023-03-15 | Airbus Operations GmbH | Flow body with two heating devices distanced in chordwise direction |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| 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 |
| 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 |
| CN106184768A (en) * | 2016-07-22 | 2016-12-07 | 中国航空工业集团公司西安飞机设计研究所 | A kind of adaptive wing steam deicing system |
| CN109641663A (en) * | 2016-09-08 | 2019-04-16 | 通用电气航空***有限责任公司 | For the deicing module of aircraft and for the method for deicing |
| CN109641663B (en) * | 2016-09-08 | 2022-05-24 | 通用电气航空***有限责任公司 | Deicing module for an aircraft and method for deicing |
| CN106741968A (en) * | 2016-12-29 | 2017-05-31 | 华中科技大学 | A kind of combined type deicing system based on the detection of ice sheet skin-surface bonding state |
| CN106741968B (en) * | 2016-12-29 | 2019-06-18 | 华中科技大学 | A kind of combined type deicing system detected based on ice sheet-skin-surface bonding state |
| CN109625291A (en) * | 2018-12-04 | 2019-04-16 | 石家庄飞机工业有限责任公司 | A kind of biplane ice-detector system |
| CN110481793A (en) * | 2019-07-12 | 2019-11-22 | 中国人民解放军空军工程大学 | A kind of new electrically heating ice shape regulation method and anti-freeze type aircraft |
| CN110606209A (en) * | 2019-09-10 | 2019-12-24 | 中国商用飞机有限责任公司 | Icing detector |
| CN110606209B (en) * | 2019-09-10 | 2022-08-16 | 中国商用飞机有限责任公司 | Icing detector |
| CN111114793A (en) * | 2019-12-13 | 2020-05-08 | 武汉航空仪表有限责任公司 | Icing detection system capable of detecting large supercooled water drops |
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| CN111452979A (en) * | 2020-04-27 | 2020-07-28 | 西北工业大学 | Deicing device and unmanned aerial vehicle |
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| CN113236406A (en) * | 2021-06-30 | 2021-08-10 | 奇瑞汽车股份有限公司 | Heating device of exhaust system, exhaust system and automobile |
| EP4147975A1 (en) * | 2021-09-08 | 2023-03-15 | Airbus Operations GmbH | Flow body with two heating devices distanced in chordwise direction |
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| CN113815869B (en) * | 2021-09-24 | 2024-02-02 | 中国航空工业集团公司西安飞机设计研究所 | Icing aircraft attack angle protection control method |
| CN114104300A (en) * | 2022-01-27 | 2022-03-01 | 成都凯天电子股份有限公司 | Deicing device and deicing method thereof |
| CN114104300B (en) * | 2022-01-27 | 2022-05-24 | 成都凯天电子股份有限公司 | Deicing device and deicing method thereof |
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