CN102407942A - Icing condition detector - Google Patents
Icing condition detector Download PDFInfo
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- CN102407942A CN102407942A CN2011102627254A CN201110262725A CN102407942A CN 102407942 A CN102407942 A CN 102407942A CN 2011102627254 A CN2011102627254 A CN 2011102627254A CN 201110262725 A CN201110262725 A CN 201110262725A CN 102407942 A CN102407942 A CN 102407942A
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- 238000010438 heat treatment Methods 0.000 claims abstract description 17
- 230000036413 temperature sense Effects 0.000 claims description 25
- 238000000034 method Methods 0.000 claims description 8
- 238000007710 freezing Methods 0.000 claims description 7
- 230000008014 freezing Effects 0.000 claims description 7
- 229910052751 metal Inorganic materials 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 7
- 238000001514 detection method Methods 0.000 claims description 4
- 230000035699 permeability Effects 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 230000006698 induction Effects 0.000 abstract 5
- 238000013500 data storage Methods 0.000 abstract 2
- 238000009413 insulation Methods 0.000 abstract 2
- 238000009434 installation Methods 0.000 description 9
- 239000003570 air Substances 0.000 description 6
- 239000011248 coating agent Substances 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 239000000523 sample Substances 0.000 description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 239000012080 ambient air Substances 0.000 description 3
- 230000001939 inductive effect Effects 0.000 description 3
- 238000004781 supercooling Methods 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 description 2
- 230000035484 reaction time Effects 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 230000000875 corresponding effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 229910052697 platinum Inorganic materials 0.000 description 1
Images
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
- B64D15/20—Means for detecting icing or initiating de-icing
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
- Measuring Temperature Or Quantity Of Heat (AREA)
Abstract
The present invention provides an icing condition detector comprising: the induction element comprises a temperature induction layer and a heat insulation layer, wherein a resistance wire is embedded in the temperature induction layer, and the heat insulation layer is fixed on the inner surface of the temperature induction layer; a temperature sensor for measuring a real-time temperature of the sensing element; and a controller, comprising: the heating control module is used for heating the resistance wire with constant electric power so as to keep the temperature of the induction element above 0 ℃; the data storage module is used for storing the temperature target values of the sensing elements under different flight conditions and acquiring real-time temperature values of the sensing elements measured by the temperature sensors; and the processor is used for retrieving the temperature target value of the sensing element under a certain flight condition from the data storage module, comparing the temperature target value with the real-time temperature value, and judging that the aircraft encounters an icing condition if the real-time temperature value is smaller than the temperature target value.
Description
Technical field
The present invention relates to the icing field of detecting of aircraft, be specifically related to a kind of ice-formation condition detector.
Background technology
Aircraft freezes and possibly cause aircraft to grasp steady quality degradation, airworthiness loss and Flight Safety Margin decline.Icing detection technology can detect aircraft in early days and freeze, so that in time take corresponding actions, is an innovative approach of flight safety." SAE AIR4367A Aircraft Inflight Ice Detectors and Icing Rate Measuring Instruments " surveys kind to freezing and introduces; Mainly contain dual mode: the icing detector of the icing state of hunter reference surface, perhaps whether hunter is in the ice-formation condition detector of ice-formation condition.
Civil aircraft A340/A380/B747/B777/ERJ/CRJ has equipped the icing detector of GOODRICH company.Probe is processed by magnetostriction materials, and the probe vibration frequency descends along with icing quality increases oscillation frequency, sends icing signal after being reduced to threshold values.The ice-formation condition detector of B787 equipment GOODRICH company is done wet platinum resistance thermometer by two in the probe and is constituted an electric bridge, and the different voltages of ice-formation condition are different, and change of voltage is sent icing signal to threshold values.Weak point is: overhanging probe destroys wing and engine inlets etc. and is prone to the surperficial aerodynamic configuration that freezes, and generally is installed in plane nose, the icing state on the easy surface that freezes such as indirect control and supervision wing and engine inlets.
The MD-80/90 aircraft has been equipped a kind of icing detector that flushes installation at upper surface of the airfoil, and detector is connected through cable with controller.Along with detector surface constantly freezes, the quality increase of freezing is risen the detector oscillation frequency, and after frequency surpassed threshold value, detector sent icing signal.Weak point is: after the quality of freezing arrives to a certain degree, could survey and freeze, the ice of certain mass maybe have been gathered on the easy surface that freezes such as wing and engine inlets at this moment; And sensor surface is the plane, and it is curved surface that wing and engine inlets etc. are prone to icing surface, can not agree with fully during installation.
Summary of the invention
In order to address the above problem; The present invention provides a kind of ice-formation condition detector; It can flush and be installed in the easy surface that freezes of aircraft like positions such as wing and engine inlets, and does not destroy its aerodynamic configuration, and can directly reflect the icing situation of the protection coating that freezes.
Principle of design of the present invention:
When aircraft flew in dry air (not having super-cooling waterdrop in the air), detector surface was under hot-fluid item effects such as convective heat exchange, pneumatic heating, and surface temperature is the function of flying condition (speed, the angle of attack, ambient-air temperature and height).(exist cold water to drip in the air, be also referred to as wet air, super-cooling waterdrop the quality---aqueous water content g/m in the available units volume in ice-formation condition
3When flying sign), detector surface is under hot-fluid item effects such as water evaporative heat loss, convective heat exchange and pneumatic heating, and surface temperature is the function of flying condition and ice-formation condition.Under the same flying condition, detector surface temperature in dry air and wet air is different, and it is poor to be called dry and wet temp.Temperature difference size is relevant with aqueous water content, and the temperature difference can judge whether aircraft has met with ice-formation condition in view of the above.The theory of the psychrometer face temperature difference and temperature threshold and method of calculating, particular content can be referring to Qiu Xiegang, 5.6 chapters-surface temperature in " aircraft anti-icing system " that Han Fenghua writes.
According to an aspect of the present invention, a kind of ice-formation condition detector is provided, comprises:
Sensing element; It flushes on the easy surface that freezes that is installed in aircraft; Said sensing element comprises temperature sense layer and adiabatic layer, and embedded resistor silk in the said temperature sense layer is used to heat said temperature sense layer; Said adiabatic layer is fixed on the inside face of said temperature sense layer, is used to prevent that the heat of said temperature sense layer scatters and disappears through its inside face;
Temperature sensor, it is fixed on the inside face of said temperature sense layer, is used to measure the real time temperature of said sensing element; And
Controller, it comprises heating control module, data memory module and treater, wherein:
Said heating control module is used for heating said resistor wire with constant electric power, so that the temperature of said sensing element remains on more than 0 ℃;
Said data memory module is used to store the temperature objectives value of said sensing element under the different flying conditions, and gathers the real time temperature value of the said sensing element that records through said temperature sensor;
Said treater is used for retrieving from said data memory module the temperature objectives value of said sensing element under certain flying condition; And itself and real time temperature value compared; If said real time temperature value is then judged aircraft encounter ice-formation condition less than said temperature objectives value.
Wherein, said temperature sensor is connected with said controller through signal wire (SW).
Wherein, said controller is connected with avionics system with aircraft power supply through electric connection.
Wherein, said temperature sense layer uses the strong metal of permeability of heat to process, for example copper, aluminium etc.
According to another aspect of the present invention, a kind of ice-formation condition detection method is provided, wherein uses above-mentioned ice-formation condition detector, said method comprises step:
(1) measures the real time temperature of sensing element through temperature sensor in real time with certain refresh rate, and the real time temperature value is delivered to the data memory module of said controller through signal wire (SW);
(2) obtain the current flying condition of aircraft through said controller from the aircraft avionics system, and from data memory module, retrieve the temperature objectives value of sensing element under this flying condition according to flying condition through said treater;
(3) through said treater said real time temperature value and said temperature objectives value are compared,, and excite icing signal if said real time temperature value is then judged aircraft encounter ice-formation condition less than said temperature objectives value;
(4) be delivered to the aircraft avionics system through the electric connection signal that will freeze, prompting flight unit manually boots anti or aircraft starts anti automatically.
Wherein, in said step (1), heat said resistor wire with constant electric power,, prevent that the sensing element outside face from freezing so that the temperature of said sensing element remains on more than 0 ℃ through heating control module.
Beneficial effect of the present invention is:
1. the temperature sense layer profile of sensing element can be arbitrary surface, can flush to be installed in the easy surface that freezes such as wing, engine inlets, agrees with fully with installation surface, do not influence the aerodynamic configuration of installation surface;
2. the icing situation that can directly reflect the protection coating that freezes does not exist because the critical temperature difference that the installation site causes;
3. can before wing, engine inlets not freeze, detect aircraft and get into ice-formation condition, have the ability of icing early warning, reduce the anti reaction time;
4. the temperature sense layer uses the strong metal of permeability of heat to process, and is unrestricted to metal types.
Description of drawings
Fig. 1 is the structural representation according to ice-formation condition detector of the present invention.
The specific embodiment
Describe the preferred embodiment of ice-formation condition detector of the present invention in detail below in conjunction with accompanying drawing.
As shown in Figure 1; It schematically shows according to ice-formation condition detector 10 of the present invention; Comprise to flush being installed in the sensing element 1 that wing and engine inlets etc. are prone to icing surface, be used to measure the temperature sensor 2 of sensing element temperature, controller 3 and electric connection 4.
Sensing element 1 is made up of temperature sense layer 5 and adiabatic layer 6.Embedded resistor silk (not shown) is used for heating-up temperature inductive layer 5 in the temperature sense layer 5.Adiabatic layer 6 is fixed and for example is bonded on the inside face of temperature sense layer 5 through adhesives, is used to prevent that the heat of temperature sense layer 5 scatters and disappears through its inside face.Sensing element 1 for example flushes through flange etc. and is installed in wing and engine inlets etc. and is prone to freeze on the surface, and temperature sense layer 5 agrees with installation surface, contacts with ambient atmosphere.
Controller 3 is made up of heating control module 7, data memory module 8 and treater 9.Resistor wire is connected with controller 3 through supply line; Heating control module 7 is with constant electric power resistive heater; Thereby heating-up temperature inductive layer 5 so that sensing element 1 remains on more than 0 ℃ in temperature under different flying conditions and the ice-formation condition, prevents that sensing element 1 outside face from freezing.Temperature sensor 2 is connected with controller 3 through signal wire (SW), and controller 3 is connected with avionics system with aircraft power supply through electric connection 4.Data memory module 8 is used to store the surface temperature expected value of sensing element 1 under the different flying conditions, and gathers the real-time table surface temperature value of the sensing element 1 that records through temperature sensor 2.Treater 9 is used for retrieving from data memory module 8 the surface temperature expected value of sensing element 1 under certain flying condition; And itself and said real-time table surface temperature value compared; If said real-time table surface temperature value is then judged aircraft encounter ice-formation condition less than said surface temperature expected value.
Controller 3 can adopt the split design with sensing element 1.Sensing element 1 can be made very for a short time, and controller 3 volumes are bigger.If installing space is limited in the aircraft slat, can sensing element be made split, be connected with supply line through signal wire (SW).
The present invention also provides a kind of ice-formation condition detection method, uses the ice-formation condition detector 10 shown in Fig. 1, and said method comprises step:
(1) measures the real-time table surface temperature of sensing element 1 through temperature sensor 2 in real time with certain refresh rate, and real-time table surface temperature value is delivered to the data memory module 8 of controller 3 through signal wire (SW).With constant electric power resistive heater,, prevent that sensing element 1 outside face from freezing through heating control module 7 so that the temperature of sensing element 1 remains on more than 0 ℃.Because the temperature operating range of temperature sensor 2 is higher than the temperature of heating back sensing element 1, heating can not influence the real-time table surface temperature of measuring sensing element 1.
(2) obtain the current flying condition of aircraft (speed, highly, the angle of attack and ambient-air temperature) through controller 3 from the aircraft avionics system, and from data memory module 8, retrieve the surface temperature expected value of sensing element under this flying condition according to flying condition through treater 9;
(3) through treater 9 said real-time table surface temperature value and said surface temperature expected value are compared,, and excite icing signal if said real-time table surface temperature value is then judged aircraft encounter ice-formation condition less than said surface temperature expected value.
(4) be delivered to the aircraft avionics system through the electric connection signal that will freeze, prompting flight unit manually boots anti or aircraft starts anti automatically.
The data memory module 8 of controller 3 stored different flying conditions (speed, highly, the angle of attack and ambient-air temperature) down the surface temperature expected value of sensing element 1 be temperature threshold.The surface temperature expected value of sensing element under the different flying conditions; Be through calculating and be stored in the memory module early stage; Do not need microprocessor to calculate the surface temperature expected value of sensing element under this flying condition in real time, thereby reduced computing time effectively.
Core of the present invention is that the temperature drop that utilizes the protection coating super-cooling waterdrop evaporative heat loss that freezes to form forms new ice-formation condition criterion, utilizes temperature threshold to replace the frequency threshold of conventional junction ice sounder, triggers icing alerting signal.
Ice-formation condition detector of the present invention has the following advantages:
1. the temperature sense layer profile of sensing element can be arbitrary surface, can flush to be installed in the easy surface that freezes such as wing, engine inlets, agrees with fully with installation surface, do not influence the aerodynamic configuration of installation surface;
2. can before wing, engine inlets not freeze, detect aircraft and get into ice-formation condition, have the ability of icing early warning, reduce the anti reaction time;
3. the icing situation that can directly reflect the protection coating that freezes has been exempted from overhanging sonde-type icing detector because the critical temperature difference that the installation site causes;
4. the temperature sense layer uses the strong metal of permeability of heat to process, and is unrestricted to metal types.
The case of practical implementation described in the present invention is merely preferable case study on implementation of the present invention, is not to be used for limiting practical range of the present invention.Be that all equivalences of doing according to the content of claim of the present invention change and modification, all belong to protection scope of the present invention.
Claims (5)
1. an ice-formation condition detector is characterized in that, comprising:
Sensing element; It flushes on the easy surface that freezes that is installed in aircraft; Said sensing element comprises temperature sense layer and adiabatic layer, and embedded resistor silk in the said temperature sense layer is used to heat said temperature sense layer; Said adiabatic layer is fixed on the inside face of said temperature sense layer, is used to prevent that the heat of said temperature sense layer scatters and disappears through its inside face;
Temperature sensor, it is fixed on the inside face of said temperature sense layer, is used to measure the real time temperature of said sensing element; And
Controller, it comprises heating control module, data memory module and treater, wherein:
Said heating control module is used for heating said resistor wire with constant electric power, so that the temperature of said sensing element remains on more than 0 ℃;
Said data memory module is used to store the temperature objectives value of said sensing element under the different flying conditions, and gathers the real time temperature value of the said sensing element that records through said temperature sensor;
Said treater is used for retrieving from said data memory module the temperature objectives value of said sensing element under certain flying condition; And itself and real time temperature value compared; If said real time temperature value is then judged aircraft encounter ice-formation condition less than said temperature objectives value.
2. ice-formation condition detector according to claim 1 is characterized in that, said temperature sensor is connected with said controller through signal wire (SW).
3. ice-formation condition detector according to claim 1 and 2 is characterized in that, said controller is connected with avionics system with aircraft power supply through electric connection.
4. ice-formation condition detector according to claim 1 is characterized in that, said temperature sense layer uses the strong metal of permeability of heat to process.
5. an ice-formation condition detection method is characterized in that, uses according to each described ice-formation condition detector among the claim 1-4, and said method comprises step:
(1) measures the real time temperature of sensing element through temperature sensor in real time with certain refresh rate, and the real time temperature value is delivered to the data memory module of said controller through signal wire (SW);
(2) obtain the current flying condition of aircraft through said controller from the aircraft avionics system, and from data memory module, retrieve the temperature objectives value of sensing element under this flying condition according to flying condition through said treater;
(3) through said treater said real time temperature value and said temperature objectives value are compared,, and excite icing signal if said real time temperature value is then judged aircraft encounter ice-formation condition less than said temperature objectives value;
(4) be delivered to the aircraft avionics system through the electric connection signal that will freeze, prompting flight unit manually boots anti or aircraft starts anti automatically.
Wherein, in said step (1), heat said resistor wire with constant electric power,, prevent that the sensing element outside face from freezing so that the temperature of said sensing element remains on more than 0 ℃ through heating control module.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110262725.4A CN102407942B (en) | 2011-09-06 | 2011-09-06 | icing condition detector |
| PCT/CN2012/081044 WO2013034083A1 (en) | 2011-09-06 | 2012-09-06 | Freezing condition detector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110262725.4A CN102407942B (en) | 2011-09-06 | 2011-09-06 | icing condition detector |
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| CN102407942A true CN102407942A (en) | 2012-04-11 |
| CN102407942B CN102407942B (en) | 2016-05-04 |
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| CN201110262725.4A Active CN102407942B (en) | 2011-09-06 | 2011-09-06 | icing condition detector |
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| WO (1) | WO2013034083A1 (en) |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102897324A (en) * | 2012-07-13 | 2013-01-30 | 中国商用飞机有限责任公司 | Aircraft anti-icing device |
| WO2013034083A1 (en) * | 2011-09-06 | 2013-03-14 | 中国商用飞机有限责任公司 | Freezing condition detector |
| CN103101626A (en) * | 2012-12-04 | 2013-05-15 | 中国商用飞机有限责任公司 | Icing detector |
| CN103387055A (en) * | 2012-05-08 | 2013-11-13 | 波音公司 | Ice protection for aircraft using electroactive polymer surfaces |
| CN103687101A (en) * | 2012-09-11 | 2014-03-26 | 英飞凌科技奥地利有限公司 | Circuits, systems and methods for integrating sensing and heating functions |
| CN105083559A (en) * | 2015-09-21 | 2015-11-25 | 成都乐也科技有限公司 | Temperature probe used for detecting icing situation on surface of airplane |
| CN105416593A (en) * | 2015-12-11 | 2016-03-23 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft deicing system |
| CN105472801A (en) * | 2015-12-18 | 2016-04-06 | 苏州权素船舶电子有限公司 | Rotary heating inductor |
| CN108128467A (en) * | 2018-04-26 | 2018-06-08 | 中国商用飞机有限责任公司 | Icing detector and icing detection method |
| CN108128466A (en) * | 2018-04-26 | 2018-06-08 | 中国商用飞机有限责任公司 | Image type icing detector and icing detection method |
| CN108820227A (en) * | 2018-07-03 | 2018-11-16 | 上海工程技术大学 | A method of utilizing the anti-deicing of the forecasting type of graphene heating film |
| CN108956684A (en) * | 2018-07-28 | 2018-12-07 | 哈尔滨工业大学 | A kind of embedded type concrete early freezc icing lossless detection method |
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| CN110606209A (en) * | 2019-09-10 | 2019-12-24 | 中国商用飞机有限责任公司 | Icing detector |
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| WO2013034083A1 (en) * | 2011-09-06 | 2013-03-14 | 中国商用飞机有限责任公司 | Freezing condition detector |
| CN103387055A (en) * | 2012-05-08 | 2013-11-13 | 波音公司 | Ice protection for aircraft using electroactive polymer surfaces |
| CN102897324B (en) * | 2012-07-13 | 2015-06-10 | 中国商用飞机有限责任公司 | Aircraft anti-icing device |
| CN102897324A (en) * | 2012-07-13 | 2013-01-30 | 中国商用飞机有限责任公司 | Aircraft anti-icing device |
| US9664178B2 (en) | 2012-09-11 | 2017-05-30 | Infineon Technologies Austria Ag | Circuits, systems and methods for integrating sensing and heating functions |
| CN103687101A (en) * | 2012-09-11 | 2014-03-26 | 英飞凌科技奥地利有限公司 | Circuits, systems and methods for integrating sensing and heating functions |
| CN103101626A (en) * | 2012-12-04 | 2013-05-15 | 中国商用飞机有限责任公司 | Icing detector |
| CN103101626B (en) * | 2012-12-04 | 2015-09-02 | 中国商用飞机有限责任公司 | Icing detector |
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| WO2013034083A1 (en) | 2013-03-14 |
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