CN102407942B - Ice formation condition detector - Google Patents
Ice formation condition detector Download PDFInfo
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- CN102407942B CN102407942B CN201110262725.4A CN201110262725A CN102407942B CN 102407942 B CN102407942 B CN 102407942B CN 201110262725 A CN201110262725 A CN 201110262725A CN 102407942 B CN102407942 B CN 102407942B
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- temperature
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
Abstract
The invention provides a kind of ice formation condition detector, comprising: sensing element, it comprises temperature sense layer and heat insulation layer, embedded resistor silk in temperature sense layer, heat insulation layer is fixed on the inner surface of described temperature sense layer; Temperature sensor, for measuring the real time temperature of sensing element; And controller, it comprises: heating control module, for constant electrical power resistive heater, so that the temperature of sensing element remains on more than 0 DEG C; Data memory module, for storing the temperature objectives value of sensing element under different flying conditions, and gathers the real time temperature value of the sensing element that records by temperature sensor; Processor, for retrieve the temperature objectives value of sensing element certain flying condition from data memory module, and contrasts itself and real time temperature value, if real time temperature value is less than temperature objectives value, judges that aircraft meets with ice-formation condition.
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 may cause aircraft to grasp steady quality degradation, flying quality loss and flight safetyNargin declines. Icing detection technology can detect in early days aircraft and freeze, to take in timeCorresponding actions is a corrective measure of flight safety. " SAEAIR4367AAircraftInflightIceDetectorsandIcingRateMeasuringInstruments " survey freezingKind is introduced, and mainly contains two kinds of modes: the knot of the icing state of hunter reference surfaceIce sounder, or the whether ice formation condition detector in ice-formation condition of hunter.
Civil aircraft A340/A380/B747/B777/ERJ/CRJ has equipped GOODRICH companyIcing detector. Probe is made up of magnetostriction materials, and probe vibration frequency is along with icing qualityIncrease vibration frequency and decline, send icing signal after being reduced to threshold values. B787 equipmentThe ice formation condition detector of GOODRICH company, does wet platinum resistance thermometers by two in probeForm an electric bridge, the different voltage differences of ice-formation condition, voltage change sends to threshold values the letter that freezesNumber. Weak point is: overhanging probe destroys wing and engine inlets etc. and easily freezes surperficialAerodynamic configuration, be generally arranged on plane nose, indirect control and supervision wing and engine inlets etc.Surperficial icing state easily freezes.
MD-80/90 aircraft has been equipped a kind of icing detector that flushes installation at upper surface of the airfoil,Detector is connected by cable with controller. Along with detector surface constantly freezes, the matter of freezingAmount increases rises detector vibration frequency, and frequency exceedes after threshold value, and detector sends the letter that freezesNumber. Weak point is: icing quality to a certain extent after, could survey freeze, this opportunityThe ice of certain mass may have been gathered on the easily icing surface such as the wing and engine inlets; And,Sensor surface is plane, and the easily icing surface such as wing and engine inlets is curved surface, installsShi Buneng agrees with completely.
Summary of the invention
In order to address the above problem, the invention provides a kind of ice formation condition detector, it can be neatSafety is contained in aircraft and easily freezes surface as the position such as wing and engine inlets, and does not destroy itAerodynamic configuration, and can directly reflect the icing situation of protection coating of freezing.
Design principle of the present invention:
When aircraft flies in dry air (there is no super-cooling waterdrop in air), detector surface existsUnder the effect of the hot-fluid such as heat convection, Aerodynamic Heating item, surface temperature be flying condition (speed,The angle of attack, atmospheric temperature and height) function. Ice-formation condition (in air, exist cold water to drip,Also referred to as humid air, the super-cooling waterdrop quality in available units volume---Liquid water content g/m3TableLevy) in when flight, detector surface is in warm such as water evaporative heat loss, heat convection and Aerodynamic HeatingsUnder a stream effect, surface temperature is the function of flying condition and ice-formation condition. Same flying conditionUnder, detector surface is different with temperature in humid air at dry air, is called dry and wet temp poor. The temperature differenceSize is relevant with Liquid water content, and the temperature difference can judge whether aircraft has met with ice-formation condition accordingly.The theory of the psychrometer face temperature difference and temperature threshold and computational methods, particular content can be mediate referring to fur coatGuiding principle, 5.6 chapters-surface temperature in " aircraft anti-icing system " that Han Fenghua writes.
According to an aspect of the present invention, provide a kind of ice formation condition detector, comprising:
Sensing element, it flushes and is arranged on the easily icing surperficial upper of aircraft, described sensing element bagDraw together temperature sense layer and heat insulation layer, embedded resistor silk in described temperature sense layer, for heatingState temperature sense layer, described heat insulation layer is fixed on the inner surface of described temperature sense layer, forThe heat that prevents described temperature sense layer scatters and disappears by its inner surface;
Temperature sensor, it is fixed on the inner surface of described temperature sense layer, for measuringState the real time temperature of sensing element; And
Controller, it comprises heating control module, data memory module and processor, wherein:
Described heating control module is used for heating described resistance wire with constant electrical power, so that described inThe temperature of sensing element remains on more than 0 DEG C;
The temperature of described data memory module for storing described sensing element under different flying conditionsDesired value, and gather the real time temperature of the described sensing element that records by described temperature sensorValue;
Described processor is for from described in described data memory module retrieves certain flying conditionThe temperature objectives value of sensing element, and itself and real time temperature value are contrasted, if described real-timeTemperature value is less than described temperature objectives value, judges that aircraft meets with ice-formation condition.
Wherein, described temperature sensor is connected with described controller by holding wire.
Wherein, described controller is connected with avionics system with aircraft power supply by electric connection.
Wherein, described temperature sense layer uses the strong metal of thermal conductivity to make, such as copper, aluminium etc.
According to another aspect of the present invention, provide a kind of ice-formation condition detection method, wherein makeUse above-mentioned ice formation condition detector, described method comprises step:
(1) measure in real time the real-time temperature of sensing element with certain refresh rate by temperature sensorSpend, and by holding wire, real time temperature value is delivered to the data memory module of described controller;
(2) obtain the current flying condition of aircraft by described controller from Aircraft electric system,And from data memory module, retrieve this flying condition according to flying condition by described processorThe temperature objectives value of lower sensing element;
(3) by described processor, described real time temperature value and described temperature objectives value are carried out rightRatio, if described real time temperature value is less than described temperature objectives value, judges that aircraft meets with icingCondition, and excite icing signal;
(4) be delivered to Aircraft electric system by the electric connection signal that will freeze, prompting flight unitManually boot anti-icing system or aircraft and automatically start anti-icing system.
Wherein, in described step (1), heat with constant electrical power by heating control moduleDescribed resistance wire, so that the temperature of described sensing element remains on more than 0 DEG C, prevents induction unitPart outer surface freezes.
Beneficial effect of the present invention is:
1. the temperature sense layer profile of sensing element can be arbitrary surface, can flush and be arranged onWing, engine inlets etc. easily freeze surperficial, agree with completely with mounting surface, do not affect peaceFill surperficial aerodynamic configuration;
2. the icing situation that can directly reflect the protection coating that freezes, does not exist due to installation siteThe critical-temperature difference causing;
3. can, before wing, engine inlets do not freeze, detect aircraft and enter and finishIce condition, has the ability of icing early warning, reduces the anti-icing system reaction time;
4. temperature sense layer uses the strong metal of thermal conductivity to make, unrestricted to metal types.
Brief description of the drawings
Fig. 1 is the structural representation according to ice formation condition detector of the present invention.
Detailed description of the invention
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 flushing being arranged on the easily icing surperficial sensing element 1 such as wing and engine inlets,For measuring temperature sensor 2, controller 3 and the electric connection 4 of sensing element temperature.
Sensing element 1 is made up of temperature sense layer 5 and heat insulation layer 6. Embedding in temperature sense layer 5Enter resistance wire (not shown), for heating-up temperature inductive layer 5. Heat insulation layer 6 is fixing for example logicalCross polymer adhesive on the inner surface of temperature sense layer 5, for preventing temperature sense layer 5Heat scatters and disappears by its inner surface. Sensing element 1 for example flushes by ring flange etc. the machine of being arranged onThe wing and engine inlets etc. easily freeze surface above, and temperature sense layer 5 agrees with mounting surface,Contact with ambient atmosphere.
Temperature sensor 2 is fixed on the inner surface of temperature sense layer 5, for example can be by bondingAgent bonds in the groove arranging on inner surface, for measuring the real time temperature of described sensing element.The surfaces externally and internally temperature difference of metal sensing element is minimum, and described temperature herein refers generally to induction unitThe temperature sense layer hull-skin temperature of part.
Controller 3 is made up of heating control module 7, data memory module 8 and processor 9.Resistance wire is connected with controller 3 by supply lines, and heating control module 7 is with constant electrical powerResistive heater, thereby heating-up temperature inductive layer 5, so that sensing element 1 is at difference flight barUnder part and ice-formation condition, temperature remains on more than 0 DEG C, prevents that sensing element 1 outer surface from freezing. TemperatureDegree sensor 2 is connected with controller 3 by holding wire, controller 3 by electric connection 4 andAircraft power supply is connected with avionics system. Data memory module 8 is for storing different flying conditionsThe surface temperature desired value of lower sensing element 1, and gather the sense recording by temperature sensor 2Answer the real-time table surface temperature value of element 1. Processor 9 is for retrieving from data memory module 8Go out the surface temperature desired value of sensing element 1 under certain flying condition, and by itself and described in real timeSurface temperature value contrasts, if described real-time table surface temperature value is less than described surface temperature orderScale value, judges that aircraft meets with ice-formation condition.
Controller 3 can adopt split design with sensing element 1. Sensing element 1 can be manufacturedMust be very little, and controller 3 volumes are larger. If installing space is limited in aircraft slat, can be bySensing element is made split, is connected with supply lines by holding wire.
The present invention also provides a kind of ice-formation condition detection method, uses the icing bar shown in Fig. 1Part detector 10, described method comprises step:
(1) measure in real time the reality of sensing element 1 with certain refresh rate by temperature sensor 2Time surface temperature, and by holding wire, real-time table surface temperature value is delivered to the data of controller 3Memory module 8. By heating control module 7 with constant electrical power resistive heater so that senseAnswer the temperature of element 1 to remain on more than 0 DEG C, prevent that sensing element 1 outer surface from freezing. Due toThe temperature working range of temperature sensor 2 is higher than the temperature of the rear sensing element 1 of heating, so addHeat can not affect the real-time table surface temperature of measuring sensing element 1.
(2) obtain the current flying condition (speed of aircraft by controller 3 from Aircraft electric systemDegree, highly, the angle of attack and atmospheric temperature), and by processor 9 according to flying condition from dataIn memory module 8, retrieve the surface temperature desired value of sensing element under this flying condition;
(3) pass through processor 9 by described real-time table surface temperature value and described surface temperature desired valueContrast, if described real-time table surface temperature value is less than described surface temperature desired value, sentenceDetermine aircraft and meet with ice-formation condition, and excite icing signal.
(4) be delivered to Aircraft electric system by the electric connection signal that will freeze, prompting flight unitManually boot anti-icing system or aircraft and automatically start anti-icing system.
The data memory module 8 of controller 3 stored different flying conditions (speed, highly,The angle of attack and atmospheric temperature) the surface temperature desired value of lower sensing element 1 is temperature threshold. DifferentThe surface temperature desired value of sensing element under flying condition is through calculating and store early stageIn memory module, do not need microprocessor to calculate in real time the table of sensing element under this flying conditionSurface temperature desired value, thus computing time effectively reduced.
Core of the present invention is the temperature drop that utilizes the protection coating super-cooling waterdrop evaporative heat loss that freezes to formForm new ice-formation condition criterion, utilize temperature threshold to replace the frequency of conventional junction ice sounderRate threshold value, triggers icing alarm 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 and be arranged onWing, engine inlets etc. easily freeze surperficial, agree with completely with mounting surface, do not affect peaceFill surperficial aerodynamic configuration;
2. can, before wing, engine inlets do not freeze, detect aircraft and enter and finishIce condition, has the ability of icing early warning, reduces the anti-icing system reaction time;
3. can directly reflect the icing situation of the protection coating that freezes, exempt from overhanging sonde-type and frozenThe critical-temperature difference that detector causes due to installation site;
4. temperature sense layer uses the strong metal of thermal conductivity to make, unrestricted to metal types.
Described in the present invention, concrete case study on implementation is only better case study on implementation of the present invention, andNon-ly be used for limiting practical range of the present invention. It is all contents according to the present patent application the scope of the claims instituteThe equivalence of doing changes and modifies, and all belongs 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 easily icing surface that is arranged on aircraft, described sensing element comprises temperature sense layer and heat insulation layer, embedded resistor silk in described temperature sense layer, be used for heating described temperature sense layer, described heat insulation layer is fixed on the inner surface of described temperature sense layer, scatters and disappears by its inner surface for the heat that prevents described temperature sense layer;
Temperature sensor, it is fixed on the inner surface of described temperature sense layer, for measuring the real time temperature of described sensing element; And
Controller, it comprises heating control module, data memory module and processor, wherein:
Described heating control module is for heating described resistance wire with constant electrical power, so that the temperature of described sensing element remains on more than 0 DEG C;
Described data memory module is used for the temperature objectives value of storing described sensing element under different flying conditions, and gathers the real time temperature value of the described sensing element recording by described temperature sensor;
Described processor is for retrieving the temperature objectives value of described sensing element certain flying condition from described data memory module, and itself and real time temperature value are contrasted, if described real time temperature value is less than described temperature objectives value, judge that aircraft meets with ice-formation condition.
2. ice formation condition detector according to claim 1, is characterized in that, described temperature sensor is connected with described controller by holding wire.
3. ice formation condition detector according to claim 1 and 2, is characterized in that, described controller is connected with avionics system with aircraft power supply by electric connection.
4. ice formation condition detector according to claim 1, is characterized in that, described temperature sense layer uses the strong metal of thermal conductivity to make.
5. an ice-formation condition detection method, is characterized in that, uses according to the ice formation condition detector described in any one in claim 1-4, and described method comprises step:
(1) measure in real time the real time temperature of sensing element with certain refresh rate by temperature sensor, and by holding wire, real time temperature value is delivered to the data memory module of described controller;
(2) obtain the current flying condition of aircraft by described controller from Aircraft electric system, and from data memory module, retrieve the temperature objectives value of sensing element under this flying condition by described processor according to flying condition;
(3) by described processor, described real time temperature value and described temperature objectives value are contrasted, if described real time temperature value is less than described temperature objectives value, judges that aircraft meets with ice-formation condition, and excite icing signal;
(4) be delivered to Aircraft electric system by the electric connection signal that will freeze, prompting flight unit manually boots anti-icing system or aircraft starts anti-icing system automatically;
Wherein, in described step (1), heat described resistance wire by heating control module with constant electrical power, so that the temperature of described sensing element remains on more than 0 DEG C, prevent that sensing element outer surface from freezing.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110262725.4A CN102407942B (en) | 2011-09-06 | 2011-09-06 | Ice formation 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 | Ice formation condition detector |
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| Publication Number | Publication Date |
|---|---|
| CN102407942A CN102407942A (en) | 2012-04-11 |
| CN102407942B true CN102407942B (en) | 2016-05-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201110262725.4A Active CN102407942B (en) | 2011-09-06 | 2011-09-06 | Ice formation condition detector |
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| CN (1) | CN102407942B (en) |
| WO (1) | WO2013034083A1 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102407942B (en) * | 2011-09-06 | 2016-05-04 | 中国商用飞机有限责任公司 | Ice formation condition detector |
| US20130299637A1 (en) * | 2012-05-08 | 2013-11-14 | The Boeing Company | 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 | Anti-icing device for aircraft |
| DE102013217774A1 (en) | 2012-09-11 | 2014-03-13 | Infineon Technologies Austria Ag | CIRCUITS, SYSTEMS AND METHODS FOR INTEGRATING DETECTION AND HEATING FUNCTIONS |
| CN103101626B (en) * | 2012-12-04 | 2015-09-02 | 中国商用飞机有限责任公司 | Icing detector |
| EP3031726B1 (en) | 2014-12-08 | 2016-11-02 | Zodiac Aerotechnics | Wing element for aircraft |
| 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 |
| CN105472801B (en) * | 2015-12-18 | 2019-04-26 | 新昌县利果机械有限公司 | A kind of rotary heating inductor |
| CN110914535B (en) * | 2017-06-29 | 2022-04-08 | 维斯塔斯风力系统集团公司 | Detecting water on a wind turbine using temperature controlled sensors |
| US11242152B2 (en) * | 2017-11-17 | 2022-02-08 | Ge Aviation Systems Llc | Method and apparatus for detecting ice accretion |
| CN108128466B (en) * | 2018-04-26 | 2018-07-27 | 中国商用飞机有限责任公司 | Image-type icing detector and icing detection method |
| CN108128467B (en) * | 2018-04-26 | 2018-07-27 | 中国商用飞机有限责任公司 | Icing detector and icing detection method |
| CN108820227B (en) * | 2018-07-03 | 2021-12-03 | 上海工程技术大学 | Predictive ice prevention and removal method utilizing graphene heating film |
| CN108956684B (en) * | 2018-07-28 | 2020-11-03 | 哈尔滨工业大学 | Embedded concrete early-stage freezing and icing nondestructive testing method |
| CN109696383A (en) * | 2019-01-25 | 2019-04-30 | 南京航空航天大学 | A kind of material surface anti-icing performance evaluation method based on statistics formula measurement result |
| CN110606209B (en) * | 2019-09-10 | 2022-08-16 | 中国商用飞机有限责任公司 | Icing detector |
| CN112678188A (en) * | 2020-12-25 | 2021-04-20 | 武汉航空仪表有限责任公司 | Icing detector based on impedance measurement principle |
| CN112550724B (en) * | 2020-12-25 | 2023-12-22 | 武汉航空仪表有限责任公司 | Icing detection system and method based on impedance measurement |
| CN113420503B (en) * | 2021-06-11 | 2022-08-12 | 中国民航大学 | Icing detection method, system, terminal and application based on temperature sequence similarity measurement |
| CN114476083A (en) * | 2021-12-31 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Shape-preserving type icing detection system and method |
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| Publication number | Publication date |
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| CN102407942A (en) | 2012-04-11 |
| WO2013034083A1 (en) | 2013-03-14 |
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