CN109696290A - A kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system - Google Patents
A kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system Download PDFInfo
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- CN109696290A CN109696290A CN201910120043.6A CN201910120043A CN109696290A CN 109696290 A CN109696290 A CN 109696290A CN 201910120043 A CN201910120043 A CN 201910120043A CN 109696290 A CN109696290 A CN 109696290A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K17/00—Measuring quantity of heat
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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Abstract
The invention discloses a kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring systems, are related to wind-tunnel technique field, its key points of the technical solution are that: including icing wind tunnel test section and wing segment model, wing segment model surface is covered with measuring unit；Measuring unit includes electric calorifie installation for maintaining wing segment model surface predetermined temperature and for the temperature sensor of Induction Heating device heating temperature；Measuring unit is connected with the control unit of control electric calorifie installation heating power variation；Control unit includes controller and power supply unit；Electric calorifie installation is connected with the power meter of real-time measurement electric calorifie installation heating power；Electric calorifie installation, temperature sensor and controller are connect with power supply unit.With the measuring system being made up of measuring unit and control unit, real-time measurement goes out the heating power of wing segment model surface electric calorifie installation, to calculate Anti-icing Heat Loads demand by heating power, achieve the purpose that the effect of survey aircraft wing section surface Anti-icing Heat Loads demand.
Description
Technical field
The present invention relates to wind-tunnel technique fields, more specifically, it relates to a kind of wind energy conversion system wing panel Anti-icing Heat Loads
Demand measuring system.
Background technique
Aircraft is at subfreezing temperature when flight, if encountering the cloud layer containing super-cooling waterdrop, the water droplet in cloud layer
It impinges upon on aircraft surfaces, will lead to freeze.It is a kind of phenomenon being widely present in flight practice that aircraft, which freezes, and is caused
One of main hidden danger of flight safety accident.The Flow Field of aircraft can be changed by freezing, and components ' load distribution is caused to change,
To destroy aerodynamic performance, the maneuverability and stability of aircraft are influenced, flight safety is endangered, less serious case can make safe flight
Range reduces, and severe one will lead to the major accident of fatal crass.Since aircraft invention, due to having when airplane crash caused by freezing
Occur, therefore, the anti-ice problem of aircraft is also always the important research contents of aviation field.It is big that the anti-icing system of aircraft is divided into two
Class: first is that anti-icing system；Second is that deicing system.Mainly there are hot air anti-icing and electro-thermal anti-ice for the method for anti-icing system.Into
When row electro thermal ice protection system design process, need that Anti-icing Heat Loads demand is measured and calculated.
Current Anti-icing Heat Loads demand analysis mainly carries out the Numerical-Mode of aircraft icing by some icing software for calculation
Quasi- research.
In the prior art for the measurement of wing section surface Anti-icing Heat Loads demand mainly pass through icing software for calculation into
Row simulation calculates.Simulated by icing software for calculation and calculate Anti-icing Heat Loads demand, fail to be reduced directly various weather conditions and
The physical process that cross-ventilation factor freezes to plane wing surfaces, so far it is not yet found that by directly measurement in different stabilizations
The heating power of electric calorifie installation calculates Anti-icing Heat Loads demand under the weather conditions of parameter, to realize survey aircraft wing section
The method of the purpose of surface Anti-icing Heat Loads demand.
Summary of the invention
The object of the present invention is to provide a kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring systems, have single by measurement
The measuring system that member and control unit are constituted, can real-time measurement go out the heating power of wing segment model surface electric calorifie installation, from
And the Anti-icing Heat Loads demand of wing segment model is calculated by heating power, so that it is anti-icing to reach survey aircraft wing section surface
The effect of the purpose of thermal force demand.
Above-mentioned technical purpose of the invention has the technical scheme that a kind of anti-icing heat of wind energy conversion system wing panel
Load requirements measuring system, the wing segment model including icing wind tunnel test section and in icing wind tunnel test section, the machine
Wing panel model surface is covered with the measuring unit for measuring machine wing panel model Anti-icing Heat Loads demand information；The measuring unit
Including for maintaining the electric calorifie installation of wing segment model surface predetermined temperature and for the temperature of Induction Heating device heating temperature
Sensor；The measuring unit is connected with the control unit of control electric calorifie installation heating power variation；Described control unit includes
The controller and power supply unit being connect with temperature sensor；The electric calorifie installation is connected with real-time measurement electric calorifie installation heating power
Power meter；The electric calorifie installation, temperature sensor and controller are connect with power supply unit.
By using above-mentioned technical proposal, in icing wind tunnel test section, Anti-icing Heat Loads demand is carried out to wing segment model
When measurement, the equipment opened the refrigeration equipment in icing wind tunnel test section and manufacture air-flow and cloud and mist field, to simulate measurement
The climatic condition feature of wing segment model surface Anti-icing Heat Loads demand；It is entire Anti-icing Heat Loads demand by power supply unit
Measuring system is powered；Wing segment model surface is heated using the electric calorifie installation in measuring unit, to be maintained
The anti-icing predetermined temperature in wing segment model surface；Incude the electric heating for being covered in wing segment model surface in real time by temperature sensor
The heating temperature of device, then the temperature information sensed is transferred to controller by temperature sensor；Controller is receiving temperature
Degree sensor sensing to temperature information after the temperature information is analyzed and processed, and judge whether the temperature information reaches anti-
The only temperature range that wing segment model surface freezes；If the temperature information is not within the scope of predetermined temperature, controller according to
The temperature information controls to adjust the heating power of electric calorifie installation, so that the heating temperature of electric calorifie installation reaches wing segment model
The temperature of surface Anti-icing Heat Loads demand；By power meter, can real-time measurement go out the heating power of electric calorifie installation, to pass through
The heating power of electric calorifie installation calculates the Anti-icing Heat Loads demand of wing segment model, to reach survey aircraft wing section surface
The purpose of Anti-icing Heat Loads demand.
The present invention is further arranged to: the controller include the data signal processor being connect with temperature sensor and with
The data storage cell of data signal processor connection；The controller is connected with variable resistance.
By using above-mentioned technical proposal, the temperature information that the electric calorifie installation sensed heats is transferred to by temperature sensor
Data signal processor, data signal processor is after receiving the temperature information that temperature sensor is experienced and to the temperature
Information is analyzed and processed；Then data signal processor is by the temperature information and storage in the data store scheduled
The temperature range that Anti-icing Heat Loads need is compared and judges；If the temperature information not in scheduled heating temperature range,
Data signal processor controls adjustable resistor work according to the temperature information；Resistance is carried out by the work of adjustable resistor
It adjusts, so that the size of the electric current in the circuit constituted to electric calorifie installation and power supply unit is adjusted, to adjust electric heating dress
The power in operating circuit is set, achievees the effect that the heating power for controlling electric calorifie installation.
The present invention is further arranged to: the heating temperature of the electric calorifie installation is 2~5 DEG C.
By using above-mentioned technical proposal, 2~5 DEG C are set by the heating temperature of electric calorifie installation, convenient for using incomplete
The electro-thermal anti-ice mode of evaporation guarantees that the heating temperature of electric calorifie installation is slightly above freezing point.
The present invention is further arranged to: the electric calorifie installation is the flexible electrical for not influencing wing segment model surface flow state
Hotting mask；The temperature sensor is the membrane type temperature sensor connecting with flexible electrothermal membrane, and the temperature sensor is multiple
Interval is covered in flexible electric heating film surface；Zhan Xiangyu wing segment model surface of the flexible electrothermal membrane along wing segment model surface
It is detachably pasted by bonding mode.
By using above-mentioned technical proposal, the temperature sensor of flexible electric heating film surface is covered in by multiple intervals, just
In the heating temperature of integrated sensor cable flexible electrothermal membrane, to improve the essence of the heating temperature of temperature sensor senses flexible electrothermal membrane
Accuracy；Detachably it is glued by flexible electrothermal membrane along the Zhan Xiangyu wing segment model surface on wing segment model surface, so that soft
Property Electric radiant Heating Film does not influence the flow regime on wing segment model surface after connecting with wing segment model surface；
Meanwhile flexible electrothermal membrane is detachably connected by way of splicing with wing segment model surface, be easily installed with more
Change the measurement that flexible electrothermal membrane carries out Anti-icing Heat Loads demand to wing segment model surface different location.
The present invention is further arranged to: the flexible electrothermal membrane is graphene material.
By using above-mentioned technical proposal, the flexible electrothermal membrane made of graphene material, convenient for improving electric calorifie installation
To the stability of the heating power on wing segment model surface.
The present invention is further arranged to: the electric calorifie installation, temperature sensor, power supply unit and controller constitute temperature control
Degeneration factor processed.
By using above-mentioned technical proposal, temperature is constituted by electric calorifie installation, temperature sensor, power supply unit and controller
It controls degeneration factor and passes through control convenient for the temperature information that the heating temperature and temperature sensor according to electric calorifie installation are experienced
The heating power of device automatic controlled electric heating device processed；When the heating power of electric calorifie installation is more than Anti-icing Heat Loads demand temperature,
The heating power that controller controls to adjust electric calorifie installation reduces, so that the heating temperature of electric calorifie installation reduces；When electric heating fills
When the heating power set is lower than Anti-icing Heat Loads demand temperature, the heating power that controller controls to adjust electric calorifie installation increases, from
And the heating temperature of electric calorifie installation is become larger, so that the heating temperature of electric calorifie installation can be stably maintained at wing Duan Mo
In the heating temperature range of type surface Anti-icing Heat Loads demand.
The present invention is further arranged to: the temperature sensor and electric calorifie installation surface are coated with thermal insulation layer.
Electric calorifie installation and temperature sensor can be prevented in work by thermal insulation layer by using above-mentioned technical proposal
It is influenced during work by the meteorological condition simulated in icing wind tunnel test section and generates failure.
In conclusion the invention has the following advantages: by icing wind tunnel test section, convenient for simulating measurement wing
The climatic condition feature of segment model surface Anti-icing Heat Loads demand；It can be entire Anti-icing Heat Loads demand by power supply unit
Measuring system is powered；Wing segment model surface is heated by the electric calorifie installation in measuring unit, is able to maintain that
The anti-icing predetermined temperature in wing segment model surface；Incude the electric heating for being covered in wing segment model surface in real time by temperature sensor
The heating temperature of device, then the temperature information sensed is transferred to controller by temperature sensor；Controller is receiving temperature
Degree sensor sensing to temperature information after the temperature information is analyzed and processed, and judge whether the temperature information reaches anti-
The only temperature range that wing segment model surface freezes；If the temperature information is not within the scope of predetermined temperature, controller according to
The temperature information controls to adjust the heating power of electric calorifie installation, so that the heating temperature of electric calorifie installation reaches wing segment model
The temperature of surface Anti-icing Heat Loads demand；By power meter, can real-time measurement go out the heating power of electric calorifie installation, to pass through
The heating power of electric calorifie installation calculates the Anti-icing Heat Loads demand of wing segment model, to reach survey aircraft wing section surface
The purpose of Anti-icing Heat Loads demand.
Detailed description of the invention
Fig. 1 is the structural schematic diagram in the embodiment of the present invention；
Fig. 2 is the structural schematic diagram of wing segment model in the embodiment of the present invention；
Fig. 3 be in Fig. 2 along line A-A split after partial cross-sectional view；
Fig. 4 is the logic diagram in the embodiment of the present invention.
In figure: 1, icing wind tunnel test section；2, wing segment model；3, measuring unit；4, flexible electrothermal membrane；5, temperature sensing
Device；6, control unit；7, controller；8, power supply unit；9, power meter；10, data signal processor；11, data storage cell；
12, adjustable resistor；13, thermal insulation layer.
Specific embodiment
Below in conjunction with attached drawing 1-4, invention is further described in detail.
Embodiment: a kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system, as shown in Figure 1, Figure 2, Figure 3 and Figure 4, packet
Icing wind tunnel test section 1 and the wing segment model 2 in icing wind tunnel test section 1 are included, 2 surface of wing segment model pastes useful
In the measuring unit 3 of 2 Anti-icing Heat Loads demand information of measuring machine wing panel model.Measuring unit 3 includes for maintaining wing Duan Mo
The electric calorifie installation of 2 surface predetermined temperature of type and temperature sensor 5 for Induction Heating device heating temperature.Measuring unit 3 connects
It is connected to the control unit 6 of control electric calorifie installation heating power variation.Control unit 6 includes the control connecting with temperature sensor 5
Device 7 and power supply unit 8.Electric calorifie installation is connected with the power meter 9 of real-time measurement electric calorifie installation heating power.Electric calorifie installation, temperature
Sensor 5 and controller 7 are connect with power supply unit 8.
In the present embodiment, power supply unit 8 is AC power source.In icing wind tunnel test section 1, wing segment model 2 is carried out
When Anti-icing Heat Loads demand measures, the equipment opened the refrigeration equipment in icing wind tunnel test section 1 and manufacture air-flow and cloud and mist field,
To simulate the climatic condition feature of 2 surface Anti-icing Heat Loads demand of measuring machine wing panel model.It is whole by power supply unit 8
A Anti-icing Heat Loads demand measuring system is powered.Using the electric calorifie installation in measuring unit 3 to 2 surface of wing segment model into
Row heating, to be maintained the anti-icing predetermined temperature in 2 surface of wing segment model.By temperature sensor 5, induction is covered in real time
The heating temperature of the electric calorifie installation on 2 surface of wing segment model, then the temperature information sensed is transferred to control by temperature sensor 5
Device 7 processed.Controller 7 is analyzed and processed the temperature information after receiving the temperature information that temperature sensor 5 senses, and
Judge whether the temperature information reaches the temperature range for preventing 2 surface of wing segment model from freezing.If the temperature information is not predetermined
Within the temperature range of when, controller 7 according to the temperature information control to adjust electric calorifie installation heating power so that electric heating fill
The heating temperature set reaches the temperature of 2 surface Anti-icing Heat Loads demand of wing segment model.It, being capable of real-time measurement by power meter 9
The heating power of electric calorifie installation out, to calculate the Anti-icing Heat Loads of wing segment model 2 by the heating power meter 9 of electric calorifie installation
Demand, to achieve the purpose that survey aircraft wing section surface Anti-icing Heat Loads demand.
Controller 7 includes the data signal processor 10 connecting with temperature sensor 5 and connects with data signal processor 10
The data storage cell 11 connect.Controller 7 is connected with variable resistance.
In the present embodiment, the temperature information that the electric calorifie installation sensed heats is transferred to data letter by temperature sensor 5
Number processor 10, data signal processor 10 is after receiving the temperature information that temperature sensor 5 is experienced and to the temperature
Information is analyzed and processed.Then data signal processor 10 by the temperature information be stored in it is pre- in data storage cell 11
The temperature range that fixed Anti-icing Heat Loads need is compared and judges.If the temperature information is not in scheduled heating temperature range
When, data signal processor 10 controls adjustable resistor 12 according to the temperature information and works.Pass through the work of adjustable resistor 12
The adjusting of resistance is carried out, so that the size of the electric current in the circuit constituted to electric calorifie installation and power supply unit 8 is adjusted, thus
Power of the electric calorifie installation in operating circuit is adjusted, achievees the effect that the heating power for controlling electric calorifie installation.
The heating temperature of electric calorifie installation is 2~5 DEG C.
In the present embodiment, 2~5 DEG C are set by the heating temperature of electric calorifie installation, convenient for using the electricity of incomplete evaporation
The anti-icing mode of heat, guarantees that the heating temperature of electric calorifie installation is slightly above freezing point.
Electric calorifie installation is the flexible electrothermal membrane 4 for not influencing 2 surface flow state of wing segment model.Temperature sensor 5 be with
The membrane type temperature sensor 5 that flexible electrothermal membrane 4 connects, and temperature sensor 5 is that multiple intervals are covered in 4 table of flexible electrothermal membrane
Face.Flexible electrothermal membrane 4 is detachably pasted along 2 surface of Zhan Xiangyu wing segment model on 2 surface of wing segment model by bonding mode.
In the present embodiment, temperature sensor 5 is the model temperature sensing that three intervals are covered in 4 surface of flexible electrothermal membrane
Device 5.It is covered in the temperature sensor 5 on 4 surface of flexible electrothermal membrane, by multiple intervals convenient for integrated sensor cable flexible electrothermal membrane 4
Heating temperature, to improve the precision that temperature sensor 5 incudes the heating temperature of flexible electrothermal membrane 4.Pass through flexible electrothermal membrane 4
Detachably it is glued along 2 surface of Zhan Xiangyu wing segment model on 2 surface of wing segment model, so that flexible electrothermal membrane 4 and wing section
The flow regime on 2 surface of wing segment model is not influenced after the connection of 2 surface of model.Meanwhile flexible electrothermal membrane 4 and wing segment model 2
Surface is detachably connected by way of splicing, is easily installed with replacement flexible electrothermal membrane 4 to 2 surface difference position of wing segment model
Set the measurement for carrying out Anti-icing Heat Loads demand.
Flexible electrothermal membrane 4 is graphene material.
In the present embodiment, the flexible electrothermal membrane 4 made of graphene material, convenient for improving electric calorifie installation to wing section
The stability of the heating power on 2 surface of model.
Electric calorifie installation, temperature sensor 5, power supply unit 8 and controller 7 constitute temperature and control degeneration factor.
In the present embodiment, temperature control is constituted by electric calorifie installation, temperature sensor 5, power supply unit 8 and controller 7
Degeneration factor passes through controller convenient for the temperature information experienced according to the heating temperature of electric calorifie installation and temperature sensor 5
The heating power of 7 automatic controlled electric heating devices.When the heating power of electric calorifie installation is more than Anti-icing Heat Loads demand temperature, control
The heating power that device 7 controls to adjust electric calorifie installation reduces, so that the heating temperature of electric calorifie installation reduces.When electric calorifie installation
When heating power is lower than Anti-icing Heat Loads demand temperature, the heating power that controller 7 controls to adjust electric calorifie installation increases, to make
The heating temperature for obtaining electric calorifie installation becomes larger, so that the heating temperature of electric calorifie installation can be stably maintained at wing segment model 2
In the heating temperature range of surface Anti-icing Heat Loads demand.
Temperature sensor 5 and electric calorifie installation surface are coated with thermal insulation layer 13.
In the present embodiment, by thermal insulation layer 13, electric calorifie installation and temperature sensor 5 can be prevented in the course of work
In influenced by the meteorological condition simulated in icing wind tunnel test section 1 and generate failure.
Working principle: it is opened when carrying out the measurement of Anti-icing Heat Loads demand to wing segment model 2 in icing wind tunnel test section 1
The equipment of refrigeration equipment and manufacture air-flow and cloud and mist field in icing wind tunnel test section 1, to simulate measuring machine wing panel model 2
The climatic condition feature of surface Anti-icing Heat Loads demand.By power supply unit 8, convenient for being for the measurement of entire Anti-icing Heat Loads demand
System is powered.2 surface of wing segment model is heated using the electric calorifie installation in measuring unit 3, to be maintained wing
The anti-icing predetermined temperature in 2 surface of segment model.The electric heating on 2 surface of wing segment model is covered in by the induction in real time of temperature sensor 5
The heating temperature of device, then the temperature information sensed is transferred to controller 7 by temperature sensor 5.Controller 7 is receiving
The temperature information is analyzed and processed after the temperature information that temperature sensor 5 senses, and judges whether the temperature information reaches
To the temperature range for preventing 2 surface of wing segment model from freezing.If the temperature information is not within the scope of predetermined temperature, controller
7 control to adjust the heating power of electric calorifie installation according to the temperature information, so that the heating temperature of electric calorifie installation reaches wing
The temperature of 2 surface Anti-icing Heat Loads demand of segment model.By power meter 9, can real-time measurement go out the heating power of electric calorifie installation,
To calculate the Anti-icing Heat Loads demand of wing segment model 2 by the heating power meter 9 of electric calorifie installation, to reach survey aircraft
The purpose of wing section surface Anti-icing Heat Loads demand.
This specific embodiment is only explanation of the invention, is not limitation of the present invention, those skilled in the art
Member can according to need the modification that not creative contribution is made to the present embodiment after reading this specification, but as long as at this
All by the protection of Patent Law in the scope of the claims of invention.
Claims (7)
1. a kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system, including icing wind tunnel test section (1) and it is located at icing wind
Wing segment model (2) in hole test section (1), it is characterized in that: the wing segment model (2) surface is covered with for measuring wing
The measuring unit (3) of segment model (2) Anti-icing Heat Loads demand information；The measuring unit (3) includes for maintaining wing Duan Mo
The electric calorifie installation of type (2) surface predetermined temperature and temperature sensor (5) for Induction Heating device heating temperature；The measurement
Unit (3) is connected with the control unit (6) of control electric calorifie installation heating power variation；Described control unit (6) includes and temperature
The controller (7) and power supply unit (8) of sensor (5) connection；The electric calorifie installation is connected with the heating of real-time measurement electric calorifie installation
The power meter (9) of power；The electric calorifie installation, temperature sensor (5) and controller (7) are connect with power supply unit (8).
2. a kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system according to claim 1, it is characterized in that: the control
Device (7) processed includes the data signal processor (10) connecting with temperature sensor (5) and connect with data signal processor (10)
Data storage cell (11)；The controller (7) is connected with variable resistance.
3. a kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system according to claim 1, it is characterized in that: the electricity
The scheduled heating temperature of thermal is 2~5 DEG C.
4. a kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system according to claim 1, it is characterized in that: the electricity
Hot charging is set to the flexible electrothermal membrane (4) for not influencing wing segment model (2) surface flow state；The temperature sensor (5) be with
The membrane type temperature sensor of flexible electrothermal membrane (4) surface connection, and the temperature sensor (5) is that multiple intervals are covered in flexibility
Electric radiant Heating Film (4) surface；The flexible electrothermal membrane (4) is logical along Zhan Xiangyu wing segment model (2) surface on wing segment model (2) surface
Bonding mode is crossed detachably to paste.
5. a kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system according to claim 4, it is characterized in that: described soft
Property Electric radiant Heating Film (4) be graphene material.
6. a kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system according to claim 5, it is characterized in that: described soft
Property Electric radiant Heating Film (4), temperature sensor (5), power supply unit (8) and controller (7) constitute temperature and control degeneration factor.
7. a kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system according to claim 6, it is characterized in that: the temperature
Degree sensor (5) and flexible electrothermal membrane (4) surface is coated with thermal insulation layer (13).
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN113884219A (en) * | 2021-12-06 | 2022-01-04 | 中国空气动力研究与发展中心低速空气动力研究所 | Surface temperature measuring device and measuring method |
| CN113984325A (en) * | 2021-10-11 | 2022-01-28 | 南京航空航天大学 | Device and method for improving total pressure of incoming flow of hypersonic static wind tunnel |
| CN114034459A (en) * | 2022-01-10 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-icing and deicing test temperature control method and system |
| CN114199503A (en) * | 2021-12-23 | 2022-03-18 | 中国航空工业集团公司沈阳空气动力研究所 | Test model for testing anti-icing and deicing effects of super-hydrophobic material |
| CN114516403A (en) * | 2022-03-07 | 2022-05-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Power control method of electric heating ice prevention and removal system based on optical fiber icing detection |
| CN116644258A (en) * | 2023-07-19 | 2023-08-25 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-icing heat load calculation method and system |
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| 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 |
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| CN114034459A (en) * | 2022-01-10 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-icing and deicing test temperature control method and system |
| CN114516403A (en) * | 2022-03-07 | 2022-05-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Power control method of electric heating ice prevention and removal system based on optical fiber icing detection |
| CN114516403B (en) * | 2022-03-07 | 2023-05-05 | 中国空气动力研究与发展中心低速空气动力研究所 | Power control method of electrothermal ice prevention and removal system based on optical fiber icing detection |
| CN116644258A (en) * | 2023-07-19 | 2023-08-25 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-icing heat load calculation method and system |
| CN116644258B (en) * | 2023-07-19 | 2023-12-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-icing heat load calculation method and system |
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