CN110834734A - Deicing system is prevented to wing - Google Patents
Deicing system is prevented to wing Download PDFInfo
- Publication number
- CN110834734A CN110834734A CN201911110539.1A CN201911110539A CN110834734A CN 110834734 A CN110834734 A CN 110834734A CN 201911110539 A CN201911110539 A CN 201911110539A CN 110834734 A CN110834734 A CN 110834734A
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- wing
- synthetic jet
- electric heating
- cavity
- vibrating diaphragm
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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
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- 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
Abstract
The invention discloses a wing ice preventing and removing system which comprises the following components: the aircraft wing comprises a wing, wherein an electric heating system is distributed in a front edge skin of the wing, the aircraft wing also comprises a synthetic jet actuator distributed in the wing, a synthetic jet outlet of the synthetic jet actuator is positioned on the surface of the wing and positioned at the rear side of an anti-icing area of the electric heating system, and synthetic jet in the synthetic jet actuator is sprayed out from the jet outlet and interacts with water drops on the surface of the wing to change the motion track of the water drops. The invention heats the surface of the wing leading edge through the electric heating system, so that the wing leading edge is kept in a certain temperature range, when supercooled water drops impact on the wing leading edge, the water drops can not freeze on the wing leading edge due to high surface temperature, but form a layer of water film to flow towards the rear of the wing, and when the water film flows to the synthetic jet outlet, the original movement track of the water film can be changed due to the action of the synthetic jet, so that the water film is far away from the rear surface of the wing, the formation of overflow ice is prevented, and the aerodynamic performance and the safety performance of the wing are improved.
Description
Technical Field
The invention belongs to the technical field of aircraft ice prevention, and particularly relates to an anti-icing and deicing system for a wing.
Background
When an airplane flies in a cloud layer containing supercooled water drops, the surfaces of the parts of the airplane, such as wings, empennages, rotors, air inlet channels, antenna covers, instrument sensors and the like, are easy to freeze. The icing of the airplane not only increases the weight of the airplane, but also damages the aerodynamic appearance of the surface of the airplane and changes the streaming flow field, so that the maximum lift-drag ratio of the airplane is reduced, the stalling attack angle is reduced, the operability and stability of the airplane are influenced, and even safety accidents can be caused in severe cases.
The existing anti-icing technology mainly comprises hot gas anti-icing, electric heating anti-icing, pneumatic belt deicing, liquid anti-icing and the like. The hot gas protection system needs an aircraft engine to provide a large amount of hot gas, and has complex pipelines and large energy consumption, and can bring certain influence on the performance of the engine; the pneumatic belt deicing system can damage the pneumatic appearance of the airplane, increase the flight resistance and also not completely deice; the liquid anti-icing system needs a large amount of onboard anti-icing liquid, has larger system weight and is less in application at present; the electric heating anti-icing system has the advantages of high reliability, light weight, easiness in automation realization and the like, has the anti-icing and deicing functions, and accords with the development trend of all-electric airplanes. However, long-term experiments show that when the electric heating anti-icing system is used for anti-icing the wings, if incomplete evaporation anti-icing is adopted, overflow ice is easily formed on the rear side of an anti-icing area in the anti-icing process, the aerodynamic characteristics of the wings are seriously affected by the overflow ice, and the flight safety of an airplane is seriously damaged; if the complete evaporation anti-icing is adopted or the electric heating module is arranged on the whole wing, the energy consumption is greatly increased, and the application of the electric heating system in the airplane anti-icing is not facilitated. Therefore, it is necessary to invent a simple, efficient and low-energy-consumption anti-icing method capable of realizing full coverage of the whole wing.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the wing anti-icing and deicing system is provided for solving the problems that overflow ice is easily formed on the rear side of a protection area in the anti-icing and deicing process of the existing anti-icing and deicing system, aerodynamic characteristics of wings are seriously influenced, and serious harm is caused to airplane safety.
In order to solve the problem, the technical scheme adopted by the invention is as follows:
an anti-icing and deicing system for a wing: the aircraft wing with the synthetic jet flow exciter comprises a wing, wherein an electric heating system for preventing and removing ice is arranged in a front edge skin of the wing, the aircraft wing with the synthetic jet flow exciter comprises a synthetic jet flow exciter arranged in the wing, a synthetic jet flow outlet of the synthetic jet flow exciter is positioned on the surface of the wing and positioned on the rear side of an ice prevention area of the electric heating system, and synthetic jet flow in the synthetic jet flow exciter interacts with water drops on the surface of the wing after being sprayed out from the jet flow outlet to change the motion track of the water drops.
Furthermore, the electric heating system comprises an electric heating film, the electric heating film is positioned inside the leading edge of the wing, and a synthetic jet outlet of the synthetic jet actuator is arranged on the rear side of an electric heating anti-icing area formed by the electric heating sheet.
Further, the electric heating film is positioned on the inner surface of the wing leading edge skin or in a sandwich layer between the skin and the inner surface.
Further, the temperature of the electric heating film is controlled by an input voltage and an energization time.
Furthermore, the synthetic jet actuator comprises a synthetic jet cavity, a vibration diaphragm, one or more jet outlets and a signal generator, wherein the vibration diaphragm is connected with the signal generator and periodically vibrates under the action of an electric signal output by the signal generator, the jet outlets are positioned on the surface of the wing, the vibration diaphragm is positioned in the synthetic jet cavity or is one surface of the synthetic jet cavity, and the synthetic jet outlets are arranged on any surface of the synthetic jet cavity except the vibration diaphragm.
Further, when the vibrating diaphragm is located in the synthetic jet cavity, the synthetic jet cavity is divided into two cavities by the vibrating diaphragm, and one or more jet outlets are respectively formed in the two divided cavities.
Furthermore, the synthetic jet cavity is surrounded by an inner surface of the wing, a vibrating diaphragm, a mounting plate for mounting the vibrating diaphragm on the synthetic jet cavity, and a connecting plate for connecting the mounting plate and the inner surface of the wing, and the synthetic jet outlet is formed in the surface of the wing.
Further, a portion of the electrically heated membrane is located at a surface of the synthetic jet cavity.
Further, when the electric heating film is positioned in a sandwich layer between the wing leading edge skin and the inner surface of the skin, or the heat is transferred into the synthetic jet cavity through the skin
Furthermore, the outlet of the cavity is a slit or a small hole which is arranged along the span direction of the machine.
Furthermore, one or more groups of synthetic jet actuators are arranged in the wing to form a synthetic jet actuator array arranged on one or two surfaces of the wing.
Compared with the prior art, the invention has the following beneficial effects:
according to the wing ice and ice preventing system, the surface of the leading edge of the wing is heated through the electric heating system, so that the leading edge of the wing is kept in a certain temperature range, and when super-cooled water drops impact on the leading edge of the wing, the water drops cannot freeze on the leading edge of the wing due to high surface temperature, and form a water film to flow towards the back of the wing. When the water film flows to the synthetic jet outlet, the water film changes the original motion track under the action of the synthetic jet, so that the water film is far away from the rear surface of the wing, and the formation of overflow ice is prevented. The invention has the advantages of high reliability, light weight and good anti-icing effect of electric heating by thermal coupling and no need of complex pipelines for the synthetic jet actuator, and can fully utilize the energy of the electric heating film to eliminate the overflow ice phenomenon in the electric heating anti-icing process, thereby achieving the purpose of full-coverage anti-icing of the whole wing, improving the pneumatic performance and the safety performance of the wing, and realizing full-coverage anti-icing of the wing under full electric control.
Drawings
FIG. 1 is an external schematic view of the electrical heating and synthetic jet coupled anti-icing method for an airfoil of the present invention;
FIG. 2 is a schematic representation of a section along a centerline of the electrical heating and synthetic jet coupled anti-icing method for an airfoil of FIG. 1 in accordance with the present invention;
FIG. 3 is a schematic diagram of the anti-icing principle of the invention by coupling electrical heating and synthetic jet.
Detailed Description
Fig. 1 to 3 show a specific embodiment of an anti-icing and deicing system for an airfoil according to the present invention, which includes an airfoil 1, an electrical heating system for anti-icing disposed inside a leading edge of the airfoil, and a synthetic jet actuator disposed inside the airfoil, wherein a jet outlet of the synthetic jet actuator is located on a surface of the airfoil and behind an electrical heating anti-icing region, and a jet in the synthetic jet actuator is ejected from the synthetic jet outlet and interacts with droplets on the surface of the airfoil to change a movement trajectory of the droplets. The embodiment heats the surface of the leading edge of the wing through the electric heating system, so that the leading edge of the wing is kept in a certain temperature range, when supercooled water drops impact on the leading edge of the wing, because the surface temperature is high, the water drops cannot freeze on the leading edge of the wing, but form a layer of water film to flow towards the rear of the wing, and the jet outlet of the synthetic jet actuator is arranged at the rear side of the electric heating system on the surface of the wing. Through thermal coupling, the invention not only has the advantages of high reliability, light weight and good anti-icing effect of electric heating anti-icing, but also can eliminate the ice overflow phenomenon in the electric heating anti-icing process, achieve the purpose of whole wing full-coverage anti-icing, improve the aerodynamic performance and safety performance of the wing, and realize full-coverage anti-icing of the wing under full electric control.
In this embodiment, the electric heating system includes an electric heating film 3, the electric heating film 3 is located on the inner surface of the skin at the front edge of the wing or in the interlayer between the skin and the inner surface, and is used for heating the front edge of the wing in an icing weather environment, the temperature of the electric heating film 3 is controlled by input voltage and energization time, and the outlet 2 of the synthetic jet actuator is distributed on the rear side of the electric heating film 3. The method is characterized in that the temperature of the surface of the front edge of the wing 1 is controlled by controlling the voltage, the current and the electrifying time of an electric heating system, so that the aim of preventing the front edge of the wing from being iced is fulfilled, the outlet 2 of a synthetic jet actuator is distributed to the rear side of an electric heating film 3, when supercooled water drops impact on the front edge of the wing, because the surface temperature is high, the water drops cannot be iced on the front edge of the wing, but a layer of water film flows towards the rear of the wing, the synthetic jet is sprayed out from the outlet 2 of the synthetic jet actuator, the motion track of the water film formed on the surface of the front edge of the wing is changed, the attachment amount of the water drops on the rear surface of.
In this embodiment, the synthetic jet actuator includes a synthetic jet cavity 6, a vibrating diaphragm 5, a signal generator, and one or more cavity outlets 2, where the cavity outlets 2 are located on the surface of the wing to form jet outlets, and the vibrating diaphragm 5 is connected to the signal generator to receive an electrical signal from the signal generator to realize periodic motion. The synthetic jet actuator is positioned in the wing, the synthetic jet cavity 6 can be a cavity which is arbitrarily surrounded by a vibrating diaphragm 5 and a mounting plate 4 which fixes the vibrating diaphragm 5 on the synthetic jet cavity 6, the cavity outlet 2 is arranged on any surface except the vibrating diaphragm 5, the vibrating diaphragm 5 receives square waves, sine waves, sawtooth waves and other electrical signals generated by a signal generator to realize periodic up-and-down vibration, and gas in the synthetic jet cavity 6 is compressed and expanded back and forth by the vibrating diaphragm 5 to form synthetic jet which is ejected from the cavity outlet 2. In this embodiment, the vibrating diaphragm 5 may also be located in the synthetic jet cavity, dividing the cavity into two parts, and the two cavities separated by the vibrating diaphragm have one or more jet outlets 2, respectively. The velocity and frequency of the synthetic jet can be controlled by the vibrating diaphragm 5, and the amplitude and frequency of the vibration of the vibrating diaphragm 5 can be controlled by the input waveform and the voltage intensity.
In this embodiment, the synthetic jet cavity 6 is formed by enclosing an inner surface of a wing, a vibrating diaphragm 5, a mounting plate 4 and a connecting plate 7 connecting the mounting plate 4 and the inner surface of the wing, the vibrating diaphragm 5 is fixed on the mounting plate 4, the cavity outlets 2 are formed on the inner surface of the wing to form synthetic jet outlets, and one or more cavity outlets 2 may be formed on one synthetic jet cavity 6. In this embodiment, in order to concentrate the energy of the synthetic jet and make the synthetic jet reach a certain speed, the cavity outlet 2 is formed into a slit or a small hole along the span direction of the wing, so as to increase the speed of the jet, the width of the slit is generally 1-5 mm, the length of the slit is smaller than the length of the cavity on the inner surface of the wing, the length of the slit is set as required, and the diameter of the small hole is generally 1-5 mm. The inner surface of the wing is used as a part of the synthetic jet cavity 6, so that the surface composition of the synthetic jet cavity is reduced, the synthetic jet actuator has a simple structure, the weight of the synthetic jet actuator is reduced, and the effect of jetting jet can be achieved. The synthetic thermal jet actuator is fully electrically input, the temperature and the strength of jet flow are easily controlled through electrical parameters, an air source and a pipeline supply system are not needed, the structure is simple and light, the direction of a water film can be changed through ejected jet flow, and the formation of overflowing ice is prevented.
In this embodiment, a portion of the electrically heated membrane 3 is located on the surface of the synthetic jet cavity 6. Specifically, a part of the inner surface of the wing constitutes the surface of the synthetic jet cavity 6, and the surface is provided with the electric heating film 3, as shown in fig. 2, since the electric heating film can be located on the inner surface of the skin or between the skin and the inner surface, when the electric heating film 3 is located between the skin and the inner surface, the heat generated by the electric heating film is transferred into the synthetic jet cavity through the skin, and since the electric heating film 3 heats the gas in the synthetic jet cavity 6, the synthetic jet with a certain temperature is ejected from the synthetic jet outlet 2. Because the synthetic hot jet flow has a certain temperature, the rear surface of the wing can be heated in the backward flowing process, so that the rear surface is not easy to freeze, and the formation of overflow ice is further prevented.
In this embodiment, the synthetic jet actuators are arranged in the wing in one or more groups to form a synthetic jet actuator array arranged on one or both surfaces of the wing. One or more groups of synthetic jet actuators are arranged along the span-wise surface of the wing as required, or the synthetic jet actuators can be arranged on one surface or two surfaces of the wing as required. The invention adopts a heating and synthetic jet coupling anti-icing method, and can independently start an electric heating system to perform anti-icing under the condition of no overflow icing phenomenon. The velocity and frequency of the synthetic jet may also be controlled based on the intensity of the overflow ice.
The principle of ice prevention and removal provided by the invention is as shown in fig. 3, when an airplane encounters an icing meteorological environment, an ice prevention system starts to work, firstly, an electric heating system positioned at the front edge of the wing is started, an electric heating film is electrified to heat the surface of the front edge of the wing, so that the front edge of the wing is kept in a certain temperature range, and when supercooled water drops impact on the front edge of the wing, due to high surface temperature, the water drops can not be iced at the front edge of the wing, but form a layer of water film to flow towards the back of the wing. When overflow ice formation is detected, the synthetic jet system is turned on. When the water film flows to the synthetic jet outlet, the original motion trail of the water film can be changed due to the action of the synthetic jet, so that the water film is far away from the rear surface of the wing, meanwhile, due to the fact that the electric heating film heats the synthetic jet, the synthetic jet has a certain temperature, the rear surface of the wing can be heated in the backward flowing process, a layer of hot film is formed on the surface of the wing, the rear surface is not easy to freeze, and accordingly the whole wing can be prevented from being iced in a full coverage mode. In FIG. 3, there is also a comparison that the absence of the synthetic jet actuator outlet on the other surface of the airfoil, which forms overflow ice when it encounters supercooled water droplets, and the absence of overflow ice on the surface of the airfoil where the synthetic jet outlet is located, forms a thermal film on the airfoil surface, illustrating the good effectiveness of the invention in preventing overflow ice formation.
The invention is also suitable for preventing and removing ice on horizontal tails, vertical tails, rotor wings and the like of aircrafts.
The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above-mentioned embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may be made by those skilled in the art without departing from the principle of the invention.
Claims (10)
1. An anti-icing and deicing system for a wing: including the wing, the inside electric heating system who is used for anti-icing that has laid of wing leading edge, its characterized in that: the jet flow in the synthetic jet flow exciter is sprayed out from the synthetic jet flow outlet and interacts with water drops on the surface of the wing, so that the movement track of the water drops is changed.
2. The system according to claim 1, wherein: the electric heating system comprises an electric heating film, the electric heating film is positioned inside the front edge of the wing, and a synthetic jet outlet of the synthetic jet actuator is arranged on the rear side of an electric heating anti-icing area formed by the electric heating sheet.
3. The system according to claim 2, wherein: the electric heating film is positioned on the inner surface of the wing leading edge skin or in a sandwich layer between the skin and the inner surface.
4. A system according to claim 3, characterized in that: the temperature of the electric heating film is controlled by input voltage and energization time.
5. The system according to claim 1, wherein: the synthetic jet actuator comprises a synthetic jet cavity, a vibrating diaphragm, one or more jet outlets and a signal generator, wherein the vibrating diaphragm is connected with the signal generator and periodically vibrates under the action of an electric signal output by the signal generator, the vibrating diaphragm is positioned in the synthetic jet cavity or is a surface of the synthetic jet cavity, and the synthetic jet outlets are arranged on any surface of the synthetic jet cavity except the vibrating diaphragm.
6. The system according to claim 5, wherein: when the vibrating diaphragm is positioned in the synthetic jet cavity, the synthetic jet cavity is divided into two cavities by the vibrating diaphragm, and one or more jet outlets are respectively arranged on the two divided cavities.
7. The system according to claim 5, wherein: the synthetic jet cavity is formed by encircling an inner surface of the wing, a vibrating diaphragm, a mounting plate for mounting the vibrating diaphragm on the synthetic jet cavity and a connecting plate for connecting the mounting plate and the inner surface of the wing, and the synthetic jet outlet is formed in the surface of the wing.
8. The system according to claim 7, wherein: a portion of the electrically heated membrane is located at a surface of the synthetic jet cavity.
9. The system according to any one of claims 1 to 8, wherein: the synthetic jet flow outlet is a slit or a small hole which is arranged along the span direction of the machine.
10. The system according to claim 9, wherein: the synthetic jet actuators are arranged in one or more groups in the wing to form a synthetic jet actuator array arranged on one or two surfaces of the wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911110539.1A CN110834734A (en) | 2019-11-14 | 2019-11-14 | Deicing system is prevented to wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911110539.1A CN110834734A (en) | 2019-11-14 | 2019-11-14 | Deicing system is prevented to wing |
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| CN110834734A true CN110834734A (en) | 2020-02-25 |
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| CN201911110539.1A Pending CN110834734A (en) | 2019-11-14 | 2019-11-14 | Deicing system is prevented to wing |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111579199A (en) * | 2020-05-27 | 2020-08-25 | 中国空气动力研究与发展中心低速空气动力研究所 | Electromagnetic force deicing device for front edge ice hull of test model in icing wind tunnel |
| CN112629093A (en) * | 2021-03-09 | 2021-04-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for removing ice growing on surface of film hot knife and model |
| CN112977835A (en) * | 2021-05-11 | 2021-06-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-overflow device |
| CN113415428A (en) * | 2021-08-20 | 2021-09-21 | 中国空气动力研究与发展中心低速空气动力研究所 | Thermal foaming type impact force generator for deicing |
| CN113562182A (en) * | 2021-07-28 | 2021-10-29 | 中国商用飞机有限责任公司 | SLD environment leading edge overflow area ice protection assembly |
-
2019
- 2019-11-14 CN CN201911110539.1A patent/CN110834734A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111579199A (en) * | 2020-05-27 | 2020-08-25 | 中国空气动力研究与发展中心低速空气动力研究所 | Electromagnetic force deicing device for front edge ice hull of test model in icing wind tunnel |
| CN112629093A (en) * | 2021-03-09 | 2021-04-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for removing ice growing on surface of film hot knife and model |
| CN112977835A (en) * | 2021-05-11 | 2021-06-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-overflow device |
| CN112977835B (en) * | 2021-05-11 | 2021-08-03 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-overflow device |
| CN113562182A (en) * | 2021-07-28 | 2021-10-29 | 中国商用飞机有限责任公司 | SLD environment leading edge overflow area ice protection assembly |
| CN113415428A (en) * | 2021-08-20 | 2021-09-21 | 中国空气动力研究与发展中心低速空气动力研究所 | Thermal foaming type impact force generator for deicing |
| CN113415428B (en) * | 2021-08-20 | 2021-11-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Thermal foaming type impact force generator for deicing |
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