CN114071853A - Wing plasma stall prevention/anti-icing/deicing bimodal switching system and working method - Google Patents
Wing plasma stall prevention/anti-icing/deicing bimodal switching system and working method Download PDFInfo
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- CN114071853A CN114071853A CN202111462898.0A CN202111462898A CN114071853A CN 114071853 A CN114071853 A CN 114071853A CN 202111462898 A CN202111462898 A CN 202111462898A CN 114071853 A CN114071853 A CN 114071853A
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- 230000002902 bimodal effect Effects 0.000 title claims abstract description 13
- 238000000034 method Methods 0.000 title claims abstract description 9
- 230000002265 prevention Effects 0.000 title abstract description 10
- 210000002381 plasma Anatomy 0.000 claims description 72
- 239000012790 adhesive layer Substances 0.000 claims description 8
- 230000004888 barrier function Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
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- 230000006866 deterioration Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H1/00—Generating plasma; Handling plasma
- H05H1/24—Generating plasma
- H05H1/2406—Generating plasma using dielectric barrier discharges, i.e. with a dielectric interposed between the electrodes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
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Abstract
The plasma generator with multiple groups of electrodes comprises multiple high-voltage electrodes, a grounding electrode, an insulating dielectric plate, an upper surface connecting circuit and a lower surface connecting circuit. The wing plasma anti-stall/anti-icing bimodal switching system comprises the multi-group electrode plasma generating device, a high-voltage power supply, a first electromagnetic relay, an icing sensor, an anti-icing controller, a second electromagnetic relay, a flight attack angle sensor and an anti-stall controller. And thus provides a plasma anti-stall/anti-icing bimodal working method. The plasma stall prevention/anti-icing bimodal switching system can monitor the attitude of an airplane and the icing state of the surface of a wing at the same time; by adjusting the number of working groups of the electrodes of the plasma exciter, the system can realize the switching of flow control and anti-icing functions; the automatic switching circuit has reliable work and low power consumption.
Description
Technical Field
The invention relates to the technical field of plasma, in particular to a plasma stall prevention/anti-icing bimodal switching system and a working method.
Background
When the airplane flies at a large attack angle, the incoming flow and the surface of the wing are easy to flow and separate, the lift force of the airplane is obviously reduced, the flight resistance is increased, a new thought is provided for inhibiting flow separation and an active flow control method, and the surface dielectric barrier discharge plasma is mature in application in the flow control field because of rapid response, low power consumption and easy arrangement of a generating device. Except flow separation, the phenomenon of icing of the wings of the airplane cannot be ignored, the ice accumulated on the surfaces can cause the reduction of lift-drag ratio, the deterioration of maneuverability and the steep increase of flying weight, the flying safety is seriously threatened, and the application effect of the discharge plasma on preventing and removing the ice of the wings is obvious due to the quick heating effect.
The plasma generating device widely adopted at present is a surface dielectric barrier discharge structure, and comprises a high-voltage electrode, a grounding electrode and an interlayer insulating barrier dielectric, wherein the high-voltage electrode and the grounding electrode are asymmetrically distributed and arranged on the front surface and the back surface of the insulating dielectric. When the high-voltage electrode is connected with a sine wave or nanosecond pulse power supply, a purple plasma which can be observed by naked eyes is formed at the edge of the high-voltage electrode, and in order to prevent discharge at one side of the grounding electrode, the back surface of the insulating medium is usually covered with a layer of insulating medium. In order to enlarge the control area of plasma for preventing and removing ice, a mode of a plurality of groups of electrodes is usually adopted to enlarge the discharge area of plasma, and the plasma flow control only needs to arrange a group of electrodes at the front edge part of the surface of the wing. Because the flow control and the deicing have coincidence in the surface area of the wing, the design of the plasma generating device with the double functions of stall prevention and deicing has important significance.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a multi-group electrode plasma generating device, which comprises a first high-voltage electrode 101, a second high-voltage electrode 102, an Nth high-voltage electrode N of …, a grounding electrode 108, an insulating dielectric plate 109, an upper surface connecting circuit 110 and a lower surface connecting circuit 111; wherein
The high-voltage electrode is a strip-shaped thin plate; the plurality of high-voltage electrodes are uniformly distributed on the upper surface of the insulating dielectric plate 109, the plurality of high-voltage electrodes are arranged in parallel and at equal intervals, and two ends of the plurality of high-voltage electrodes are basically flush; the left and right opposite sides of the high-voltage electrode and the insulating dielectric plate 109 are parallel to each other, and the two outermost high-voltage electrodes (the first high-voltage electrode 101 and the second high-voltage electrode 102) keep a substantially equal distance from the two opposite sides of the insulating dielectric plate 109; the upper surface connecting circuit 110 is divided into two parts, the left part of which is connected with one end of the first high-voltage electrode 101 and led out to the left edge of the insulating dielectric plate 109; the right side part of the insulating dielectric plate is connected with the connecting ends of the high-voltage electrodes 102 and …, which are different from the first high-voltage electrode 101, of the Nth high-voltage electrode N, and is led out to the right edge of the insulating dielectric plate 109;
the grounding electrode 108 is arranged on the lower surface of the insulating medium plate 109, a plurality of groups of electrode plasma generating devices are rotated by 180 degrees around the front edge of the insulating medium plate 109, from the angle, the projection of the left edge of the grounding electrode 108 on the horizontal plane is overlapped with the right edge of the first high-voltage electrode 101, the projection of the right edge of the grounding electrode 108 on the horizontal plane is positioned on the right side of the right edge of the Nth high-voltage electrode N, and the right edge of the grounding electrode 108 keeps a certain distance with the right edge of the insulating medium plate 109; the lower surface connection circuit 111 is led out from the left side edge of the ground electrode 108 to extend to the left side edge of the insulating dielectric sheet 109;
the double-sided insulating tape 112 is arranged on the lower surface of the plasma generating device, and the arrangement range of the insulating tape 112 completely coincides with the insulating dielectric plate 109 and does not extend to the side surface of the insulating dielectric plate 109.
An adhesive layer 112 is arranged on the lower surface of the plasma generating device, the arrangement range of the adhesive layer 112 completely coincides with the insulating medium plate 109 and does not extend to the side surface of the insulating medium plate 109, the upper surface of the adhesive layer 112 is adhered to the lower surface of the grounding electrode 108, and the adhesive layer 112 completely covers the lower surface of the insulating medium plate 109. .
In one embodiment of the invention, the right edge of the ground electrode 108 is 10-20mm from the right edge of the dielectric sheet 109.
In one embodiment of the present invention, the right edge of the ground electrode 108 is 15mm from the right edge of the insulating dielectric sheet 109; and a fillet is formed around the high-voltage electrode.
Also provides a wing plasma anti-stall/anti-icing dual-mode switching system, which comprises the multi-group electrode plasma generating device 1, a high-voltage power supply 2, a first electromagnetic relay 3, an icing sensor 8, an anti-icing controller 4, a second electromagnetic relay 5, a flight attack angle sensor 6 and an anti-stall controller 7, which are all in the technical scheme as claimed in any one of claims 1 to 3; wherein
A high-voltage wire led out from the output end of the high-voltage power supply 2 is respectively connected with the normally closed antennae of the first electromagnetic relay 3 and the second electromagnetic relay 5, and the negative end of the high-voltage power supply 2 is grounded; the flight angle of attack sensor 6 controls the second electromagnetic relay 5 through the anti-stall controller 7 alone, and the icing sensor 4 controls the first electromagnetic relay 3 and the second electromagnetic relay 5 through the anti-icing and anti-icing controller 4 at the same time; the anti-stall controller 7 and the anti-icing and deicing controller 4 both comprise a single chip microcomputer and a driving circuit, the single chip microcomputer of the anti-stall controller 7 is used for reading flight angle of attack parameters from the flight angle of attack sensor 6, the single chip microcomputer of the anti-icing and deicing controller 4 is used for reading icing signals from the icing sensor 8, the single chip microcomputer controls the driving circuit, and the driving circuit is used for controlling the on-off of the first electromagnetic relay 3 and the second electromagnetic relay 5; the first high-voltage electrode 101 of the multi-group electrode plasma generating device 1 is connected with a normally open antenna of the second electromagnetic relay 5 through the left part of the upper surface connecting circuit 110 and a lead; the high voltage electrode 102, … nth high voltage electrode N is connected to the normally open antenna of the first electromagnetic relay 3 through the right side portion of the upper surface connection circuit 110 and a wire.
In one embodiment of the present invention, the first electromagnetic relay 3 and the second electromagnetic relay 5 use a switching contact type relay.
In addition, a plasma anti-stall/anti-icing dual-mode working method is further provided, which is based on the wing plasma anti-stall/anti-icing dual-mode switching system as claimed in claim 4 or 5, and comprises the following specific steps:
when the aircraft flight angle of attack sensor 6 monitors that the angle of attack exceeds a set range, a single chip microcomputer in the anti-stall controller 7 reads a signal from the aircraft flight angle of attack sensor 6, a driving circuit is controlled to boost the voltage, the driving circuit enables a power supply VCC in the second electromagnetic relay 5 to be switched on, an antenna is switched from a normally closed state to a normally open state, the output end of the high-voltage power supply 2 is connected with the first high-voltage electrode 101, only one group of discharge plasmas appears in a discharge plasma area 901 at the moment and appears at the right edge of the first high-voltage electrode 101 and is used for controlling the plasma flow of the aircraft wing; when the flying angle of attack of the airplane returns to the set range, a single chip microcomputer in the anti-stall controller 7 reads a signal from the flying angle of attack sensor 6 of the airplane, a driving circuit is controlled to reduce the voltage, the driving circuit enables a power supply VCC in the second electromagnetic relay 5 to be disconnected, and the antenna returns to the initial normally closed state from the normally open state;
when the aircraft icing sensor 8 monitors that the ice accretion occurs on the wing, a singlechip in the anti-icing controller 4 reads a signal from the aircraft icing sensor 8, a driving circuit is controlled to boost the voltage, the driving circuit enables the power VCC in the first electromagnetic relay 3 and the second electromagnetic relay 5 to be simultaneously switched on, the antennae in the first electromagnetic relay 3 and the second electromagnetic relay 5 are simultaneously switched from a normally closed state to a normally open state, the output end of the high-voltage power supply 2 is connected with all high-voltage electrodes, and at the moment, a plurality of groups of discharge plasma regions (901, 902, 903, 904, 905, 906, 907, 908, 909, 910, 911, 912 and 913) occur to generate large-range discharge plasma for controlling the anti-icing of the wing; when the aircraft icing sensor 8 monitors that no ice is accumulated, the single chip microcomputer in the anti-stall controller 7 reads a signal from the aircraft icing sensor 8, a driving circuit is controlled to reduce the voltage, the driving circuit enables the power VCC in the first electromagnetic relay 3 and the second electromagnetic relay 5 to be disconnected, and the antenna returns to the initial normally closed state from the normally open state.
Compared with a single-group electrode dielectric barrier discharge plasma exciter, the system and the method of the invention can not meet the requirement of ice prevention and removal, and the multi-group electrode dielectric barrier discharge plasma exciter has the defect of large power consumption after being applied to flow control, and has the following advantages: the plasma anti-stall/anti-icing dual-mode switching system can monitor the attitude of the airplane and the icing state of the surface of the wing at the same time; by adjusting the number of working groups of the electrodes of the plasma exciter, the system can realize the switching of flow control and anti-icing functions; the automatic switching circuit has reliable work and low power consumption.
Drawings
FIG. 1 shows a side view of a multiple electrode plasma generating device;
FIG. 2 shows a high voltage electrode distribution diagram of a multi-electrode plasma generator;
FIG. 3 shows a ground electrode distribution diagram of a multi-electrode plasma generator;
FIG. 4 shows a bottom rubberizing pattern of a multi-electrode plasma generating device;
FIG. 5 shows a wing plasma stall prevention/ice control bimodal switching system component structure;
FIG. 6 illustrates a plasma flow control mode operation;
fig. 7 shows the working state of the plasma deicing prevention mode.
Detailed Description
The present invention will be further described with reference to the following drawings and examples, which include, but are not limited to, the following examples.
In an embodiment of the present invention, a plasma stall prevention/anti-icing dual-mode switching system, as shown in fig. 1, includes a first high voltage electrode 101, a second high voltage electrode 102, a third high voltage electrode 103, a fourth high voltage electrode 104, a fifth high voltage electrode 105, a sixth high voltage electrode 106, and a seventh high voltage electrode 107, a ground electrode 108, an insulating dielectric plate 109, an upper surface connection circuit 110, and a lower surface connection circuit 111. The number of the high-voltage electrodes is determined according to the area required by the aircraft wing anti-icing, the number of the electrode groups required to be covered by different types of aircraft is different, and can be 10, 20 or even 40, and the like, and the 7 high-voltage electrodes are only one example of the invention.
Fig. 2 shows the distribution of high voltage electrodes in the multi-electrode plasma generator. The high-voltage electrode is a strip-shaped thin plate, and in order to avoid point discharge and prolong the service life of the insulating medium, round corners are led around the high-voltage electrode. The plurality of high-voltage electrodes are uniformly distributed on the upper surface of the insulating dielectric plate 109, the plurality of high-voltage electrodes are arranged in parallel and at equal intervals, and two ends of the plurality of high-voltage electrodes are basically flush; the high-voltage electrodes are parallel to the left and right opposite sides of the insulating dielectric plate 109, and the two outermost high-voltage electrodes are spaced from the two opposite sides of the insulating dielectric plate 109 at substantially the same distance. The upper surface connecting circuit 110 is divided into two parts, the left part of which is connected with one end of the high-voltage electrode 101 and led out to the left edge of the insulating dielectric plate 109; the right side part of the insulating dielectric plate is connected with the connecting ends of the high-voltage electrode 102, the high-voltage electrode 103, the high-voltage electrode 104, the high-voltage electrode 105, the high-voltage electrode 106 and the high-voltage electrode 107 which are different from the high-voltage electrode 101, and is led out to the right edge of the insulating dielectric plate 109.
Fig. 3 shows the arrangement of the ground electrodes of the multiple electrode plasma generating devices, the ground electrodes 108 are arranged on the lower surface of the insulating medium plate 109, and fig. 3 shows the arrangement of the ground electrodes 108 on the back surface of the insulating medium 110 obtained by rotating the multiple electrode plasma generating devices in fig. 2 by 180 degrees around the front edge of the insulating medium plate 109. The projection of the left edge of the grounding electrode 108 on the horizontal plane is superposed with the right edge of the high-voltage electrode 101, and the projection of the right edge of the grounding electrode 108 on the horizontal plane is positioned at the right side of the right edge of the high-voltage electrode 107 and is 10-20mm, preferably 15mm away from the right edge of the insulating dielectric plate 109. The lower surface connection circuit 111 is led out from approximately the middle of the left edge of the ground electrode 108 to the left edge of the insulating dielectric sheet 109.
Fig. 4 shows a bottom adhesive coating diagram of a multi-electrode plasma generation device, in order to prevent discharge at the edge of a back electrode and achieve close fit with an airplane wing, a double-sided insulating tape 112 is arranged on the lower surface of the plasma generation device, and the arrangement range of the insulating tape 112 completely coincides with the insulating dielectric plate 109 and does not extend to the side surface of the insulating dielectric plate 109.
Fig. 5 shows a wing plasma stall-prevention/deicing dual-mode switching system composition structure, which comprises a multi-electrode plasma generating device 1, a high-voltage power supply 2, a first electromagnetic relay 3, an icing sensor 8, an deicing controller 4, a second electromagnetic relay 5, a flight angle-of-attack sensor 6 and an anti-stall controller 7. And a high-voltage wire led out from the output end of the high-voltage power supply 2 is respectively connected with the normally closed feelers of the electromagnetic relay 3 and the electromagnetic relay 5, and the negative end of the high-voltage power supply 2 is grounded. The attack angle sensor 6 controls the second electromagnetic relay 5 through the anti-stall controller 7 alone, and the icing sensor 4 controls the first electromagnetic relay 3 and the second electromagnetic relay 5 through the anti-icing controller 4 simultaneously. The anti-stall controller 7 and the anti-icing and deicing controller 4 both comprise a single chip microcomputer and a driving circuit, the single chip microcomputer of the anti-stall controller 7 is used for reading flight angle of attack parameters from the flight angle of attack sensor 6, the single chip microcomputer of the anti-icing and deicing controller 4 is used for reading icing signals from the icing sensor 8, the single chip microcomputer controls the driving circuit in turn, and the driving circuit is used for controlling the on-off of the first electromagnetic relay 3 and the second electromagnetic relay 5. The first high-voltage electrode 101 of the multi-group electrode plasma generating device 1 is connected with a normally open antenna of the second electromagnetic relay 5 through the left part of the upper surface connecting circuit 110; the high voltage electrode 102, the high voltage electrode 103, the high voltage electrode 104, the high voltage electrode 105, the high voltage electrode 106, and the high voltage electrode 107 are connected to the normally open antenna of the first electromagnetic relay 3 through the right side portion of the upper surface connection circuit 110. In one embodiment of the present invention, the first electromagnetic relay 3 and the second electromagnetic relay 5 use a switching contact type relay.
Based on the plasma anti-stall/anti-icing/deicing bimodal switching system, the invention also provides a plasma anti-stall/anti-icing bimodal working method, which comprises the following steps:
when the aircraft flight angle of attack sensor 6 monitors that the angle of attack exceeds a set range, a single chip microcomputer in the anti-stall controller 7 reads a signal from the aircraft flight angle of attack sensor 6, a driving circuit is controlled to boost the voltage, the driving circuit enables a power supply VCC in the second electromagnetic relay 5 to be switched on, the antenna is switched from a normally closed state to a normally open state, the output end of the high-voltage power supply 2 is connected with the first high-voltage electrode 101, only one group of discharge plasmas appears in a discharge plasma region 901 at the moment and appears at the right edge of the first high-voltage electrode 101 for controlling the plasma flow of the aircraft wing, and the working mode is shown in fig. 6; when the aircraft flight angle of attack returns to the set range, the single chip microcomputer in the anti-stall controller 7 reads a signal from the aircraft flight angle of attack sensor 6, the driving circuit is controlled to reduce the voltage, the driving circuit enables the power supply VCC in the second electromagnetic relay 5 to be disconnected, and the antenna returns to the initial normally closed state from the normally open state.
When the aircraft icing sensor 8 monitors that the ice accretion occurs on the wing, a single chip microcomputer in the anti-icing controller 4 reads a signal from the aircraft icing sensor 8, a driving circuit is controlled to boost the voltage, the driving circuit enables power supplies VCC in the first electromagnetic relay 3 and the second electromagnetic relay 5 to be simultaneously switched on, antennae in the first electromagnetic relay 3 and the second electromagnetic relay 5 are simultaneously switched from a normally closed state to a normally open state, the output end of the high-voltage power supply 2 is connected with all high-voltage electrodes, at the moment, a plurality of groups of discharge plasma regions (901, 902, 903, 904, 905, 906, 907, 908, 909, 910, 911, 912 and 913) occur, and large-range discharge plasmas are generated and are used for controlling the anti-icing of the wing, and the working mode of the anti-icing controller is shown in fig. 7. When the aircraft icing sensor 8 monitors that no ice is accumulated, a single chip microcomputer in the anti-icing controller 7 reads a signal from the aircraft icing sensor 8, a driving circuit is controlled to reduce the voltage, the driving circuit enables a power supply VCC in the first electromagnetic relay 3 and the second electromagnetic relay 5 to be disconnected, and the antenna returns to an initial normally closed state from a normally open state.
The plasma anti-stall anti-icing and deicing bimodal switching system has the following advantages:
1. the plasma flow control/anti-stall bimodal switching system can simultaneously monitor the aircraft attitude and the icing state of the wing surface;
2. by adjusting the number of working groups of the electrodes of the plasma exciter, the system can realize intelligent switching on stall prevention and anti-icing functions;
3. the automatic switching circuit has reliable work and low power consumption.
Claims (7)
1. The multi-electrode plasma generating device is characterized by comprising a first high-voltage electrode (101), a second high-voltage electrode (102), an … Nth high-voltage electrode (N), a grounding electrode (108), an insulating dielectric plate (109), an upper surface connecting circuit (110) and a lower surface connecting circuit (111); wherein
The high-voltage electrode is a strip-shaped thin plate; the high-voltage electrodes are uniformly distributed on the upper surface of the insulating dielectric plate (109), the high-voltage electrodes are arranged in parallel at equal intervals, and two ends of the high-voltage electrodes are basically level; the left and right opposite sides of the high-voltage electrode and the insulating dielectric plate (109) are parallel to each other, and the two outermost high-voltage electrodes and the two opposite sides of the insulating dielectric plate (109) keep the same distance; the upper surface connecting circuit (110) is divided into two parts, the left part of the upper surface connecting circuit is connected with one end of the first high-voltage electrode (101) and is led out to the left edge of the insulating dielectric plate (109); the right side part of the insulating dielectric plate is connected with the connecting ends of the second high-voltage electrode (102) and the … Nth high-voltage electrode (N) which are different from the first high-voltage electrode (101), and is led out to the right edge of the insulating dielectric plate (109);
the grounding electrode (108) is arranged on the lower surface of the insulating medium plate (109), the multiple groups of electrode plasma generating devices are rotated by 180 degrees around the front edge of the insulating medium plate (109), from the angle, the projection of the left edge of the grounding electrode (108) on the horizontal plane is superposed with the right edge of the first high-voltage electrode (101), the projection of the right edge of the grounding electrode (108) on the horizontal plane is positioned on the right side of the right edge of the Nth high-voltage electrode (N), and the right edge of the grounding electrode (108) keeps a certain distance from the right edge of the insulating medium plate (109); the lower surface connection circuit (111) is led out from the left edge of the ground electrode (108) and extended to the left edge of the insulating dielectric sheet (109).
2. The plasma generator with multiple groups of electrodes as claimed in claim 1, wherein an adhesive layer (112) is arranged on the lower surface of the plasma generator, the arrangement range of the adhesive layer (112) is completely overlapped with the insulating medium plate (109) and does not extend to the side surface of the insulating medium plate (109), the upper surface of the adhesive layer (112) is adhered to the lower surface of the grounding electrode 108, and the adhesive layer (112) completely covers the lower surface of the insulating medium plate (109).
3. The plasma generator of claim 1, wherein the right edge of the ground electrode (108) is 10-20mm away from the right edge of the dielectric insulating sheet (109).
4. The plasma generating apparatus of claim 3, wherein the right edge of the ground electrode (108) is 15mm from the right edge of the insulating dielectric sheet (109); and a fillet is formed around the high-voltage electrode.
5. The wing plasma anti-stall/anti-icing dual-mode switching system is characterized by comprising a multi-group electrode plasma generating device (1) as claimed in any one of claims 1 to 3, a high-voltage power supply (2), a first electromagnetic relay (3), an icing sensor (8), an anti-icing controller (4), a second electromagnetic relay (5), a flight attack angle sensor (6) and an anti-stall controller (7); wherein
A high-voltage wire led out from the output end of the high-voltage power supply (2) is respectively connected with the normally closed feelers of the first electromagnetic relay (3) and the second electromagnetic relay (5), and the negative end of the high-voltage power supply (2) is grounded; the flight angle of attack sensor (6) controls the second electromagnetic relay (5) through the anti-stall controller (7) alone, and the icing sensor (4) controls the first electromagnetic relay (3) and the second electromagnetic relay (5) through the anti-icing controller (4) simultaneously; the anti-stall controller (7) and the anti-icing and deicing controller (4) both comprise a single chip microcomputer and a driving circuit, the single chip microcomputer of the anti-stall controller (7) is used for reading flight angle of attack parameters from the flight angle of attack sensor (6), the single chip microcomputer of the anti-icing and deicing controller (4) is used for reading icing signals from the icing sensor (8), the single chip microcomputer then controls the driving circuit, and the driving circuit is used for controlling the on-off of the first electromagnetic relay (3) and the second electromagnetic relay (5); a first high-voltage electrode (101) of the multi-group electrode plasma generating device (1) is connected with a normally open antenna of a second electromagnetic relay (5) through the left side part of an upper surface connecting circuit (110) and a lead; the high-voltage electrodes (102) and … are connected with the normally open antenna of the first electromagnetic relay (3) through the right part of the upper surface connecting circuit (110) and a lead.
6. The wing plasma anti-stall/anti-icing dual-mode switching system is characterized in that the first electromagnetic relay (3) and the second electromagnetic relay (5) are switched contact type relays.
7. A plasma anti-stall/anti-icing bimodal working method is based on the wing plasma anti-stall/anti-icing bimodal switching system as claimed in claim 4 or 5, and comprises the following specific steps:
when the aircraft flight angle of attack sensor (6) monitors that the angle of attack exceeds a set range, a single chip microcomputer in the anti-stall controller (7) reads a signal from the aircraft flight angle of attack sensor (6), a driving circuit is controlled to boost the voltage, the driving circuit enables a power supply VCC in the second electromagnetic relay (5) to be switched on, the antenna is switched from a normally closed state to a normally open state, the output end of the high-voltage power supply (2) is connected with the first high-voltage electrode (101), only one group of discharge plasmas appear in a discharge plasma region 901 at the time and appear at the right edge of the first high-voltage electrode (101) and are used for controlling the plasma flow of the aircraft wing; when the flying angle of attack of the airplane returns to the set range, a single chip microcomputer in the anti-stall controller (7) reads a signal from the flying angle of attack sensor (6) of the airplane, a driving circuit is controlled to reduce the voltage, the driving circuit enables a power supply VCC in the second electromagnetic relay (5) to be disconnected, and the antenna returns to the initial normally closed state from the normally open state;
when an aircraft icing sensor (8) monitors that ice accretion occurs on a wing, a singlechip in an anti-icing controller (4) reads a signal from the aircraft icing sensor (8), a driving circuit is controlled to boost the voltage, the driving circuit enables power VCC in a first electromagnetic relay (3) and a second electromagnetic relay (5) to be switched on simultaneously, antennae in the first electromagnetic relay (3) and the second electromagnetic relay (5) are switched from a normally closed state to a normally open state simultaneously, the output end of a high-voltage power supply (2) is connected with all high-voltage electrodes, and at the moment, a plurality of groups of discharge plasma regions (901, 902, 903, 904, 905, 906, 907, 908, 909, 910, 911, 912 and 913) occur to generate discharge plasma in a large range for controlling the ice accretion on the wing; when the aircraft icing sensor (8) monitors that no ice is accumulated, a single chip microcomputer in the anti-stall controller (7) reads a signal from the aircraft icing sensor (8), a driving circuit is controlled to reduce the voltage, the driving circuit enables a power supply VCC in the first electromagnetic relay (3) and the second electromagnetic relay (5) to be disconnected, and the antenna returns to an initial normally closed state from a normally open state.
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| CN202111462898.0A CN114071853B (en) | 2021-12-03 | 2021-12-03 | Wing plasma stall-preventing/ice-preventing dual-mode switching system and working method |
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| US20100127624A1 (en) * | 2007-05-08 | 2010-05-27 | University Of Florida Research Foundation ,Inc. | Method and Apparatus for Multibarrier Plasma Actuated High Performance Flow Control |
| US20100218896A1 (en) * | 2007-09-11 | 2010-09-02 | Atomic Energy Council - Institute Of Nuclear Energy Research | Atmospheric pressure plasma reactor |
| CN108545197A (en) * | 2018-05-03 | 2018-09-18 | 中国人民解放军空军工程大学 | The device and method for carrying out the anti-deicing of wing is encouraged using rf (discharge) plasma |
| EP3585136A1 (en) * | 2018-06-20 | 2019-12-25 | Masarykova Univerzita | A method and device for generating low-temperature electrical water-based plasma at near-atmospheric pressures and its use |
| CN111498089A (en) * | 2020-04-24 | 2020-08-07 | 南京理工大学 | Device and method for realizing aircraft flow control based on plasma exciter |
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2021
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| US20100127624A1 (en) * | 2007-05-08 | 2010-05-27 | University Of Florida Research Foundation ,Inc. | Method and Apparatus for Multibarrier Plasma Actuated High Performance Flow Control |
| US20100218896A1 (en) * | 2007-09-11 | 2010-09-02 | Atomic Energy Council - Institute Of Nuclear Energy Research | Atmospheric pressure plasma reactor |
| CN108545197A (en) * | 2018-05-03 | 2018-09-18 | 中国人民解放军空军工程大学 | The device and method for carrying out the anti-deicing of wing is encouraged using rf (discharge) plasma |
| EP3585136A1 (en) * | 2018-06-20 | 2019-12-25 | Masarykova Univerzita | A method and device for generating low-temperature electrical water-based plasma at near-atmospheric pressures and its use |
| CN111498089A (en) * | 2020-04-24 | 2020-08-07 | 南京理工大学 | Device and method for realizing aircraft flow control based on plasma exciter |
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