Anti-icing and de-icing device for helicopter propeller

Abstract

A helicopter propeller ice preventing and removing device comprises a pump, a flow dividing bin, a pressure dividing valve and micro-channel rubber, the pump is arranged in a helicopter, the inlet end of the pump is connected with a liquid storage tank, the outlet end of the pump is connected with the flow dividing bin, the flow dividing bin is rotationally assembled on a rotating shaft of the helicopter, the pressure dividing valve is arranged in the propeller, and a liquid outlet hole of the flow dividing bin is connected with the pressure dividing valve; the front edge of the propeller is coated with micro-channel rubber, a plurality of liquid storage chambers are arranged in the micro-channel rubber, a plurality of liquid inlet holes are formed in the micro-channel rubber located on one sides of the liquid storage chambers and used for being attached to the outer surface of the propeller, and a plurality of micron-sized channels distributed in an array mode are formed in the micro-channel rubber located on the other sides of the liquid storage chambers. Each liquid storage chamber is communicated with a plurality of corresponding micron-sized flow channels, a liquid outlet of the partial pressure valve is communicated with the liquid inlet hole, deicing liquid is intermittently or continuously sprayed on the super-amphiphobic surface of the micro-flow channel rubber, a super-smooth interface is formed, the anti-icing and deicing effects are achieved, and meanwhile the self-cleaning function is provided.

Description

Technical Field

[0001] The invention belongs to the technical field of helicopter propeller anti-icing and de-icing, and in particular relates to a device for realizing helicopter propeller anti-icing and de-icing by using micro-channel rubber. Background Art

[0002] Helicopter propeller icing is an extremely dangerous phenomenon that poses multiple threats to flight safety. First, ice accumulation on the propeller will significantly change the aerodynamic characteristics of the blades, resulting in a significant decrease in lift and thrust, making it difficult for the helicopter to maintain normal flight conditions. As the propeller efficiency decreases, the flight altitude may drop, or even fail to maintain hovering. Second, the accumulation of ice increases the weight of the propeller and the helicopter as a whole, which may exceed the design load capacity, further weakening the flight performance. In addition, since ice is usually unevenly distributed, it causes the propeller to be unbalanced and produce violent vibrations. This vibration not only affects the pilot's control, but may also cause damage to the helicopter's structure and key equipment. Further, the reduction in controllability makes it difficult for the pilot to make precise flight control, increasing the risk of accidents. More seriously, ice may cause the propeller blades to stall, causing the helicopter to fall into an uncontrollable state, posing great danger. Furthermore, when ice falls off the propeller, it may hit other parts of the helicopter, such as the tail rotor or fuselage, causing further damage. Therefore, in weather conditions where icing is possible, pilots must actively take anti-icing or de-icing measures (such as changing the flight altitude or route, but the flight altitude and flight route are predetermined and cannot be changed at any time) to reduce the adverse effects of icing and ensure flight safety. Summary of the invention

[0003] In view of the above-mentioned technical problems, the object of the present invention is to provide a helicopter propeller anti-icing device.

[0004] The purpose of the present invention is to be achieved by adopting the following technical scheme: a helicopter propeller anti-icing device, comprising a pump, a liquid storage tank, a shunt component, a detection component, a controller, and a microchannel rubber. The shunt component comprises a shunt chamber and a pressure dividing valve. The pump is arranged inside the helicopter and the inlet end of the pump is connected to the liquid storage tank, and the outlet end of the pump is connected to the shunt chamber. The shunt chamber is rotatably assembled on the rotating shaft of the helicopter. A pressure dividing valve is arranged inside each propeller, and the liquid outlet hole of the shunt chamber is connected to the pressure dividing valve in the propeller through a pipeline. The leading edge of the propeller is coated with microchannel rubber, and the microchannel rubber is provided with a pressure dividing valve. A plurality of liquid storage chambers are arranged inside the flow channel rubber, a plurality of liquid inlet holes are arranged on the micro-flow channel rubber located on one side of the liquid storage chamber and used to fit the outer surface of the propeller, and each liquid storage chamber is connected with a corresponding liquid inlet hole, a plurality of micron-level flow channels distributed in an array are arranged on the micro-flow channel rubber located on the other side of the liquid storage chamber, each liquid storage chamber is connected with a plurality of micron-level flow channels covered by the liquid storage chamber, and the liquid outlet of the pressure dividing valve is connected with the aforementioned liquid inlet hole through a pipeline; the detection component includes an ice sensor arranged on the leading edge surface of the propeller, and the ice sensor and the pump are electrically connected to the controller.

[0005] In one embodiment, the diversion chamber includes an outer shell and an inner shell that are rotatably matched, the inner wall of the outer shell is provided with two first bosses distributed along the axial direction, the inner shell is rotatably assembled on the rotating shaft of the helicopter, and a sealing ring is sandwiched between the outer wall of the inner shell and the inner walls of the two first bosses so that the two first bosses, the outer shell and the inner shell together form a chamber; a liquid outlet is provided on the outer shell located between the two first bosses, and a liquid inlet is provided inside the inner shell, and the liquid outlet and the liquid inlet are both connected to the chamber.

[0006] In one embodiment, an annular groove for the sealing ring to be embedded is provided on the inner wall of the first boss.

[0007] In one embodiment, an outer wall of the end of the inner shell is provided with a third boss for placing the outer shell.

[0008] In one embodiment, a plurality of liquid storage chambers are formed inside the microchannel rubber through a plurality of crisscross partition walls.

[0009] In one embodiment, the leading edge surface of the propeller is coated with a plurality of microchannel rubbers along its length direction, and a corresponding ice sensor is arranged on the leading edge surface of the propeller covered by each microchannel rubber, and the ice sensors are electrically connected to the controller.

[0010] In one embodiment, the detection component further includes a temperature and humidity sensor disposed on the outer surface of the cabin of the helicopter, and the temperature and humidity sensor is electrically connected to the controller.

[0011] In one embodiment, a micro-nano protrusion structure is provided on the outer surface of the microchannel rubber located on the other side of the oil storage chamber, and a super-amphiphobic suspension is sprayed on the outer surface of the microchannel rubber.

[0012] In one embodiment, the preparation process of the microfluidic rubber is as follows: polydimethylsiloxane and a curing agent are mixed at a mass ratio of 10:1 to form a prepolymer; nano-scale carbon powder is added to the prepolymer at a mass ratio of 1:50 and stirred, and the mixture of the prepolymer and the nano-scale carbon powder is poured on a polytetrafluoroethylene template having a microcolumn array structure, and after curing at 90°C for 60 minutes and peeling off, a PDMS prepolymer sheet having a regular micropore array structure is obtained.

[0013] In one embodiment, the preparation process of the microfluidic rubber is as follows: (1) polydimethylsiloxane and a curing agent are mixed at a mass ratio of 10:1 to form a prepolymer; nano-scale carbon powder is added to the prepolymer at a mass ratio of 1:50 and stirred, and the mixture of the prepolymer and the nano-scale carbon powder is poured on a polytetrafluoroethylene template having a micro-pillar array structure, and cured at 90° C. for 60 minutes and peeled off to obtain a PDMS prepolymer sheet; (2) 0.1 g of aluminum oxide nanoparticles are first ultrasonically dissolved in 50 ml of anhydrous ethanol for 20 minutes to obtain a first mixed solution, and then tetraethyl orthosilicate with a volume ratio of 1:2 is added. Ester and hexadecyltrimethoxysilane are simultaneously added to the first mixed solution to obtain a second mixed solution, and then 2 g of deionized water and 4.5 g of ammonia solution are quickly injected into the second mixed solution to obtain a third mixed solution. The third mixed solution is reacted at 800 rpm for 6 h to obtain a super-amphiphobic suspension; (3) the PDMS prepolymer sheet is ultrasonically cleaned with anhydrous ethanol and acetone for 3 times in sequence, and blown dry with a blower after cleaning; and then 6 ml of the super-amphiphobic suspension is sprayed onto the outer surface of the PDMS prepolymer sheet at a pressure of 0.2 MPa to obtain a microfluidic rubber with a super-amphiphobic surface.

[0014] By means of the above technical solution, the present invention can obtain the following advantages: (1) The leading edge of the helicopter propeller is coated with rubber with micron-scale flow channels. With the cooperation of the diversion chamber and the pressure-dividing valve, deicing liquid can be sprayed on the outer surface of the microchannel rubber to form an ultra-smooth interface, reduce the nucleation sites of ice, reduce the crystallization rate of water on the outer surface, and reduce the adhesion strength of ice, thereby achieving anti-deicing effect and providing self-cleaning function; (2) The leading edge of the helicopter propeller is coated with a microfluidic rubber with a super-amphiphobic surface, so that the outer surface of the rubber has super-hydrophobic and super-oleophobic functions, further enhancing the anti-icing effect; (3) Through the cooperation of the detection components and the controller, the intermittent spraying of deicing fluid or the continuous spraying of deicing fluid can be executed according to different icing conditions, thereby ensuring the anti-icing effect while efficiently utilizing the deicing fluid.

[0015] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention, it can be implemented according to the contents of the specification. In order to make the above and other purposes, features and advantages of the present invention more obvious and easy to understand, the following preferred embodiments are specifically cited and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The present invention is a structural block diagram of an embodiment of a helicopter propeller anti-icing and de-icing device of the present invention.

[0017] Figure 2A The figure is an axonometric diagram of a diversion chamber in an embodiment of a helicopter propeller anti-icing and deicing device of the present invention.

[0018] Figure 2B The present invention is a schematic cross-sectional view of a diversion chamber in an embodiment of a helicopter propeller anti-icing and deicing device.

[0019] Figure 3A yes Figure 2A , 2B An axonometric diagram of the outer shell of the diversion chamber shown.

[0020] Figure 3B yes Figure 2A , 2B A schematic cross-sectional view of the outer shell in the diversion chamber is shown.

[0021] Figure 4A yes Figure 2A , 2B An axonometric diagram of the inner shell in the diversion chamber is shown.

[0022] Figure 4B yes Figure 2A , 2B A schematic cross-sectional view of the inner shell in the diversion chamber is shown.

[0023] Figure 5 The figure is a top view schematic diagram of a micro-channel rubber in an embodiment of a helicopter propeller anti-icing and deicing device of the present invention.

[0024] Figure 5A yes Figure 5 AA cross-sectional view of .

[0025] Figure 5B yes Figure 5 A magnified schematic diagram of point B in the middle.

[0026] Figure 6 The present invention is a schematic cross-sectional view of a micro-channel rubber in another embodiment of a helicopter propeller anti-icing and deicing device.

[0027] [Reference Signs] 1-diversion chamber, 10-outer shell, 101 first boss, 1011-annular groove, 102-liquid outlet, 103-sealing ring, 104-chamber, 11-inner shell, 111-second boss, 112-third boss, 113-liquid inlet, 12-bearing, 2-microchannel rubber, 201-partition wall, 2011-through hole, 21-liquid storage chamber, 22-liquid inlet, 23-micrometer-level flow channel, 24-micrometer-level protrusion. DETAILED DESCRIPTION

[0028] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by showing examples of the present invention. In the drawings and the following description, at least part of the known structures and technologies are not shown to avoid unnecessary ambiguity of the present invention; and, for clarity, the size of some structures may be exaggerated. The features, structures or characteristics described below can be combined in one or more embodiments in any suitable manner. In addition, the terms "first or I", "second or II", "third or III", etc. are used only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0029] The directional words appearing in the following description are all directions shown in the figures, and do not limit the specific structure of the present invention. In the description of the present invention, it should also be noted that, unless otherwise clearly specified and limited, the terms "setting", "installation" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected or indirectly connected. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0030] See also Figure 1The present embodiment designs a helicopter propeller anti-icing device, which protects the helicopter propeller from icing through micro-channel rubber, and specifically includes a liquid storage tank, a pump, a shunt component, a controller, a detection component, and a micro-channel rubber, wherein the liquid storage tank and the pump are arranged at appropriate positions inside the helicopter, and the liquid storage tank is used to store deicing liquid. Common deicing liquids include ethylene glycol, isopropanol, ethanol, methanol, etc. The inlet end of the pump is connected to the liquid storage tank, and the outlet end thereof is connected to the shunt bin 1 of the shunt component. The shunt bin 1 is installed on the rotating shaft of the helicopter in a rotating connection manner, and each propeller is provided with a shunt inside. The pressure dividing valve of the flow component, the leading edge of each propeller is coated with a microchannel rubber 2, the liquid outlet of the diverter bin is connected to the pressure dividing valve in the corresponding propeller through a pipeline, and the liquid outlet of the pressure dividing valve is connected to the liquid storage chamber in the microchannel rubber through a pipeline. When the propeller needs to be de-iced, after starting the pump, the coolant in the liquid storage tank is successively sent into the liquid storage chamber in the microchannel rubber through the diverter bin and the pressure dividing valve, and then sprayed out from the micron-level flow channel on the microchannel rubber. The deicing liquid is mixed with the supercooled water droplets impacting the outer surface of the propeller to reduce its freezing point, thereby reducing the freezing temperature of the outer surface of the propeller to achieve the anti-icing purpose.

[0031] Specifically, since the propeller blades have the same angular velocity but different linear velocities, the farther from the center, the greater the linear velocity and the greater the speed, the less likely ice will adhere. Therefore, the blade root is relatively more prone to ice formation. Therefore, the microchannel rubber described in this embodiment should cover at least about 1 / 3 of the blade root.

[0032] Specifically, the flow diversion chamber 1 in this embodiment includes an outer shell 10 and an inner shell 11. Figure 2A and Figure 2B The outer shell is an axially hollow cylindrical part, and the upper and lower sides of the inner wall thereof are respectively provided with circumferentially closed first bosses 101, and the outer shell located between the two first bosses is provided with a plurality of circumferentially distributed liquid outlets 102, and the number of the liquid outlets should be equal to the number of the propellers; please refer to Figure 3A and Figure 3BThe inner shell is an axially hollow part with a T-shaped cross-section. The upper and lower sides of the inner wall are respectively provided with second bosses 111. During assembly, the inner shell is rotated and assembled on the outside of the rotating shaft of the helicopter through the cooperation of the bearing, the bearing retaining ring and the second boss (the bearing retaining ring is used to limit the bearing in one axial direction, and the second boss is used to limit the bearing in another axial direction). The outer shell 10 is rotated and assembled on the outside of the inner shell 11 through the cooperation of the bearing 12, the bearing retaining ring and the first boss 101. When assembled in place, the lower end of the outer shell 10 is placed on the third boss 112 at the lower end of the inner shell 11 (at this time, the third boss can limit the lower bearing in another axial direction). When the rotating shaft of the helicopter rotates, the propeller will rotate synchronously. At this time, the outer shell will rotate under the drive of the oil pipe between the outer shell and the pressure dividing valve, but the inner shell will not rotate, thereby avoiding the phenomenon of multiple oil pipes being entangled. In addition, an annular groove 1011 is provided on the inner wall of the first boss 101 for the sealing ring 103 to be embedded. When the outer shell is rotated and assembled on the outer side of the inner shell, the outer wall of the inner shell and the sealing ring 103 form an extrusion fit so that the two first bosses, the outer shell and the inner shell together form a chamber 104. The interior of the inner shell is provided with two liquid inlet channels 113 connected to the aforementioned chamber. The two liquid inlet entrances located on the lower end surface of the inner shell are connected to the outlet end of the pump through roads and pipe joints respectively. After starting the pump, the deicing liquid in the liquid storage tank is sent into the chamber through the pipeline and the liquid inlet channel, and then can flow to the pressure dividing valve through the liquid outlet hole.

[0033] Specifically, in this embodiment, a pressure sensor electrically connected to the controller is provided on the pipeline inside the propeller. Through the real-time feedback of the pressure sensor, the pressure-dividing valve provided inside the propeller has the function of accurately controlling the pressure of each liquid-dividing pipeline, ensuring that the deicing liquid can be delivered to the surface of the microchannel rubber with uniform pressure to achieve uniform distribution. This fine adjustment can effectively avoid the problem of too much or too little local deicing liquid, thereby improving the overall performance of the microchannel rubber, enhancing its anti-deicing and self-lubricating effects, and thus extending the service life of the helicopter propeller.

[0034] Specifically, in the present embodiment, the microfluidic rubber 2 coated on the leading edge of the propeller forms a plurality of liquid storage chambers 21 in its interior through a plurality of criss-crossing partition walls 201; a plurality of large-aperture liquid inlet holes 22 are provided on the microfluidic rubber located on one side of the liquid storage chamber and used to fit the outer surface of the propeller, and each liquid storage chamber is connected to a corresponding liquid inlet hole; a plurality of micron-sized flow channels 23 extending along the thickness direction of the microfluidic rubber are provided on the microfluidic rubber located on the other side of the liquid storage chamber; the plurality of micron-sized flow channels are distributed in an array and each liquid storage chamber is connected to a plurality of micron-sized flow channels covered by the liquid storage chamber. With the aid of the aforementioned design, a three-layer structure is formed inside the microfluidic rubber in this embodiment. In the direction away from the propeller, the first layer of the structure is a plurality of cylindrical flow channels with large apertures. When the microfluidic rubber is wrapped around the leading edge of the propeller, the liquid inlet hole is connected to the pressure dividing valve through a pipeline and a pipeline joint, ensuring that the deicing liquid can be smoothly transported from the pressure dividing valve to the inside of the microfluidic rubber; the second layer of the structure is a micro liquid storage chamber, which is used to store the deicing liquid during the deicing process to ensure that the liquid can be supplied in time when the demand changes; the third layer of the structure is a micron-level flow channel structure, which distributes the deicing liquid evenly to the outer surface of the microfluidic rubber (i.e., the surface of the microfluidic rubber away from the propeller) through tiny through holes, forming an ultra-smooth interface, reducing the nucleation sites of ice, reducing the crystallization rate of water on the outer surface, and reducing the adhesion strength of ice, thereby achieving an anti-deicing effect. The aforementioned three layers of the structure cooperate with each other to improve the delivery efficiency and distribution uniformity of the deicing liquid, thereby improving the overall performance of the device.

[0035] Furthermore, the first layer structure of the microfluidic rubber includes a plurality of large-aperture cylindrical channels, the bottom of which is in direct contact with the outer surface of the helicopter propeller to form a fitting state, and each cylindrical channel is connected to an independent oil storage chamber, which is functionally independent of each other, ensuring that the deicing effect of each area is not affected by other areas. Although the liquid storage chambers and the areas covered by the liquid storage chambers are independent, the multiple micron-level channels covered by the same liquid storage chamber are effectively interconnected to form an internal liquid network. The above design can not only evenly distribute the deicing liquid on the outer surface of the microfluidic rubber, but also effectively prevent the deicing liquid from flowing unevenly between regions, thereby improving the anti-icing and self-lubricating properties of the microfluidic rubber. In addition, since the centrifugal force generated when the propeller rotates continuously will directly throw the deicing liquid away, resulting in a reduction in the deicing effect, this embodiment uses the second layer of liquid storage chamber inside the microfluidic rubber to reduce the spraying speed of the deicing liquid, so that the deicing liquid acts on the outer surface of the rubber as much as possible, thereby ensuring the deicing effect and avoiding excessive waste of the deicing liquid.

[0036] Furthermore, a micro-nano protrusion structure 24 is provided on the outer surface of the microchannel rubber 2. With the aid of the aforementioned micro-nano protrusion structure, the outer surface of the microchannel rubber has a super-hydrophobic function, further enhancing the anti-icing effect. At the same time, a super-amphiphobic suspension is sprayed on the outer surface of the microchannel rubber, so that the outer surface of the microchannel rubber forms a super-amphiphobic surface (i.e., it has both super-hydrophobic and super-oleophobic properties). With the aid of the super-amphiphobic surface, not only can the adhesion between the ice layer and the surface be significantly reduced, so that ice is not easy to adhere to the surface, which is easy to remove, but also the behavior of water droplets can be changed, so that the time for water droplets to form on the surface becomes longer, thereby reducing the speed of ice formation, and at the same time, it can also reduce the residence time of liquid water on the surface, reducing the probability of water freezing.

[0037] Furthermore, the preparation process of the microfluidic channel rubber in this embodiment is as follows: First, polydimethylsiloxane (PDMS) and a curing agent are mixed in a mass ratio of 10:1 to form a prepolymer; then, nano-scale carbon powder is added to the aforementioned prepolymer (wherein the mass ratio of carbon powder to prepolymer is 1:50) and stirred, and the mixture of the prepolymer and the carbon powder is poured on a polytetrafluoroethylene (PTFE) mold having a micro-pillar array structure, and after curing at 90°C for 60 minutes and peeling, a PDMS prepolymer sheet having a regular microporous array structure (hereinafter referred to as MS sheet) is prepared, and the MS sheet is a microfluidic channel rubber having a micron-scale protrusion structure; Secondly, 0.1 g of aluminum oxide (Al2O3) nanoparticles were ultrasonically dissolved in 50 ml of anhydrous ethanol for 20 min to obtain a first mixed solution, and then tetraethyl orthosilicate (TEOS) and hexadecyltrimethoxysilane (HDTMS) with a volume ratio of 1:2 were simultaneously added to the first mixed solution (i.e., aluminum oxide / anhydrous ethanol solution) to obtain a second mixed solution, and then 2 g of deionized water and 4.5 g of ammonia solution were quickly injected into the second mixed solution (i.e., Al2O3NPs / TEOS / HDTMS / anhydrous ethanol solution) to obtain a third mixed solution, and the third mixed solution was stirred at 800 rpm for 6 h to obtain a milky white super-amphiphobic suspension; Furthermore, the MS sheet was ultrasonically cleaned three times with anhydrous ethanol and acetone in sequence to remove the grease on the initial surface, and then dried with a blower; 6 ml of the super-amphiphobic suspension was introduced into a spray gun (Anest Iwata, Japan) and sprayed onto the outer surface of the microfluidic rubber at a pressure of 0.2 MPa provided by an air compressor to obtain a microfluidic rubber with a super-amphiphobic surface. In addition, the aforementioned spraying process was carried out on a heating plate at a temperature above 120°C.

[0038] Specifically, the present embodiment detects whether the leading edge of the propeller needs to be de-iced and controls the operation of the pump through the cooperation of the detection component and the controller. The detection component includes an ice sensor, which is arranged on the leading edge surface of the propeller to detect whether the propeller is frozen and uploads the data (such as ice thickness) of whether the propeller is frozen to the controller. After analyzing the above data, the controller controls the pump to start, and sprays the de-icing liquid in the liquid storage tank onto the super-amphiphobic surface of the microchannel through the diversion component. After the de-icing liquid combines with the super-cooled water droplets, the de-icing effect is easily achieved by means of the self-cleaning effect of the super-amphiphobic surface and the centrifugal force during the rotation of the propeller. Furthermore, in the early stage of ice formation, the present embodiment executes an intermittent spraying mode of the de-icing liquid. In the case of ice formation caused by harsh environment In the scenario of rapid or severe ice accumulation, considering that the propeller speed is usually 960 rpm, it can be calculated according to the centrifugal force formula, where a drop of water is calculated as 1g in weight, the angular velocity is 960 rpm, and after conversion, ω is 32πrad / s, and the rotation radius is based on the radius of a large helicopter propeller (6m). According to the formula F=mω^2r, F=60.6N is obtained. After the metal is frozen, the ice adhesion force is approximately between 250-300N. Therefore, in this scenario, this embodiment executes a continuous spraying of deicing fluid. By continuously spraying the deicing fluid, the adhesion force on the propeller surface is reduced to below 190N, ensuring that the accumulated ice can be removed; when the detection component detects that the leading edge does not need deicing, the controller controls the pump to stop.

[0039] Furthermore, the detection component may also include a temperature and humidity sensor, which is arranged on the outer surface of the helicopter cabin, for detecting the temperature and humidity of the propeller environment, and uploading the detected ambient temperature data and ambient humidity data to the controller, so as to facilitate the controller to combine environmental conditions, icing rate, ice thickness and other data to achieve more accurate control and more working modes.

[0040] Furthermore, a plurality of micro-channel rubbers may be arranged on the leading edge surface of the propeller along the length direction of the propeller, and corresponding ice sensors may be arranged on the leading edge of the propeller covered by each micro-channel rubber. These ice sensors are electrically connected to the controller, and the data uploaded by the ice sensors at different positions may be used to achieve fixed-point deicing, thereby ensuring the deicing effect and efficiently utilizing the deicing fluid.

[0041] In other embodiments of the present invention, the inner housing may be an axially hollow cylindrical part, in which case the bearing located on the lower side needs to be limited by a corresponding bearing retaining ring (instead of the third boss in this embodiment) so that the outer housing can be rotatably assembled on the outside of the inner housing.

[0042] In other embodiments of the present invention, an annular groove for embedding the sealing ring is provided on the outer wall of the inner shell body. When the outer shell body is rotated and assembled on the outer side of the inner shell body, the inner wall of the first boss squeezes the aforementioned sealing ring so that the two first bosses, the outer shell body and the inner shell body jointly form an oil chamber.

[0043] In other embodiments of the present invention, the user can adjust the number of liquid inlets as needed.

[0044] In other embodiments of the present invention, additional through holes 2011 may be provided on the partition wall between two adjacent liquid storage chambers to reduce the number of liquid inlet holes on the microfluidic channel rubber (eg, Figure 6 As shown in the figure, the number of holes on the outer surface of the propeller for the pipeline to pass through is reduced, thereby ensuring the overall strength of the propeller.

[0045] Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A helicopter propeller anti-icing device, characterized in that The invention comprises a pump, a liquid storage tank, a flow dividing component, a detection component, a controller and a microfluidic rubber. The flow dividing component comprises a flow dividing chamber and a pressure dividing valve. The pump is arranged inside the helicopter and the inlet end of the pump is connected to the liquid storage tank and the outlet end thereof is connected to the flow dividing chamber. The flow dividing chamber is rotatably assembled on the rotating shaft of the helicopter. A pressure dividing valve is arranged inside each propeller. The liquid outlet hole of the flow dividing chamber is connected to the pressure dividing valve in the propeller through a pipeline. The leading edge of the propeller is covered with the microfluidic rubber. A plurality of liquid storage chambers are arranged inside the microfluidic rubber. A plurality of liquid inlet holes are arranged on the microfluidic rubber located on one side of the liquid storage chamber and used for fitting the outer surface of the propeller, and each liquid storage chamber is connected to a corresponding liquid inlet hole. A plurality of micrometer-level flow channels distributed in an array are arranged on the microfluidic rubber located on the other side of the liquid storage chamber. Each liquid storage chamber is connected to a plurality of micrometer-level flow channels covered by the liquid storage chamber. The liquid outlet of the pressure dividing valve is connected to the aforementioned liquid inlet hole through a pipeline. The detection component comprises an icing sensor arranged on the leading edge surface of the propeller. The icing sensor and the pump are both electrically connected to the controller.

2. A helicopter propeller anti-icing device according to claim 1, characterized in that The diversion chamber includes an outer shell and an inner shell that are rotatably matched. The inner wall of the outer shell is provided with two first bosses distributed along the axial direction. The inner shell is rotatably assembled on the rotating shaft of the helicopter, and a sealing ring is sandwiched between the outer wall of the inner shell and the inner walls of the two first bosses so that the two first bosses, the outer shell and the inner shell form a chamber together; a liquid outlet is provided on the outer shell between the two first bosses, and a liquid inlet is provided inside the inner shell, and the liquid outlet and the liquid inlet are both connected to the chamber.

3. A helicopter propeller anti-icing device according to claim 2, characterized in that An annular groove for the sealing ring to be embedded is arranged on the inner wall of the first boss.

4. A helicopter propeller anti-icing device according to claim 2, characterized in that The outer wall of the end of the inner shell is provided with a third boss for placing the outer shell.

5. The helicopter propeller anti-icing device according to claim 1, characterized in that The interior of the microfluidic rubber forms multiple liquid storage chambers through multiple crisscross partition walls.

6. A helicopter propeller anti-icing device according to claim 1, characterized in that The leading edge surface of the propeller is coated with a plurality of micro-channel rubbers along its length direction, and corresponding ice sensors are arranged on the leading edge surface of the propeller covered by each micro-channel rubber, and the ice sensors are electrically connected to the controller.

7. A helicopter propeller anti-icing device according to claim 1 or 6, characterized in that The detection component also includes a temperature and humidity sensor arranged on the outer surface of the cabin of the helicopter, and the temperature and humidity sensor is electrically connected to the controller.

8. The helicopter propeller anti-icing device according to claim 1, characterized in that A micro-nano protrusion structure is arranged on the outer surface of the microfluidic channel rubber located on the other side of the oil storage chamber, and a super-amphiphobic suspension is sprayed on the outer surface of the microfluidic channel rubber.

9. A helicopter propeller anti-icing device according to claim 1, characterized in that The preparation process of the microfluidic rubber is as follows: polydimethylsiloxane and a curing agent are mixed at a mass ratio of 10:1 to form a prepolymer; nano-scale carbon powder is then added to the aforementioned prepolymer at a mass ratio of 1:50 and stirred; the mixture of the prepolymer and the nano-scale carbon powder is poured on a polytetrafluoroethylene template with a microcolumn array structure, and after curing at 90°C for 60 minutes and peeling off, a PDMS prepolymer sheet with a regular micropore array structure is obtained.

10. A helicopter propeller anti-icing device according to claim 8, characterized in that The preparation process of the microfluidic rubber is as follows: (1) polydimethylsiloxane and a curing agent are mixed at a mass ratio of 10:1 to form a prepolymer; then nano-scale carbon powder is added to the prepolymer at a mass ratio of 1:50 and stirred; the mixture of the prepolymer and the nano-scale carbon powder is poured on a polytetrafluoroethylene template with a microcolumn array structure, cured at 90°C for 60 minutes and peeled off to obtain a PDMS prepolymer sheet; (2) 0.1 g of aluminum oxide nanoparticles are first ultrasonically dissolved in 50 ml of anhydrous ethanol for 20 minutes to obtain a first mixed solution, and then tetraethyl orthosilicate and decafluoroethane are added at a volume ratio of 1:

2. Hexaalkyltrimethoxysilane is simultaneously added to the first mixed solution to obtain a second mixed solution, and then 2 g of deionized water and 4.5 g of ammonia solution are quickly injected into the second mixed solution to obtain a third mixed solution. The third mixed solution is reacted at 800 rpm for 6 h to obtain a super-amphiphobic suspension; (3) The PDMS prepolymer sheet is ultrasonically cleaned three times with anhydrous ethanol and acetone in sequence, and then dried with a blower; and then 6 ml of the super-amphiphobic suspension is sprayed onto the outer surface of the PDMS prepolymer sheet at a pressure of 0.2 MPa to obtain a microfluidic rubber with a super-amphiphobic surface.

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