Anti-icing system of aircraft wing, control method of anti-icing system and aircraft

Abstract

The invention relates to an anti-icing system of an aircraft wing, a control method of the anti-icing system and an aircraft. The anti-icing system of the aircraft wing comprises an air source, an anti-icing pipeline, an anti-icing valve, an electric heating device and an anti-icing controller, wherein the anti-icing valve and the electric heating device are arranged on the anti-icing pipeline. The gas source is used for supplying gas with a first preset temperature, and the anti-icing pipeline is connected between the gas source and a pipeline in an aircraft wing. And the anti-icing controller is electrically connected with the anti-icing valve and the electric heating device. When the weather condition is converted from the non-icing weather to the first icing weather, the anti-icing controller controls the anti-icing valve to be opened, so that the gas with the first preset temperature is transmitted into the pipeline of the aircraft wing through the anti-icing pipeline; and when the meteorological condition is converted from the first icing weather to the second icing weather, the anti-icing controller controls the anti-icing valve and the electric heating device to be started at the same time, so that the gas is heated from the first preset temperature to the second preset temperature when passing through the electric heating device, and then the gas is transmitted to the pipeline in the aircraft wing.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft wing anti-icing, and particularly to an anti-icing system for an aircraft wing, a control method thereof, and an aircraft. Background Art

[0002] Aircraft icing is an important challenge in the field of aviation safety, especially prominent in cold or humid flight environments. The icing phenomenon mainly occurs when the aircraft flies through clouds or precipitation areas containing supercooled water droplets. These droplets freeze rapidly after colliding with the aircraft body, forming ice layers, which affect flight performance and safety.

[0003] Currently, the anti-icing system of aircraft wings mainly relies on engine bleed air to spray high-temperature gas onto the wing skin for heating, thereby achieving the functions of anti-icing and de-icing. The traditional anti-icing system of aircraft wings is mainly designed for icing weather in lower airspace (such as below 31,000 feet, etc.). In higher airspace (such as above 31,000 feet, etc.), although the probability of encountering icing weather is relatively low, icing may still occur.

[0004] However, as the flight altitude increases, the hot air flow available for anti-icing gradually decreases. If the high-altitude anti-icing system is designed according to the most severe icing conditions, the size of the air source pre-cooler may be too large, and even limited by the aircraft design space, making it difficult to meet the actual requirements. In addition, when cruising above 31,000 feet, the probability of the aircraft encountering an extreme icing environment is relatively low. If designed according to the most extreme situation, most of the energy of the system will be in an excessive state, thereby reducing fuel economy. Summary of the Invention

[0005] Embodiments of the present application provide an anti-icing system for an aircraft wing, a control method thereof, and an aircraft, aiming to improve the adaptability and fuel economy of the anti-icing system of the aircraft wing.

[0006] To achieve the above object, according to the first aspect of the present application, an anti-icing system for an aircraft wing is provided, including:

[0007] An air source and an anti-icing pipeline. The air source is used to supply gas, and the gas has a first preset temperature. One end of the anti-icing pipeline is connected to the air source, and the other end is connected to the pipeline in the aircraft wing;

[0008] An anti-icing valve, provided on the anti-icing pipeline;

[0009] An electric heating device, provided on the anti-icing pipeline;

[0010] An anti-icing controller, electrically connected to the anti-icing valve and the electric heating device;

[0011] Wherein, when the meteorological condition changes from a non-icing condition to a first icing condition, the anti-icing controller can control the anti-icing valve to open, so that the gas with a first preset temperature is transmitted through the anti-icing pipeline to the pipeline of the aircraft wing; when the meteorological condition changes from the first icing condition to a second icing condition, the anti-icing controller can control the anti-icing valve and the electric heating device to open simultaneously, so that when the gas passes through the electric heating device, it is heated from the first preset temperature to the second preset temperature, and then transmitted to the pipeline in the aircraft wing, and the first preset temperature is lower than the second preset temperature.

[0012] Optionally, the anti-icing pipeline includes: a first section and a second section, the first section is connected to the gas source, and the second section is connected to the pipeline in the aircraft wing;

[0013] The electric heating device includes: a ventilation pipe and an electric heating wire; both ends of the ventilation pipe are respectively connected to the first section and the second section for the gas to pass through; the electric heating wire is arranged in the ventilation pipe and is electrically connected to the anti-icing controller;

[0014] When the anti-icing controller turns on the electric heating device, the electric heating wire heats the gas with a first preset temperature passing through the ventilation pipe to the second preset temperature.

[0015] Optionally, the ventilation pipe includes an outer sleeve, a first inner lining pipe and a second inner lining pipe nested in sequence along the wall thickness direction of the ventilation pipe;

[0016] The electric heating wire includes a first part and a second part, the first part is arranged between the first inner lining pipe and the second inner lining pipe, and the second part is connected to the first part and is arranged in the hollow area of the second inner lining pipe;

[0017] The ventilation pipe further includes an electrical connector, the electrical connector penetrates through the outer sleeve, the first inner lining pipe and the second inner lining pipe, and the electrical connector electrically connects the electric heating wire and the anti-icing controller.

[0018] Optionally, the second part is arranged in a Y shape, a triangle, a star shape or a spiral shape.

[0019] Optionally, the outer sleeve is a metal pipe, and the first inner lining pipe and the second inner lining pipe are insulating pipes.

[0020] Optionally, the anti-icing system of the aircraft wing further includes an anti-icing temperature sensor, and the anti-icing temperature sensor is arranged on the aircraft wing;

[0021] The anti-icing temperature sensor is used to transmit temperature conditions, and the temperature conditions include a first temperature signal and a second temperature signal. When the temperature is lower than the first temperature, the anti-icing temperature sensor emits the first temperature signal. When the temperature is higher than the second temperature, the anti-icing temperature sensor emits the second temperature signal, and the first temperature is lower than the second temperature;

[0022] When the meteorological conditions change from the second icing meteorological condition to the first icing meteorological condition, and the first temperature signal disappears while the second temperature signal is not sent, the anti-icing controller controls the anti-icing valve and the electric heating device to remain open;

[0023] When the meteorological conditions change from the second icing meteorological condition to the first icing meteorological condition, and the second temperature signal is sent, the anti-icing controller controls the anti-icing valve to remain open and closes the electric heating device.

[0024] Optionally, the anti-icing system of the aircraft wing further includes an anti-icing switch, which has a first gear, a second gear, and a third gear;

[0025] When the anti-icing switch is in the first gear, the anti-icing controller controls the anti-icing valve and the electric heating device to close;

[0026] When the anti-icing switch is in the second gear, the anti-icing controller controls the anti-icing valve to open and the electric heating device to close;

[0027] When the anti-icing switch is in the third gear, the anti-icing controller controls the anti-icing valve and the electric heating device to open.

[0028] According to the second aspect of the present application, a control method for an anti-icing system of an aircraft wing is provided, which is applied to the anti-icing system of an aircraft wing disclosed in any one of the above, and the control method includes:

[0029] Obtain environmental condition information, where the environmental condition information characterizes the environmental state of the aircraft;

[0030] Based on the environmental condition information, send an execution instruction to the anti-icing valve and the electric heating device; the execution instruction is used to control the opening and closing states of the anti-icing valve and the electric heating device.

[0031] Optionally, based on the environmental condition information, sending an execution instruction to the anti-icing valve and the electric heating device; the execution instruction for controlling the opening and closing states of the anti-icing valve and the electric heating device includes:

[0032] If the environmental condition information is the first environment, send a closing instruction to the anti-icing valve and the electric heating device; or;

[0033] If the environmental condition information is the second environment, send an opening instruction to the anti-icing valve and a closing instruction to the electric heating device, so that the gas supplied by the air source is transmitted to the aircraft wing through the anti-icing pipeline; or;

[0034] If the environmental condition information is the third environment, send an opening instruction to the anti-icing valve and the electric heating device, so that the gas is further heated when passing through the electric heating device and then transmitted to the aircraft wing.

[0035] Optionally, the environmental condition information includes meteorological conditions; the meteorological conditions include non-icing meteorological conditions, the first icing meteorological condition, and the second icing meteorological condition;

[0036] When the meteorological condition is non-icing weather, the environmental condition information is the first environment;

[0037] When the meteorological condition changes from non-icing weather to the first icing weather, the environmental condition information is the second environment;

[0038] When the meteorological condition changes from the first icing weather to the second icing weather, the environmental condition information is the third environment.

[0039] Optionally, the environmental condition information further includes a temperature condition; the anti-icing system of the aircraft wing further includes an anti-icing temperature sensor, which is arranged on the aircraft wing and is used to collect and transmit the temperature condition; the temperature condition includes a first temperature signal and a second temperature signal. When the temperature is lower than the first temperature, the anti-icing temperature sensor emits the first temperature signal. When the temperature is higher than the second temperature, the anti-icing temperature sensor emits the second temperature signal, and the first temperature is lower than the second temperature;

[0040] When the meteorological condition changes from the second icing weather to the first icing weather, and the first temperature signal disappears and the second temperature signal is not emitted, the environmental condition information is also the third environment;

[0041] When the meteorological condition changes from the second icing weather to the first icing weather, and the second temperature signal is emitted, the environmental condition information is also the second environment.

[0042] According to the third aspect of the present application, an aircraft is further provided, including the anti-icing system of the aircraft wing according to any one of the above disclosures.

[0043] In the ice protection system of the aircraft wing according to the embodiments of the present application, an ice protection valve and an electric heating device are provided on the ice protection pipeline. When the ice protection valve is closed, it can prevent gas from flowing into the pipeline of the aircraft wing, thus avoiding wasting heat energy when ice protection or ice breaking is not required. When the ice protection valve is opened, it can allow gas to be transmitted through the ice protection pipeline to the pipeline of the aircraft wing to provide a basic ice protection function and prevent ice formation on the wing surface; when the gas passes through the ice protection pipeline, it will pass through the electric heating device. When the electric heating device is turned on, it can further heat the passing gas, increase the temperature of the gas, and enhance the ice protection effect of the ice protection system of the aircraft wing. Specifically, the present application implements a multi-level ice protection strategy by setting an ice protection valve and an electric heating device on the ice protection pipeline, and adjusts the ice protection strategy according to the conversion of meteorological conditions. When the meteorological conditions change from non-icing weather to the first icing weather, the system only opens the ice protection valve and uses the gas supplied by the air source for ice protection, saving energy. When the meteorological conditions change from the first icing weather to the second icing weather, the system simultaneously opens the ice protection valve and the electric heating device to heat the gas supplied by the air source and provide a stronger ice protection ability. With such a setting, the ice protection system of the aircraft wing only uses gas with a first preset temperature without additional heating, saving energy consumption and improving fuel economy; in harsh environmental conditions, the ice protection system of the aircraft wing can provide a stronger ice protection ability to ensure that ice does not form on the wing surface, maintain the normal flight performance and controllability of the aircraft, and effectively improve the adaptability and fuel economy of the ice protection system of the aircraft wing.

[0044] Other features and advantages of the present application will be described in detail in the subsequent specific implementation section. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the following drawings are only some embodiments of the present application, and those skilled in the art can obtain other drawings according to these drawings without creative efforts.

[0046] In order to more completely understand the present application and its beneficial effects, the following will be described in conjunction with the drawings, where the same reference numerals in the following description represent the same parts.

[0047] Figure 1 is a schematic diagram of the overall structure of the ice protection system of the aircraft wing provided by the embodiments of the present application;

[0048] Figure 2 is a cross-sectional view of the electric heating device provided by the embodiments of the present application;

[0049] Figure 3 is a schematic connection diagram of the electric heating device and the ice protection controller provided by the embodiments of the present application;

[0050] Figure 4 It is a control method for the anti-icing system of an aircraft wing provided by an embodiment of the present application;

[0051] Figure 5 It is a switching logic diagram of an anti-icing switch provided by an embodiment of the present application.

[0052] Explanation of reference numerals:

[0053] 1. Air source;

[0054] 2. Anti-icing pipeline; 21. First section; 22. Second section;

[0055] 3. Anti-icing valve;

[0056] 4. Electric heating device; 41. Vent pipe; 411. Outer sleeve; 412. First inner lining pipe; 413. Second inner lining pipe; 42. Electric heating wire; 421. First part; 422. Second part; 43. Electrical connector;

[0057] 5. Anti-icing controller; 51. Current controller;

[0058] 6. Anti-icing switch; 7. Anti-icing temperature sensor;

[0059] 8. Aircraft wing; 9. Aircraft power supply;

[0060] 10. Pressure detection component. Detailed implementation manners

[0061] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative efforts belong to the protection scope of the present application.

[0062] An embodiment of the present application provides an anti-icing system for an aircraft wing. Please refer to Figure 1 , Figure 1 which is a schematic diagram of the overall structure of the anti-icing system for an aircraft wing provided by an embodiment of the present application. The anti-icing system for an aircraft wing disclosed in the embodiment of the present application includes: an air source 1, an anti-icing pipeline 2, an anti-icing valve 3, an electric heating device 4, and an anti-icing controller 5. The air source 1 is used to supply gas with a first preset temperature. One end of the anti-icing pipeline 2 is communicated with the air source 1, and the other end is communicated with the pipeline in the aircraft wing 8. The anti-icing valve 3 is arranged on the anti-icing pipeline 2. The electric heating device 4 is arranged on the anti-icing pipeline 2. The anti-icing controller 5 is electrically connected to the anti-icing valve 3 and is also electrically connected to the electric heating device 4.

[0063] When the meteorological conditions change from non-icing meteorological conditions to the first icing meteorological conditions, the anti-icing controller 5 can control the anti-icing valve 3 to open, so that the gas with the first preset temperature can be transmitted through the anti-icing pipeline 2 into the pipeline of the aircraft wing 8. When the meteorological conditions change from the first icing meteorological conditions to the second icing meteorological conditions, the anti-icing controller 5 can control the anti-icing valve 3 and the electric heating device 4 to open simultaneously, so that when the gas passes through the electric heating device 4, it is heated from the first preset temperature to the second preset temperature, and then transmitted into the pipeline in the aircraft wing 8, where the first preset temperature is lower than the second preset temperature. When the meteorological conditions change from the first icing meteorological conditions to non-icing meteorological conditions, the anti-icing valve 3 closes. When the meteorological conditions change from the second icing meteorological conditions to non-icing meteorological conditions, both the anti-icing valve 3 and the electric heating device 4 close.

[0064] In the anti-icing system of the aircraft wing according to the embodiment of the present application, an anti-icing valve 3 and an electric heating device 4 are provided on the anti-icing pipeline 2. When the anti-icing valve 3 is closed, it can prevent the gas from flowing into the pipeline of the aircraft wing 8, thus avoiding wasting heat energy when anti-icing or de-icing is not required. When the anti-icing valve 3 is open, it can allow the gas to be transmitted through the anti-icing pipeline 2 into the pipeline of the aircraft wing 8 to provide a basic anti-icing function and prevent ice formation on the wing surface. The gas passing through the anti-icing pipeline 2 will pass through the electric heating device 4. When the electric heating device 4 is open, it can further heat the passing gas, increase the temperature of the gas, and enhance the anti-icing effect of the anti-icing system of the aircraft wing. Specifically, the present application implements a multi-stage anti-icing strategy by setting the anti-icing valve 3 and the electric heating device 4 on the anti-icing pipeline 2, and adjusts the anti-icing strategy according to the conversion of meteorological conditions. When the meteorological conditions change from non-icing meteorological conditions to the first icing meteorological conditions, the system only opens the anti-icing valve 3 and uses the gas supplied by the gas source 1 for anti-icing, saving energy. When the meteorological conditions change from the first icing meteorological conditions to the second icing meteorological conditions, the system opens the anti-icing valve 3 and the electric heating device 4 simultaneously to heat the gas supplied by the gas source 1 and provide a stronger anti-icing ability. With such a setting, the anti-icing system of the aircraft wing only uses the gas with the first preset temperature without additional heating, saving energy consumption and improving fuel economy; in harsh environmental conditions, the anti-icing system of the aircraft wing can provide a stronger anti-icing ability to ensure that the wing surface does not ice up, maintain the normal flight performance and controllability of the aircraft, and effectively improve the adaptability and fuel economy of the anti-icing system of the aircraft wing.

[0065] In some embodiments, the ice protection system of the aircraft wing further includes an ice protection temperature sensor 7, which is disposed on the aircraft wing 8; the ice protection temperature sensor 7 is used to transmit temperature conditions, and the temperature conditions include a first temperature signal and a second temperature signal. When the temperature is lower than the first temperature, the ice protection temperature sensor 7 emits the first temperature signal; when the temperature is higher than the first temperature, the first temperature signal disappears; when the temperature is higher than the second temperature, the ice protection temperature sensor 7 emits the second temperature signal; the first temperature is lower than the second temperature. In some embodiments, during the period when the temperature is lower than the first temperature, the first temperature signal will be continuously emitted as an alarm signal. When the temperature is higher than the second temperature, the second temperature signal will only be emitted within a preset time as a reminder signal. In some embodiments, the first temperature can be thirty degrees, and the second temperature can be fifty degrees.

[0066] In some embodiments, when the meteorological conditions change from the second icing meteorological condition to the first icing meteorological condition, and the first temperature signal disappears and the second temperature signal is not emitted, the ice protection controller 5 controls the ice protection valve 3 and the electric heating device 4 to remain open. When the meteorological conditions change from the second icing meteorological condition to the first icing meteorological condition, and the second temperature signal is emitted, the ice protection controller 5 controls the ice protection valve 3 to remain open and closes the electric heating device 4.

[0067] In the initial stage of the improvement of the meteorological conditions, even if the temperature in the area where the ice protection temperature sensor 7 is located is slightly higher than the first temperature, the temperature in some local areas of the aircraft wing 8 may still be close to the freezing point. Keeping the ice protection valve 3 and the electric heating device 4 open simultaneously can effectively prevent moisture from refreezing on the aircraft surface or the wing, thus ensuring flight safety. At the same time, keeping the electric heating device 4 on when the second temperature signal is not emitted can avoid the icing risk caused by temperature fluctuations and the energy consumption loss caused by the frequent opening and closing of the electric heating device 4 due to temperature fluctuations.

[0068] Refer to Figure 1 and Figure 2, the anti-icing pipeline 2 includes a first section 21 and a second section 22. The first section 21 is connected to the gas source 1, and the second section 22 is connected to the pipeline in the aircraft wing 8. The electric heating device 4 includes a ventilation pipe 41 and an electric heating wire 42. Both ends of the ventilation pipe 41 are respectively connected to the first section 21 and the second section 22 to allow gas to pass through. The electric heating wire 42 is arranged in the ventilation pipe 41 and is electrically connected to the anti-icing controller 5. When the anti-icing controller 5 turns on the electric heating device 4, the electric heating wire 42 heats the gas passing through the ventilation pipe 41. In this embodiment, the anti-icing valve 3 is arranged on the first section 21. After the anti-icing valve 3 is opened, the gas first passes through the anti-icing valve 3 and then through the electric heating device 4. In some other embodiments, the anti-icing valve 3 is arranged on the second section 22. After the anti-icing valve 3 is opened, the gas first passes through the electric heating device 4 and then through the anti-icing valve 3. In some embodiments, the heating power of the electric heating device 4 is 15 kw. This value is for reference only. The specific design of the heating power should be comprehensively determined in combination with the aircraft model, flight envelope, etc.

[0069] Further, referring to Figure 2 , in some embodiments, the ventilation pipe 41 includes an outer sleeve 411, a first inner liner 412, and a second inner liner 413 nested in sequence along the wall thickness direction of the ventilation pipe 41. The electric heating wire 42 includes a first part 421 and a second part 422. The first part 421 is arranged between the first inner liner 412 and the second inner liner 413, and the second part 422 is connected to the first part 421 and is arranged in the hollow area of the second inner liner 413. The ventilation pipe 41 further includes an electrical connector 43. The electrical connector 43 penetrates through the outer sleeve 411, the first inner liner 412, and the second inner liner 413, and the electrical connector 43 electrically connects the electric heating wire 42 and the anti-icing controller 5.

[0070] In the embodiment of the present application, the second part 422 is arranged in a Y shape. In some other embodiments, the second part 422 can be arranged in a triangle, a star shape, or a spiral shape.

[0071] In some embodiments, the outer sleeve 411 is a metal pipe, and the first inner liner 412 and the second inner liner 413 are insulating pipes. Setting the outer sleeve 411 as a metal pipe can improve the structural strength of the electric heating device 4. Setting the first inner liner 412 and the second inner liner 413 as insulating pipes can prevent the electric heating wire 42 from directly contacting the outer sleeve 411 and causing a short circuit. In some embodiments, the first section 21 and the second section 22 are usually also metal pipes. Setting the first inner liner 412 and the second inner liner 413 as insulating pipes also reduces the risk of electric leakage in the anti-icing pipeline 2.

[0072] In some embodiments, connection flanges are provided at both ends of the vent pipe 41. Connection flanges are also provided at one end of the first section 21 and the second section 22 for connecting to the vent pipe 41. The vent pipe 41 and the first section 21 are connected through the connection flanges, and the vent pipe 41 and the second section 22 are also connected through the connection flanges. In some embodiments, two connected connection flanges can be fixedly connected through a connection clamp. With such a setting, the electric heating device 4 can be freely disassembled on the anti-icing pipeline 2. Compared with the traditional bolt fixation, the way of using a clamp to fix the connection flanges does not require tightening or disassembling bolts one by one, but realizes quick clamping and loosening through a single clamp. When the electric heating device 4 needs to be replaced, only the clamp needs to be loosened, and then the electric heating device 4 can be taken off as a whole, greatly reducing the disassembly and assembly time and improving the maintenance efficiency.

[0073] Referring to Figure 3 , in some embodiments, the anti-icing controller 5 internally has a current controller 51. The current controller 51 is electrically connected to the electrical connector 43 of the electric heating device 4 and the aircraft power supply 9. The current controller 51 of the anti-icing controller 5 realizes the start and stop of the electric heating device 4 by controlling the on-off of the current between the aircraft power supply 9 and the electrical connector 43. The aircraft power supply 9 provides three-phase alternating current for the electric heating device 4.

[0074] In some embodiments, a pressure detection assembly 10 is further provided on the second section 22 of the anti-icing pipeline 2. The pressure detection assembly 10 is located on the side of the anti-icing valve 3 away from the gas source 1 and is used to detect the gas pressure in the anti-icing pipeline 2. The anti-icing controller 5 is electrically connected to the pressure detection assembly 10. After the anti-icing valve 3 is opened, the anti-icing controller 5 can adjust the flow rate of the gas provided by the gas source 1 to a set value through the gas pressure feedback by the pressure detection assembly 10. In some embodiments, the set value of the gas flow rate can be 0.6 kg / s. This value is for reference only, and the specific design of the flow rate size should be comprehensively determined in combination with the aircraft model, flight envelope, etc. In some embodiments, the pressure detection assembly 10 includes two pressure sensors arranged at intervals.

[0075] In some embodiments, a part of the pipeline of the second section 22 is a telescopic pipe, and the telescopic pipe can be deformed according to a certain length or angle. Setting a part of the pipeline of the second section 22 as a telescopic pipe can reduce the requirements for the relative position relationship between the pipeline in the aircraft wing 8 and the gas source 1, and facilitate the flow of gas from the gas source 1 to the pipeline in the aircraft wing 8. In some embodiments, the pipeline in the aircraft wing 8 is a flute-shaped pipe.

[0076] In some embodiments, the ice protection system of the aircraft wing further includes an ice protection switch 6, which has a first gear OFF, a second gear ON, and a third gear HI. By switching different gears of the ice protection switch 6, different ice protection strategies can be switched. Specifically, when the ice protection switch 6 is set to the first gear OFF, the ice protection controller 5 controls the ice protection valve 3 and the electric heating device 4 to close; when the ice protection switch 6 is set to the second gear ON, the ice protection controller 5 controls the ice protection valve 3 to open and the electric heating device 4 to close; when the ice protection switch 6 is set to the third gear HI, the ice protection controller 5 controls the ice protection valve 3 and the electric heating device 4 to open.

[0077] Referring to Figure 5 , when the meteorological condition is a non-icing meteorological condition, the ice protection switch 6 is in the first gear OFF. The meteorological condition being a non-icing meteorological condition includes: the meteorological condition itself being a non-icing meteorological condition, the meteorological condition changing from a first icing meteorological condition to a non-icing meteorological condition, and the meteorological condition changing from a second icing meteorological condition to a non-icing meteorological condition. When the meteorological condition changes from a non-icing meteorological condition to a first icing meteorological condition, the ice protection switch 6 switches from the first gear OFF to the second gear ON. When the meteorological condition changes from the first icing meteorological condition to the second icing meteorological condition, the ice protection switch 6 changes from the second gear ON to the third gear HI. It should be noted that when the meteorological condition changes from the first icing meteorological condition to the second icing meteorological condition, the temperature is usually lower than the first temperature (the first temperature signal will be sent). When the meteorological condition changes from the second icing meteorological condition to the first icing meteorological condition and the temperature is greater than the second temperature (the second temperature signal will be sent), the ice protection switch 6 changes from the third gear HI to the second gear ON.

[0078] Referring to Figure 4 , the embodiment of the present application also provides a control method for the ice protection system of the aircraft wing, which is applied to the ice protection system of the aircraft wing disclosed in any one of the above, and the control method includes:

[0079] S100: Obtain environmental condition information, where the environmental condition information characterizes the environmental state of the aircraft;

[0080] S200: Based on the environmental condition information, send an execution instruction to the ice protection valve and the electric heating device; the execution instruction is used to control the opening and closing states of the ice protection valve and the electric heating device.

[0081] In step S200, based on the environmental condition information, send an execution instruction to the ice protection valve and the electric heating device; the execution instruction is used to control the opening and closing states of the ice protection valve and the electric heating device.

[0082] In some embodiments, when the environmental condition information indicates the first environment, a closing instruction is sent to the anti-icing valve and the electric heating device; when the environmental condition information indicates the second environment, an opening instruction is sent to the anti-icing valve and a closing instruction is sent to the electric heating device, so that the gas with the first preset temperature supplied by the air source is transmitted to the aircraft wing through the anti-icing pipeline; when the environmental condition information indicates the third environment, an opening instruction is sent to the anti-icing valve and the electric heating device, so that when the gas passes through the electric heating device, the temperature is heated from the first preset temperature to the second preset temperature and then transmitted to the aircraft wing.

[0083] In some embodiments, the environmental condition information includes meteorological conditions; the meteorological conditions include non-icing weather, first icing weather, and second icing weather. When the meteorological condition is non-icing weather, the environmental condition information is the first environment. When the meteorological condition changes from non-icing weather to the first icing weather, the environmental condition information is the second environment. When the meteorological condition changes from the first icing weather to the second icing weather, the environmental condition information is the third environment.

[0084] In some other embodiments, the environmental condition information further includes temperature conditions; the anti-icing system of the aircraft wing further includes an anti-icing temperature sensor, which is arranged on the aircraft wing and used to collect and transmit the temperature conditions; the temperature conditions include a first temperature signal and a second temperature signal. When the temperature is lower than the first temperature, the anti-icing temperature sensor sends out the first temperature signal. When the temperature is higher than the second temperature, the anti-icing temperature sensor sends out the second temperature signal, and the first temperature is less than the second temperature. When the meteorological condition changes from the second icing weather to the first icing weather and the first temperature signal disappears and the second temperature signal is not sent, the environmental condition information is also the third environment; when the meteorological condition changes from the second icing weather to the first icing weather and the second temperature signal is sent, the environmental condition information is also the second environment.

[0085] With such a setting, when the meteorological conditions are non-icing, the aircraft is in the first environment, and both the anti-icing valve and the electric heating device are in the closed state. When the meteorological conditions change from non-icing to the first icing condition, the aircraft is in the second environment, the anti-icing valve opens, and the electric heating device remains closed. When the meteorological conditions change from the first icing condition to the second icing condition, the aircraft is in the third environment, the anti-icing valve remains open, and the electric heating device is turned on (it is worth mentioning that when the meteorological conditions change from the first icing condition to the second icing condition, the temperature is usually lower than the first temperature, and at this time the anti-icing temperature sensor will send out the first temperature signal). When the meteorological conditions change from the second icing condition to the first icing condition, the first temperature signal disappears, but the second temperature signal has not been sent yet, the aircraft is still in the third environment, and both the anti-icing valve and the electric heating device remain in the open state. When the meteorological conditions change from the second icing condition to the first icing condition and the second temperature signal is sent, the aircraft is in the second environment, the anti-icing valve remains open, and the electric heating device is turned off. When the aircraft is in the third environment, the heat generated by the electric heating wire in the electric heating device can heat the gas from the first preset temperature to the second preset temperature. The anti-icing performance of the anti-icing system is improved.

[0086] The embodiment of the present application also provides an aircraft, including the anti-icing system of the aircraft wing disclosed above.

[0087] In the description of the present application, the terms "first" and "second" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more features. In the description of the present application, "a plurality of" means two or more, unless otherwise specifically defined.

[0088] In the above embodiments, the descriptions of the various embodiments have their own emphases. For the parts not detailed in a certain embodiment, reference may be made to the relevant descriptions of other embodiments.

[0089] Among the embodiments, embodiments, and related technical features of the present application, they can be combined and replaced with each other without conflict.

[0090] The above are only the preferred embodiments of the present application, and do not impose any form of limitation on the present application. However, any simple modification, equivalent change, and modification made to the above embodiments based on the technical essence of the present application without departing from the content of the technical solution of the present application still fall within the scope of the technical solution of the present application.

Claims

1. An anti-icing system for an aircraft wing, characterized in that: include: An air source (1) and an anti-icing pipeline (2), wherein the air source (1) is used to supply air, the air having a first preset temperature, and the anti-icing pipeline (2) is connected to the air source (1) at one end and connected to a pipeline in an aircraft wing (8) at the other end; An anti-icing valve (3) is arranged on the anti-icing pipeline (2); An electric heating device (4) is arranged on the anti-icing pipeline (2); an anti-icing controller (5), electrically connected to the anti-icing valve (3) and the electric heating device (4); When the meteorological condition changes from non-icing weather to first icing weather, the anti-icing controller (5) is capable of controlling the anti-icing valve (3) to open, so that the gas having the first preset temperature is transmitted to the pipeline of the aircraft wing (8) through the anti-icing pipeline (2); When the meteorological conditions change from the first icing weather to the second icing weather, the anti-icing controller (5) can control the anti-icing valve (3) and the electric heating device (4) to open simultaneously, so that the gas is heated from the first preset temperature to the second preset temperature when passing through the electric heating device (4), and then transmitted to the pipeline in the aircraft wing (8), and the first preset temperature is lower than the second preset temperature.

2. The anti-icing system for an aircraft wing according to claim 1, characterized in that: The anti-icing pipeline (2) comprises: a first section (21) and a second section (22), the first section (21) being connected to the gas source (1), and the second section (22) being connected to a pipeline in the aircraft wing (8); The electric heating device (4) comprises: a ventilation pipe (41) and an electric heating wire (42); two ends of the ventilation pipe (41) are respectively connected to the first section (21) and the second section (22) to allow gas to pass through; the electric heating wire (42) is arranged in the ventilation pipe (41) and is electrically connected to the anti-icing controller (5); When the anti-icing controller (5) turns on the electric heating device (4), the electric heating wire (42) heats the gas having a first preset temperature passing through the ventilation pipe (41) to a second preset temperature.

3. The anti-icing system for an aircraft wing according to claim 2, characterized in that: The ventilation pipe (41) comprises an outer sleeve (411), a first liner pipe (412) and a second liner pipe (413) which are sequentially nested along the thickness direction of the pipe wall of the ventilation pipe (41); The electric heating wire (42) comprises a first portion (421) and a second portion (422), wherein the first portion (421) is disposed between the first inner liner tube (412) and the second inner liner tube (413), and the second portion (422) is connected to the first portion (421) and is disposed in a hollow area of ​​the second inner liner tube (413); The ventilation pipe (41) also includes an electrical connector (43), which passes through the outer sleeve (411), the first inner liner tube (412) and the second inner liner tube (413), and the electrical connector (43) electrically connects the electric heating wire (42) and the anti-icing controller (5).

4. The anti-icing system for an aircraft wing according to claim 3, characterized in that: The second portion (422) is arranged in a Y-shape, a triangle, a star shape or a spiral shape.

5. The anti-icing system for an aircraft wing according to claim 3, characterized in that: The outer casing (411) is a metal tube, and the first inner liner tube (412) and the second inner liner tube (413) are insulating tubes.

6. The anti-icing system for an aircraft wing according to claim 1, characterized in that: It also includes an anti-icing temperature sensor (7), wherein the anti-icing temperature sensor (7) is arranged on the aircraft wing (8); The anti-icing temperature sensor (7) is used to transmit a temperature condition, the temperature condition comprising a first temperature signal and a second temperature signal, when the temperature is lower than the first temperature, the anti-icing temperature sensor (7) sends the first temperature signal, when the temperature is higher than the second temperature, the anti-icing temperature sensor (7) sends the second temperature signal, the first temperature being lower than the second temperature; When the meteorological condition changes from the second icing meteorological condition to the first icing meteorological condition, and the first temperature signal disappears and the second temperature signal is not sent, the anti-icing controller (5) controls the anti-icing valve (3) and the electric heating device (4) to remain open; When the meteorological condition is converted from the second icing meteorological condition to the first icing meteorological condition and a second temperature signal is issued, the anti-icing controller (5) controls the anti-icing valve (3) to remain open and turns off the electric heating device (4).

7. The anti-icing system for an aircraft wing according to claim 1, characterized in that: Also included is an anti-icing switch (6), wherein the anti-icing switch (6) has a first gear position, a second gear position, and a third gear position; When the anti-icing switch (6) is in the first gear position, the anti-icing controller (5) controls the anti-icing valve (3) and the electric heating device (4) to be closed; When the anti-icing switch (6) is in the second gear position, the anti-icing controller (5) controls the anti-icing valve (3) to open and the electric heating device (4) to close; When the anti-icing switch (6) is in the third gear position, the anti-icing controller (5) controls the anti-icing valve (3) and the electric heating device (4) to open.

8. A method for controlling an anti-icing system of an aircraft wing, characterized in that: The anti-icing system for an aircraft wing according to any one of claims 1 to 7, wherein the control method comprises: Acquiring environmental condition information, wherein the environmental condition information represents an environmental state of the aircraft; Based on the environmental condition information, an execution instruction is sent to the anti-icing valve and the electric heating device; the execution instruction is used to control the opening and closing states of the anti-icing valve and the electric heating device.

9. The control method of the anti-icing system of the aircraft wing according to claim 8, characterized in that: sending an execution instruction to the anti-icing valve and the electric heating device based on the environmental condition information; The execution instruction for controlling the opening and closing states of the anti-icing valve and the electric heating device includes: If the environmental condition information is the first environment, sending a closing instruction to the anti-icing valve and the electric heating device; or; If the environmental condition information is the second environment, sending an opening instruction to the anti-icing valve and a closing instruction to the electric heating device, so that the gas supplied by the gas source is transmitted to the aircraft wing through the anti-icing pipeline; or; If the environmental condition information is the third environment, the opening instruction is sent to the anti-icing valve and the electric heating device, so that the gas is further heated when passing through the electric heating device and then transmitted to the aircraft wing.

10. The control method of the anti-icing system of the aircraft wing according to claim 9, characterized in that: The environmental condition information includes meteorological conditions; the meteorological conditions include non-icing meteorology, first icing meteorology and second icing meteorology; If the meteorological condition is non-icing weather, the environmental condition information is the first environment; If the meteorological condition is converted from non-icing weather to the first icing weather, the environmental condition information is the second environment; If the meteorological condition is converted from the first icing meteorology to the second icing meteorology, the environmental condition information is the third environment.

11. The control method of the anti-icing system of the aircraft wing according to claim 10, characterized in that: The environmental condition information also includes temperature conditions; the anti-icing system of the aircraft wing also includes an anti-icing temperature sensor, which is arranged on the aircraft wing and is used to collect and transmit the temperature conditions; the temperature conditions include a first temperature signal and a second temperature signal, when the temperature is lower than the first temperature, the anti-icing temperature sensor sends a first temperature signal, when the temperature is higher than the second temperature, the anti-icing temperature sensor sends a second temperature signal, and the first temperature is lower than the second temperature; If the meteorological condition changes from the second icing weather to the first icing weather, the first temperature signal disappears, and the second temperature signal is not sent, the environmental condition information is also the third environment; If the meteorological condition is converted from the second freezing weather to the first freezing weather and the second temperature signal is sent, the environmental condition information is also the second environment.

12. An aircraft, characterized in that: An anti-icing system for an aircraft wing comprising the invention as claimed in any one of claims 1 to 7.

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