A wing electric de-icing system and control method

Abstract

The present disclosure provides a wing electric de-icing system and a control method, comprising: a plurality of heating partitions; a plurality of heating films respectively arranged in the plurality of heating partitions, each heating film comprising a first heating band and a second heating band; and a controller comprising a first control channel and a second control channel which are independent of each other, the first control channel being electrically connected to the first heating band of each heating film respectively, and the second control channel being electrically connected to the second heating band of each heating film respectively; wherein the controller is configured to: when the first heating band and the second heating band are both in a normal state, control the first control channel and the second control channel to output heating power in a specified proportion, and when any one of them fails, control the control channel electrically connected to the heating band without failure to increase the heating power of the heating band without failure. Thus, when a local fault occurs in the heating film, the de-icing capability of the corresponding heating partition can still be maintained, thereby improving the reliability of the wing electric de-icing system.

Description

Technical Field

[0001] This disclosure relates to the field of aircraft anti-icing technology, specifically to a wing electric anti-icing system and control method. Background Technology

[0002] Wing anti-icing systems are used to prevent icing on the wing surface during flight, ensuring the aircraft's aerodynamic performance and flight safety. With the development of more-electric aircraft technology, electric heating for wing anti-icing has gradually become one of the mainstream solutions. Compared to traditional bleed-air anti-icing systems, wing electric anti-icing systems have certain advantages in terms of structural simplification, energy efficiency, and weight.

[0003] Existing wing electro-icing systems typically employ a zoned heating approach. Multiple heating zones are defined along the wing's leading edge, with an electrically heated film installed within each zone. Anti-icing is achieved by supplying power to each zone individually. For example, in some existing aircraft models, multiple heating areas are located on both sides of the wing, each further divided into sub-zones. The heating films within each sub-zone are usually arranged using a specific wiring method. When the heating film in a sub-zone malfunctions, the heating function of that sub-zone will fail.

[0004] In existing technologies, although wing electro-icing systems possess a certain degree of redundancy—for example, they can continue to operate even when a single zone or a group of symmetrical areas fails—the entire anti-icing system will malfunction when the number of heating film failures exceeds a preset limit. In this case, if an anti-icing system failure is detected before flight, the aircraft cannot perform flight missions under known or predicted icing conditions; if an anti-icing system failure occurs during flight, the aircraft must fly away from the icing area, thus adversely affecting flight safety and operational reliability.

[0005] Therefore, existing wing electro-icing systems have limited redundancy when the heating film fails, making it difficult to maintain the anti-icing function of each heating zone in the event of multiple zone or channel failures, resulting in insufficient safety and reliability.

[0006] In particular, in existing systems, when a heating film channel in a heating zone fails, it is usually difficult to effectively maintain the overall heating capacity of the heating zone through the remaining channels, which leads to a decrease or even failure of the anti-icing function of the heating zone. Summary of the Invention

[0007] The problem the invention aims to solve: To address the aforementioned issues, the purpose of this disclosure is to provide a wing electro-icing system and control method to maintain the anti-icing function of the corresponding heating zone in the event of a partial failure of the heating film, thereby improving the system's redundancy, reliability, and flight safety.

[0008] Technical means to solve the problem: This disclosure provides an electronic anti-icing system for an airfoil, comprising: multiple heating zones disposed on the airfoil; multiple heating films disposed in the multiple heating zones, each heating film including a first heating band and a second heating band, the first heating band and the second heating band being capable of independently providing the heating power required by the corresponding heating zone; and a controller for controlling the heating power of the heating films, including mutually independent first control channels and second control channels, the first control channels being electrically connected to the first heating band of each heating film, and the second control channels being electrically connected to the second heating band of each heating film; wherein, the controller is configured to: for any heating zone, when both the first heating band and the second heating band are in normal condition, control the first control channel and the second control channel to output a preset proportion of heating power to the corresponding first heating band and the second heating band respectively; when either the first heating band or the second heating band fails, control the control channel electrically connected to the fault-free heating band to increase the heating power of the fault-free heating band.

[0009] Preferably, the controller is configured to: for any of the heating zones, when both the first heating band and the second heating band are in normal condition, control the first control channel and the second control channel to output 50% of the heating power required by the heating zone to the corresponding first heating band and the second heating band, respectively.

[0010] Preferably, the controller is configured to: for any of the heating zones, when either the first heating belt or the second heating belt fails, control the control channel electrically connected to the fault-free heating belt to output 100% of the heating power required by the heating zone to the fault-free heating belt.

[0011] Preferably, the controller is further configured to: for any of the heating zones, when both the first heating belt and the second heating belt fail, stop heating of the heating zone and the heating zone symmetrically arranged on the other side of the wing.

[0012] Preferably, the system further includes temperature sensors, which are respectively disposed in the heating zones and electrically connected to the first control channel and the second control channel of the controller. The controller is configured to: determine the resistance value of each heating zone based on the voltage value at both ends of each heating zone and the current value flowing through each heating zone, compensate the resistance value based on the temperature information collected by the temperature sensors, and compare the compensated resistance value with a preset limit value to determine whether each heating zone has malfunctioned.

[0013] Preferably, the first heating band and the second heating band of each heating film are arranged in a double-wound manner with uniform spacing within the corresponding heating zone.

[0014] Preferably, the rated heating power of the first heating band and the second heating band of each heating film are equivalent.

[0015] Preferably, the heating film further includes: a heat equalization layer disposed on the side of the first heating band and the second heating band away from the wing, for distributing heat evenly within the heating zone; and a heat insulation layer disposed on the side of the first heating band and the second heating band close to the wing, for preventing heat from being conducted into the wing.

[0016] Preferably, the first control channel and the second control channel are dissimilar control channels, and the two control channels communicate with each other via a bus to exchange their status information.

[0017] This disclosure also provides a wing electro-icing control method, applied to the aforementioned wing electro-icing system, comprising: acquiring status information of the first heating band and the second heating band in each of the heating zones; based on the status information, for any heating zone, when both the first heating band and the second heating band are in a normal state, controlling the first control channel and the second control channel to output a preset proportion of heating power to the corresponding first heating band and the second heating band respectively; when either the first heating band or the second heating band fails, controlling the control channel electrically connected to the fault-free heating band to increase the heating power of the fault-free heating band; when both the first heating band and the second heating band fail, stopping the heating of the heating zone and the heating zone symmetrically arranged on the other side of the wing.

[0018] Preferably, the preset ratio is 50%.

[0019] Preferably, for any of the heating zones, when either the first heating belt or the second heating belt fails, the control channel electrically connected to the fault-free heating belt outputs 100% of the heating power required by the heating zone to the fault-free heating belt.

[0020] Preferably, the acquisition of status information includes: determining the resistance value of each heating element based on the voltage value at both ends of each heating element and the current value flowing through each heating element, compensating the resistance value based on temperature information, and comparing the compensated resistance value with a preset limit value to determine whether each heating element has malfunctioned.

[0021] Therefore, compared with the prior art, this disclosure has the following beneficial effects: (1) This disclosure provides a first heating belt and a second heating belt in each heating zone, and both of them have the rated heating capacity to independently meet the anti-icing requirements of the corresponding heating zone. When any heating belt fails, the heating power of the fault-free heating belt is increased to maintain the anti-icing function of the heating zone, so that a single heating belt failure will not cause the heating zone to fail immediately, which significantly improves the local redundancy of the wing electric anti-icing system.

[0022] (2) This disclosure dynamically allocates the heating power of each heating zone. Under normal conditions, the heating power is allocated proportionally, and under single-channel failure, the heating power is concentrated on the fault-free heating zone. This enables the reconstruction of heating capacity without adding additional heating units, and improves the system's ability to maintain anti-icing function under various fault conditions.

[0023] (3) This disclosure provides a heat-spreading layer on the outside of the heating band and a heat-insulating layer on the inside, so that the heat generated by the heating band can be evenly diffused within the corresponding heating zone and the heat conduction to the interior of the wing is restricted, thereby allowing the heat to be preferentially transferred to the outer surface of the wing. Through the combined effect of the heat-spreading layer and the heat-insulating layer, a uniform temperature distribution can still be formed within the corresponding heating zone when a single heating band is working, thus structurally ensuring the heating effect when a single channel is working.

[0024] (4) This disclosure improves the accuracy of fault detection by calculating the resistance of the heating belt based on voltage, current and temperature information, and judging the working status of the heating belt accordingly. This enables early identification of heating belt abnormalities and further enhances the reliability of the system.

[0025] (5) When all heating zones fail, this disclosure stops heating of the corresponding heating zone and the heating zone symmetrically located on the other side of the wing, thereby ensuring the consistency of the heating state on both sides of the wing, avoiding adverse effects on flight performance due to local heating asymmetry, and improving the safety of the system under extreme failure conditions.

[0026] (6) By setting up independent and dissimilar control channels and communicating with each other via a bus to exchange status information, this disclosure improves the fault tolerance of the control system and reduces the risk of system failure due to a single control channel failure, thereby further improving the overall reliability of the wing electric anti-icing system.

[0027] In summary, this disclosure, through the synergy of structural design and control strategies, enables the maintenance of heating zone anti-icing function even in the event of single-channel or even multi-channel failure of the heating film, thereby significantly improving the reliability and safety of the wing's electric anti-icing system. Attached Figure Description

[0028] Figure 1This is a schematic diagram of the overall structure of an airfoil electro-icing system according to one embodiment of the present disclosure.

[0029] Figure 2 This is a top view of the wiring structure of the heating film in one embodiment of the present disclosure.

[0030] Figure 3 This is a cross-sectional view of the layer structure of the heating film in one embodiment of the present disclosure.

[0031] Figure 4 This is a flowchart of the heating power control in a wing electric anti-icing control method according to one embodiment of the present disclosure.

[0032] Figure 5 This is a flowchart illustrating the heating film fault judgment in a wing electro-icing control method according to an embodiment of the present disclosure. Detailed Implementation

[0033] The embodiments of this disclosure will now be described in detail with reference to the accompanying drawings. Those skilled in the art should understand that the following embodiments are for illustrative purposes only and are not intended to limit the scope of protection of this disclosure. The same or corresponding reference numerals in the figures denote the same components, and repeated descriptions are omitted. The components of the embodiments of this disclosure described and shown in the accompanying drawings can generally be arranged and designed in various different configurations. All other embodiments obtained by those skilled in the art based on the embodiments of this disclosure without inventive effort are within the scope of protection of this disclosure.

[0034] like Figure 1 As shown, this disclosure provides a wing electro-icing system, which is installed in the area of ​​the wing that needs to be heated for anti-icing (hereinafter sometimes referred to as the heating area) to heat the wing surface to suppress or eliminate icing, thereby ensuring the aerodynamic performance and flight safety of the wing. The wing electro-icing system includes multiple heating films, multiple temperature sensors, and a controller.

[0035] In this embodiment, the area on the wing requiring heating is symmetrically divided into multiple independent heating zones. Specifically, in this embodiment, the multiple heating zones are symmetrically arranged on both sides of the wing, meaning that each heating zone on one side of the wing has a corresponding heating zone on the other side. It should be noted that the heating zones are functional divisions of the wing area based on heating requirements, not independent structural components, and their specific division method can be adjusted according to actual needs. For example, the multiple heating zones can be sequentially divided along the extension direction of both sides of the wing to form multiple independent heating zones.

[0036] Multiple heating films are respectively disposed in multiple heating zones, covering at least a portion of the corresponding heating zone, to achieve heating of different heating zones of the wing. Specifically, each heating film includes a first heating band ChA and a second heating band ChB, which extend within the corresponding heating zone and form two independent heating paths. In this embodiment, the rated heating power of the first heating band ChA and the second heating band ChB is equivalent, and each can independently meet the heating requirements of the corresponding heating zone. That is, even when only the first heating band ChA or only the second heating band ChB is working, a temperature distribution that meets the anti-icing requirements can still be formed within the corresponding heating zone, thereby maintaining the anti-icing function of that heating zone.

[0037] like Figure 2 The wiring structure of the heating film is illustrated below.

[0038] In this embodiment, to ensure a relatively uniform temperature distribution within the corresponding heating zone under different operating conditions, the first heating band ChA and the second heating band ChB are preferably arranged in a double-wound, uniformly spaced configuration within the heating film. Double-wound refers to the first heating band ChA and the second heating band ChB being laid out in a reciprocating manner within the corresponding heating zone, and spatially staggered, so that all locations within the heating zone are simultaneously heated by both heating bands ChA and ChB. That is, even if one heating band fails, the other, due to its uniform winding distribution, can still generate continuous and relatively uniform heat output throughout the entire heating zone, avoiding the occurrence of localized overheating or undercooling areas.

[0039] With the above arrangement, the first heating band ChA and the second heating band ChB form complementary heating paths within the heating zone. Under normal operating conditions, the first heating band ChA and the second heating band ChB can jointly provide a relatively uniformly distributed heat source to the corresponding heating zone; when one heating band fails, the other heating band can still cover the main area of ​​the corresponding heating zone, thereby forming a continuous heating area within the heating zone and maintaining a temperature distribution that meets anti-icing requirements.

[0040] In addition, in other embodiments, the arrangement of the first heating band ChA and the second heating band ChB can also be adjusted according to actual needs. For example, different arrangement forms or spacing settings can be adopted, as long as the anti-icing function of the corresponding heating zone can be maintained when a single heating band is working.

[0041] For ease of description, the structure formed by the double-wound first heating band ChA and the second heating band ChB is sometimes referred to as the heating layer.

[0042] like Figure 3 The layer structure of the heating film is illustrated below.

[0043] In this embodiment, to further improve the heating efficiency and temperature distribution characteristics of the heating film, the heating film may further include a heat-spreading layer and a heat-insulating layer. The heating layer is disposed between the heat-spreading layer and the heat-insulating layer. The heat-spreading layer is located on the side of the heating layer away from the wing, and is used to diffuse the heat generated by the first heating zone ChA and the second heating zone ChB within the corresponding heating zones, thereby reducing local temperature differences and improving the temperature uniformity of the heating area. For example, the heat-spreading layer can be formed of a material with good thermal conductivity (such as copper, aluminum foil, or thermally conductive graphite film). The heat-insulating layer is located on the side of the heating layer closer to the wing, and is used to prevent heat from being conducted into the wing, thereby allowing more heat to be released towards the outer surface of the wing, improving thermal energy utilization efficiency. For example, the heat-insulating layer can be formed of a material with low thermal conductivity (such as glass fiber, aerogel, or polyimide foam).

[0044] Through the combined action of the heat spreader and the insulation layer, the heat generated by the heating belt can diffuse within the corresponding heating zone and form a relatively uniform temperature distribution, while reducing heat loss into the wing interior. Therefore, even when only one heating belt is operational, the temperature distribution within that heating zone can still meet anti-icing requirements, thereby further ensuring the anti-icing function of the heating zone.

[0045] In addition, the heating film may also include a coating layer and a load-bearing layer. The coating layer is located on the side of the heat spreader away from the heat-generating layer, and is used to form the outer surface of the wing and meet environmental adaptability requirements. The load-bearing layer is located on the side of the insulation layer away from the heat-generating layer, and is used to provide structural support for the heating film and for connection with the wing structure.

[0046] Therefore, in this embodiment, from the side closest to the wing to the side furthest from the wing, the heating film can sequentially include a load-bearing layer, a heat insulation layer, a heating layer, a heat spreader layer, and a coating layer. The heating layer contains a first heating band ChA and a second heating band ChB. For example, the layers can be connected by bonding, lamination, or integral molding. Thus, the heating film in this embodiment has a multi-layer structure, shown as a five-layer structure in the illustrated example, but is not limited to this. In other embodiments, the number of layers, the thickness of each layer, and the interlayer combination relationship can be adjusted according to actual needs, as long as the first heating band ChA and the second heating band ChB can achieve their heating function. Preferably, the heat spreader layer and the heat insulation layer respectively achieve heat diffusion and heat blocking. Furthermore, in other embodiments, the number of layers, the thickness, and the arrangement of the heat spreader layer and the heat insulation layer can be adjusted according to actual applications, as long as effective heat transfer to the outer surface of the wing and heat suppression to the interior of the wing can be achieved.

[0047] return Figure 1 The wing electro-icing system is equipped with multiple temperature sensors. In this embodiment, the multiple temperature sensors are respectively installed in each heating zone to obtain the temperature information of the corresponding heating zone. The temperature sensors can be installed near the location of the heating film, or in a location that can reflect the temperature state of the heating area, thereby achieving effective monitoring of the temperature of the heating area.

[0048] Furthermore, the number of temperature sensors installed in each heating zone is unlimited. For example, multiple temperature sensors can be installed at different locations within the same heating zone to obtain the temperature status at different locations within that heating zone, thereby improving the accuracy of temperature monitoring. As another example, in this embodiment, each heating zone is equipped with two temperature sensors, which are respectively installed at positions corresponding to the first heating zone ChA and the second heating zone ChB, thereby obtaining temperature information related to the first heating zone ChA and the second heating zone ChB respectively.

[0049] The wing electro-icing system includes a controller. In this embodiment, the controller controls the heating power of each heating film and is connected to multiple heating films and multiple temperature sensors. Specifically, the controller is connected to the first heating zone ChA and the second heating zone ChB in each heating film to provide heating power to each heating zone. Simultaneously, the controller is connected to multiple temperature sensors located within each heating zone to acquire temperature information for the corresponding heating zone.

[0050] In addition, the controller is also used to acquire the voltage values ​​at both ends of each heating zone and the current values ​​flowing through each heating zone, thereby monitoring the operating status of each heating zone. Based on the temperature, voltage, and current information, the controller makes a comprehensive judgment on the operating status of each heating zone and adjusts the heating power accordingly.

[0051] The controller includes a first control channel A and a second control channel B, which are independently configured to form a dual-channel control architecture. Preferably, the first control channel A and the second control channel B are dissimilar control channels to reduce the impact of common-cause failures on the system (e.g., the same hardware design flaws or software programming errors). Furthermore, the first control channel A and the second control channel B can interact via a communication link to exchange their acquired status information. This allows the other control channel to acquire relevant information and respond when either control channel experiences an anomaly, improving the fault tolerance and operational reliability of the control system.

[0052] In this embodiment, the first control channel A is connected to the first heating band ChA in each heating film, and the second control channel B is connected to the second heating band ChB in each heating film, so that the first heating band ChA and the second heating band ChB in the same heating zone are controlled by different control channels. Based on this connection relationship, a dual-channel heating structure consisting of two heating bands and two control channels is formed in each heating zone.

[0053] In this dual-channel structure, the first control channel A and the second control channel B can independently adjust the heating power of their respective heating bands. Based on the operating status of each heating band, the controller adjusts the distribution of heating power between the first heating band ChA and the second heating band ChB, thereby redistributing heating capacity under different operating conditions. For example, under normal operating conditions, the two heating bands output heating power according to a preset ratio; if one heating band malfunctions, the controller increases the heating power of the other, undamaged heating band to maintain the anti-icing function of the corresponding heating zone; if both heating bands malfunction, the controller stops heating the corresponding heating zone and can further stop heating the other symmetrically positioned heating zone to ensure consistent heating on both sides of the wing.

[0054] The following, combined with Figure 4 The control logic of the controller is explained.

[0055] After the wing's electric anti-icing system is powered on, the controller first performs a power-on self-test to confirm the system's basic operating status. After completing the power-on self-test, the controller enters the heating film status judgment step to determine the working status of the heating film within the current heating zone.

[0056] In the heating film status determination step, the controller first determines whether the heating film is faulty. When the determination result is that the heating film is not faulty, the controller controls the first control channel A and the second control channel B to output heating power at preset ratios. In this embodiment, the target power of the first control channel A is 50%, and the target power of the second control channel B is 50%, so that the first heating band ChA and the second heating band ChB jointly provide the heating capacity required for this heating zone.

[0057] When the determination result indicates a fault in the heating film, and the fault is a single-channel fault, the system further determines whether the first heating zone ChA or the second heating zone ChB is faulty. If the determination result indicates a fault in the first heating zone ChA, the controller sets the target power of the first control channel A to 0%, while simultaneously setting the target power of the second control channel B to 100%, with the second heating zone ChB solely responsible for heating that zone. If the determination result indicates a fault in the second heating zone ChB, the controller sets the target power of the first control channel A to 100%, while simultaneously setting the target power of the second control channel B to 0%, with the first heating zone ChA solely responsible for heating that zone.

[0058] When the determination result indicates a fault in the heating film, and both the first heating zone ChA and the second heating zone ChB are faulty, the controller controls the target power of both the first control channel A and the second control channel B to 0%, stops heating in that heating zone, and triggers an anti-icing fault alarm. Preferably, the controller can further stop heating in the heating zone symmetrically located on the other side of the wing to ensure consistent heating on both sides of the wing. Specifically, the target power of both the first control channel A and the second control channel B in the heating zone on the other side can be controlled to 0%.

[0059] The following, combined with Figure 5 The process of diagnosing faults in the heating film is explained.

[0060] First, the controller collects the temperature, voltage, and current information of the heating film. The temperature information is obtained by a temperature sensor located within the heating zone, the voltage information is the voltage value across the heating band, and the current information is the current flowing through the heating band.

[0061] After acquiring voltage and current information, the controller calculates the first heating zone ChA and the second heating zone ChB based on the acquired voltage and current values, respectively. Figure 5 The resistance value is uniformly represented as that of the heating film.

[0062] Subsequently, the controller performs temperature compensation on the calculated resistance value based on the collected temperature information to eliminate the influence of temperature changes on the resistance judgment, thereby obtaining the compensated resistance value. Specifically, the controller can correct the calculated resistance value according to the resistance change relationship of the heating element at different temperatures, or convert the calculated resistance value into an equivalent resistance value at a preset reference temperature. The purpose of this temperature compensation is that the resistance value of the heating element increases with the increase of temperature. If the resistance value at high temperature is directly compared with the preset limit value at room temperature, it may lead to a false judgment of 'excessive resistance' for a normally operating heating element. Through temperature compensation, the resistance values ​​at different temperatures can be converted to the same reference temperature (such as 25°C), thereby accurately determining whether the resistance has actually changed due to a fault (such as an open circuit or a partial short circuit).

[0063] After obtaining the compensated resistance value, the controller determines the state of the heating film accordingly. Specifically, the controller compares the compensated resistance values ​​of the first heating band ChA and the second heating band ChB with preset limits to determine whether the resistance of the corresponding heating band exceeds the limit.

[0064] When the compensated resistance value of at least one of the first heating zone ChA and the second heating zone ChB exceeds the limit value, the controller determines that the corresponding heating film has malfunctioned and outputs the corresponding fault signal.

[0065] When the compensated resistance values ​​of the first heating band ChA and the second heating band ChB do not exceed the limit, the controller determines that the heating film is in normal condition.

[0066] In other embodiments, the division of each heating zone can be adjusted according to the wing structure and anti-icing requirements, and is not limited to the division along the wing extension direction.

[0067] The above control method can be executed by a controller, and its specific process can be implemented by a program or logic circuit in the controller. In other embodiments, the first control channel and the second control channel in the controller can also adopt different implementation methods, such as hardware dissimilar structures or software dissimilar structures, to further improve the reliability of the system.

[0068] This disclosure achieves heating capacity reconfiguration under different operating conditions by setting a first heating zone ChA and a second heating zone ChB in each heating zone, and by adopting a dual-channel control structure and a heating power distribution method based on the operating state of the heating zones. It has the following beneficial effects: By setting up a first heating belt ChA and a second heating belt ChB within the same heating zone, each heating belt can independently provide the heating power required by that heating zone. Thus, if one heating belt fails, the other heating belt can still maintain the anti-icing function of that heating zone, improving the redundancy and reliability of the system.

[0069] By setting up a first control channel and a second control channel to be connected to the first heating band ChA and the second heating band ChB respectively, the two heating bands are controlled independently. Combined with the non-similar channel structure, the impact of common cause failures on the system is effectively reduced, thereby further improving the safety and reliability of the system operation.

[0070] By allocating heating power to the two heating belts according to a preset ratio under normal operating conditions, and increasing the heating power of the other heating belt when one heating belt fails, the heating capacity can be dynamically allocated according to the operating conditions. This maintains the anti-icing capability of the heating zone under different fault conditions and avoids a significant decrease in anti-icing performance due to local failure.

[0071] By calculating the resistance value based on the voltage and current values ​​at both ends of the heating belt and compensating for the resistance value in combination with temperature information, the working status of the heating belt can be accurately determined under different temperature conditions, thereby improving the accuracy and stability of fault detection.

[0072] By judging the resistance of the first heating zone ChA and the second heating zone ChB respectively, the specific faulty heating zone can be identified, thereby enabling differentiated heating power allocation for different fault conditions and improving the control accuracy and response capability of the system.

[0073] By stopping heating of the corresponding heating zone when both heating zones fail, and further stopping heating of the symmetrical heating zone on the other side of the wing, the heating state of both sides of the wing is kept consistent, thereby avoiding aerodynamic performance deviations caused by asymmetrical heating and improving flight safety.

[0074] By setting a heat equalization layer and a heat insulation layer in the heating film, the heat generated by the heating band can be effectively diffused to the outer surface of the wing, while reducing heat loss to the interior of the wing, thereby improving the thermal energy utilization efficiency and improving the temperature uniformity within the heating zone.

[0075] By employing a double-winding arrangement with uniform spacing, the first heating band ChA and the second heating band ChB are spatially staggered, ensuring that each location can be heated by at least one heating band. Even if only one heating band is working, a continuous heating area can be formed within the corresponding heating zone, improving the stability of the anti-icing effect.

[0076] The above embodiments are only used to illustrate the technical solutions of this disclosure, and are not intended to limit this disclosure. Those skilled in the art can modify the above embodiments or make equivalent substitutions for some of the technical features without departing from the technical concept of this disclosure, and such modifications or substitutions should not depart from the protection scope of this disclosure.

[0077] It should be understood that the above embodiments further illustrate the purpose, technical solution, and beneficial effects of this disclosure, but this disclosure is not limited to the specific embodiments described above. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this disclosure should be included within the protection scope of this disclosure.

Claims

1. A wing electro-icing system, characterized in that, include: Multiple heating zones are located on the wings; Multiple heating films are respectively disposed in multiple heating zones. Each heating film includes a first heating band and a second heating band. Both the first heating band and the second heating band can independently provide the heating power required by the corresponding heating zone. as well as The controller, which controls the heating power of the heating film, includes a first control channel and a second control channel that are independent of each other. The first control channel is electrically connected to the first heating band of each heating film, and the second control channel is electrically connected to the second heating band of each heating film. The controller is configured as follows: For any of the heating zones, when both the first heating belt and the second heating belt are in normal condition, the first control channel and the second control channel are controlled to output a specified proportion of heating power to the corresponding first heating belt and the second heating belt respectively; If either the first heating band or the second heating band fails, the control channel electrically connected to the fault-free heating band increases the heating power of the fault-free heating band.

2. The wing electro-icing system according to claim 1, characterized in that, The controller is configured to: For any of the heating zones, when both the first heating band and the second heating band are in normal condition, the first control channel and the second control channel are controlled to output 50% of the heating power required by the heating zone to the corresponding first heating band and the second heating band, respectively.

3. The wing electro-icing system according to claim 1 or 2, characterized in that, The controller is configured to: For any of the heating zones, if either the first heating zone or the second heating zone fails, the control channel electrically connected to the fault-free heating zone outputs 100% of the heating power required by the heating zone to the fault-free heating zone.

4. The wing electro-icing system according to claim 1, characterized in that, The controller is also configured to: For any of the heating zones, if both the first heating belt and the second heating belt fail, heating of that heating zone and the heating zone symmetrically located on the other side of the wing shall be stopped.

5. The wing electro-icing system according to claim 1, characterized in that, It also includes temperature sensors, which are respectively installed in the heating zones and connected to the controller. The controller is configured to: The resistance value of each heating element is determined based on the voltage value at both ends of each heating element and the current value flowing through each heating element. The resistance value is then compensated based on the temperature information collected by the temperature sensor. The compensated resistance value is compared with a preset limit value to determine whether each heating element has malfunctioned.

6. The wing electro-icing system according to claim 1, characterized in that, The first heating band and the second heating band of each heating film are arranged in a double-wound manner with uniform spacing within the corresponding heating zone.

7. The wing electro-icing system according to claim 1, characterized in that, The rated heating power of the first heating band and the second heating band of each heating film is equivalent.

8. The wing electro-icing system according to claim 1, characterized in that, The heating film also includes: A heat equalization layer, disposed on the side of the first and second heating bands away from the wing, is used to uniformly distribute heat within the heating zone; and A heat insulation layer is disposed on the side of the first heating band and the second heating band near the wing to prevent heat from being conducted into the wing.

9. The wing electro-icing system according to claim 1, characterized in that, The first control channel and the second control channel are dissimilar control channels, and the two control channels communicate with each other via a bus to exchange their status information.

10. A method for controlling wing electrical anti-icing, characterized in that, The wing electro-icing system applied to any one of claims 1 to 9 comprises: Obtain the status information of the first heating band and the second heating band in each of the heating zones; According to the status information, for any heating zone, when both the first heating belt and the second heating belt are in normal condition, the first control channel and the second control channel are controlled to output a preset proportion of heating power to the corresponding first heating belt and the second heating belt respectively; If either the first heating band or the second heating band fails, the control channel electrically connected to the fault-free heating band increases the heating power of the fault-free heating band. When both the first heating band and the second heating band fail, heating of the heating zone and the heating zone symmetrically located on the other side of the wing shall be stopped.

11. The wing electro-icing control method according to claim 10, characterized in that, The preset ratio is 50%.

12. The wing electro-icing control method according to claim 10, characterized in that, For any of the heating zones, if either the first heating zone or the second heating zone fails, the control channel electrically connected to the fault-free heating zone outputs 100% of the heating power required by the heating zone to the fault-free heating zone.

13. The wing electro-icing control method according to claim 10, characterized in that, The acquired status information includes: The resistance value of each heating element is determined based on the voltage value at both ends of each heating element and the current value flowing through each heating element. The resistance value is then compensated based on temperature information, and the compensated resistance value is compared with a preset limit value to determine whether each heating element has malfunctioned.

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