Reconfigurable intelligent aircraft de-icing system and method

Abstract

The application belongs to the technical field of aircraft deicing, and discloses a reconfigurable intelligent aircraft deicing system and method. The hidden deicing liquid nozzle unit sprays deicing liquid on different deicing yard areas divided by different pressure nozzle assemblies to perform aircraft engine deicing operation; the deicing detection unit adopts image recognition technology to collect the ice and snow coverage area, thickness and type of the aircraft body in real time, and determines the aircraft model and parking position; the deicing waste liquid detection unit detects the physical property parameters of the deicing waste liquid during deicing operation in real time; the intelligent control unit controls the flow, temperature, pressure and angle of the nozzle assembly with the same pressure in real time, so as to optimize the deicing efficiency; the deicing liquid supply unit, deicing liquid conveying unit and deicing liquid recovery unit jointly supply and recycle the deicing liquid without interruption. The application greatly improves the deicing efficiency of the aircraft, greatly avoids the possibility of secondary icing of the aircraft, and maximally avoids the invalid energy loss.

Description

Technical Field

[0001] This invention belongs to the field of aircraft de-icing technology, and particularly relates to a reconfigurable intelligent aircraft de-icing system and method. Background Technology

[0002] During autumn and winter, temperatures can drop to tens of degrees below zero Celsius, often accompanied by rain and snow. This severe weather makes aircraft surfaces prone to frost and ice formation. Icing on aircraft wings drastically reduces lift, icing on engine components severely impairs aerodynamics, and icing on sensors can cause instrument malfunctions. In severe cases, it can even lead to serious flight accidents. To date, an aircraft-related accident occurs almost every few years; therefore, de-icing and anti-icing of aircraft surfaces are crucial for safe flight. Liquid anti-icing, a primary physical de-icing method, involves mixing alcohol and water in a specific ratio, heating the mixture, and spraying it onto the aircraft surface to remove ice, depending on the specific icing conditions and weather. Large hub airports mainly use de-icing fluid centralized proportioning and mixing heating stations to carry out de-icing operations on aircraft before takeoff using de-icing trucks and refill trucks. This operation method has the following disadvantages: (1) The capacity of the refill truck is limited. Once the internal de-icing fluid is completely consumed, it cannot be replenished quickly, and may even cause secondary icing of the aircraft, prolonging the de-icing time; (2) The preheated de-icing fluid will generate a lot of energy loss during the transfer process, which is not conducive to improving the efficiency of de-icing operations; (3) The refill truck frequently shuttles in the airport, which increases the scheduling workload of airport management and poses safety hazards; (4) It is difficult to meet the de-icing fluid volume control requirements of different parts of the aircraft and different icing conditions, resulting in ineffective consumption and waste of de-icing fluid.

[0003] To address the shortcomings of existing de-icing methods, Chinese patent CN106477052A, published on March 8, 2017, discloses a rail-mounted robotic arm de-icing system for aircraft; Chinese patent CN112455718A, published on March 9, 2021, discloses a novel method and device for spraying de-icing fluid on aircraft. Both of these prior art technologies propose using robotic arm systems for de-icing. The disadvantages of this de-icing method are: the movement control of the robotic arm is complex, and the de-icing area that each robotic arm can operate on is limited, and some parts of the aircraft may be in de-icing blind spots; the movement of the robotic arm requires a certain amount of space, so the number of robotic arms that can be installed at one de-icing position is limited, resulting in low de-icing efficiency. Summary of the Invention

[0004] To overcome the problems existing in related technologies, the present invention discloses a reconfigurable intelligent aircraft de-icing system and method.

[0005] The technical solution is as follows: a reconfigurable intelligent aircraft de-icing system, comprising:

[0006] The de-icing fluid concealed nozzle unit is used to achieve spray de-icing at different pressures in different de-icing areas, and automatically sinks and hides after de-icing is completed;

[0007] The de-icing detection unit is used to collect data on the area, thickness, and type of ice and snow covering the fuselage in real time, and to determine the aircraft type and parking location.

[0008] The de-icing waste liquid detection unit is located on the ground below the nose of the aircraft, the two wings of the aircraft, the fuselage of the aircraft, and the tail of the aircraft, and is used to detect the physical properties of the de-icing waste liquid during de-icing operations in real time.

[0009] The intelligent control unit is used to control the flow rate, temperature, pressure, and angle of the nozzle assembly at different pressures in real time to optimize the de-icing efficiency.

[0010] The de-icing fluid supply unit is used for the preparation and mixing of de-icing fluids of different concentrations.

[0011] The de-icing fluid transport unit is used to heat the de-icing fluid and transport it to different de-icing areas;

[0012] The de-icing fluid recovery unit is used for the filtration and repurification of waste liquid residues.

[0013] The de-icing fluid supply unit, de-icing fluid transportation unit, and de-icing fluid recovery unit work together to ensure uninterrupted supply and recycling of de-icing fluid.

[0014] In one embodiment, the de-icing fluid concealed nozzle unit includes: a high-pressure nozzle assembly, a medium-pressure nozzle assembly, and a low-pressure nozzle assembly;

[0015] The different de-icing areas include:

[0016] I. De-icing area, located at the front end of the de-icing pad, is equipped with medium-pressure nozzle assemblies, which are distributed in an arc.

[0017] II. De-icing area, located in the front middle of the de-icing pad, is equipped with high-pressure nozzle assemblies. The nozzles of the high-pressure nozzle assemblies are arranged in two rows along the horizontal direction, with each row of high-pressure nozzle assemblies arranged on the left and right sides.

[0018] De-icing zone III is located in the middle of the de-icing pad and is equipped with low-pressure nozzle assemblies. De-icing zone III is located between the two rows of high-pressure nozzle assemblies in de-icing zone II.

[0019] The IV de-icing zone is located behind the III de-icing zone and is equipped with high-pressure nozzle assemblies. The high-pressure nozzle assemblies on the left and right sides are arranged in two columns along the longitudinal direction.

[0020] V. The de-icing area is located on the left and right sides of the de-icing pad, and high-pressure nozzle assemblies are installed, arranged longitudinally, with one row on each side.

[0021] In one embodiment, a track is laid below the medium-pressure nozzle assembly and slides longitudinally along the track to spray de-icing fluid to complete the de-icing operation on the aircraft nose.

[0022] In one embodiment, a track is laid below the high-pressure nozzle assembly installed in the II de-icing area and slides longitudinally along the track to spray de-icing fluid to complete the aircraft wing de-icing operation.

[0023] In one embodiment, the low-pressure nozzle assembly is arranged in an array within two rectangles on the left and right sides to spray de-icing fluid to complete the aircraft engine de-icing operation.

[0024] The high-pressure nozzle assembly installed in the IV de-icing zone slides longitudinally along the track to spray de-icing fluid to complete the aircraft tail de-icing operation;

[0025] The high-pressure nozzle assembly installed in the V de-icing area slides laterally along the track to spray de-icing fluid and complete the de-icing operation on the aircraft cabin surface.

[0026] Both the high-pressure nozzle assembly and the medium-pressure nozzle assembly adopt a concealable sliding rail type and a movable nozzle assembly. A linkage cover plate is installed on the ground surface above, and a track for controlling the sliding is connected below. The track is installed on the lifting base.

[0027] The low-pressure nozzle assembly is a fixed nozzle assembly, which is fixedly installed on the lifting base and has a linkage cover plate installed on top.

[0028] In one embodiment, the de-icing detection unit includes an image acquisition device installed at the front end of the de-icing pad and a position sensor integrated into the de-icing waste liquid detection unit. The image acquisition device is used to collect the area, thickness and type of ice and snow coverage on the fuselage in real time, and to cooperate with the position sensor to determine the aircraft type and parking position.

[0029] The de-icing waste liquid detection unit integrates a refractive index sensor, a temperature sensor, and a viscosity sensor. A linkage cover plate is installed on the ground above the de-icing waste liquid detection unit and is fixedly installed on the base that controls the lifting.

[0030] The de-icing supply unit includes a water tank and a propylene glycol solution tank. The outlet of the water tank is connected to a water flow control valve, and the outlet of the propylene glycol solution tank is connected to a propylene glycol solution flow control valve. The outlets of the two flow control valves are connected to a de-icing fluid mixing tank. A de-icing fluid mixing controller controls the two flow control valves. By processing the concentration information of the de-icing fluid mixing tank detected by the concentration detection device, the ratio of water to propylene glycol solution is calculated, and the flow rates of the two liquids are controlled. The outlet of the de-icing fluid mixing tank is connected to a high-pressure water pump on the de-icing fluid transport unit. The power provided by the high-pressure water pump is used to transport the de-icing fluid from the de-icing fluid supply unit to the de-icing fluid concealed nozzle units on each de-icing pad.

[0031] Another object of the present invention is to provide a reconfigurable intelligent aircraft de-icing method, which, using the aforementioned reconfigurable intelligent aircraft de-icing system, includes the following steps:

[0032] S1, detect whether there are aircraft parked on the de-icing pad;

[0033] S2, activate the de-icing system to detect aircraft type and parking location and collect icing data;

[0034] S3. Based on the collected data, the particle swarm optimization algorithm is used to perform iterative calculations with the principle of minimizing energy dissipation in order to obtain the optimal parameters for de-icing.

[0035] S4 controls the high-pressure nozzle assembly, medium-pressure nozzle assembly, and low-pressure nozzle assembly to rise to a designated position and rotate to a designated angle through the central control system in the intelligent control unit, and starts the de-icing fluid supply and transportation system to carry out spraying operations.

[0036] S5 monitors the physical properties of the de-icing fluid waste liquid and the aircraft icing situation in real time, and feeds the data back to the central control system to obtain the optimal parameter configuration for de-icing;

[0037] S6, after the ice buildup is cleared, the high-pressure nozzle assembly, medium-pressure nozzle assembly, and low-pressure nozzle assembly are lowered and hidden.

[0038] In step S1, the image acquisition device acquires image information on the de-icing pad in real time and detects whether there are aircraft parked on the de-icing pad;

[0039] In step S2, the de-icing detection unit detects the aircraft type and parking position and collects icing data. First, it establishes a linear relationship between the camera and the aircraft based on the camera's internal and external parameters to determine the proportional relationship between the image and the actual object. Then, it performs preprocessing, image segmentation, and edge detection on the acquired image to obtain the boundary features of the ice layer. Finally, it combines the 3D reconstructed aircraft model to obtain the ice and snow coverage area, thickness, and ice and snow coverage type of the aircraft.

[0040] In step S4, the intelligent control unit uses the Runge-Kutta algorithm based on the set of differential equations of motion of the fluid mass micro-element to iteratively solve the spray trajectories of the high-pressure nozzle assembly, medium-pressure nozzle assembly, and low-pressure nozzle assembly at different angles, and compares them to obtain the trajectory with the least kinetic energy loss. It then obtains the starting point coordinates and landing point coordinates of the corresponding high-pressure nozzle assembly, medium-pressure nozzle assembly, and low-pressure nozzle assembly, and controls them to move to the corresponding positions.

[0041] In step S5, a de-icing fluid waste detection unit is installed on the ground at the nose of the aircraft, both sides of the wings, and under the tail of the aircraft to collect the temperature T of the de-icing waste fluid in real time. ac Refractive index W ac Viscosity η acDuring the de-icing process, the collected information on de-icing waste liquid is fed back to the intelligent control unit;

[0042] According to Q in =m L C L (T in -T ac ) Adjust the temperature of the de-icing fluid supply and the amount of de-icing fluid injected in real time, wherein T in m L and C L Q represents the temperature, volume, and specific heat capacity of the input de-icing fluid, respectively. in Energy is input to the system through a function f(W) of refractive index and viscosity. ac ,η ac To determine the loss of de-icing fluid, the concentration of de-icing fluid can be adjusted accordingly.

[0043] Combining all the above technical solutions, the advantages and positive effects of this invention are as follows: This invention, as a concealable surface spraying method, can be applied to intelligent de-icing operations using de-icing fluid on aircraft. De-icing fluid is a mixture of alcohols or olefins and water in a certain proportion. After contact with ice and snow, its physical properties such as temperature, viscosity, and density will change. The system described in this invention is buried underground on the surface of the airport's centralized de-icing pad. It can intelligently sense takeoff and landing starts and stops. After the aircraft is parked without obstruction, the system rises to initiate de-icing operations. After the de-icing operation is completed, the system sinks and hides in the lower ground level. It can intelligently move and assemble the nozzle array, making it suitable for de-icing operations on various aircraft types. It can intelligently adjust the de-icing fluid spray parameters according to the aircraft's de-icing requirements.

[0044] This invention, through the combination of concealable sliding rail-type movable nozzles and concealable fixed dot matrix nozzles, can meet the de-icing needs of different aircraft models. The control system, power unit, and rotating device enable control of nozzle spray angle, flow rate, temperature, pressure, and other parameters, allowing for effective and targeted simultaneous de-icing of key de-icing areas of the aircraft, significantly improving de-icing efficiency and greatly reducing the possibility of secondary icing. The de-icing detection unit and de-icing waste liquid detection unit, through multi-factor detection and feedback of the aircraft surface de-icing process and underground waste liquid, make the control of the de-icing fluid spray system more precise, minimizing ineffective energy loss. The de-icing fluid supply unit, de-icing fluid transportation unit, and de-icing fluid recovery unit form a de-icing fluid recycling loop, realizing the reuse of de-icing fluid.

[0045] The advantages of this invention are also reflected in the following aspects:

[0046] a. Improved safety. The intelligent control system enables rapid and accurate de-icing of the aircraft, enhancing flight safety.

[0047] b. Reduce flight delays. Compared to traditional de-icing operations, this method saves time and manpower, improving flight punctuality.

[0048] c. Reduce costs. Based on real-time monitoring of ice accumulation, the system intelligently adjusts the amount of de-icing fluid used and can recycle excess de-icing fluid from the ground, reducing manpower and material resources and lowering costs.

[0049] e. Automated de-icing: Traditional de-icing systems require manual intervention, while the concealed intelligent aircraft de-icing system can automatically detect the icing condition on the aircraft surface and automatically perform de-icing operations as needed.

[0050] f. Precise control: The concealed intelligent aircraft de-icing system can precisely control the de-icing process, ensuring safe flight operations in icy and snowy weather, while avoiding environmental pollution and resource waste caused by excessive use of de-icing fluid.

[0051] g. Energy saving and environmental protection: An ice-recovery unit has been added, which can collect, purify and reuse the ice-recovery fluid.

[0052] h. The problem of uneven surface area distribution: In traditional fixed nozzle systems, nozzles de-ice the object in the same way regardless of whether the surface is uniform. This may result in some areas not being adequately covered, while other areas may be over-cleaned. Reconfigurable intelligent de-icing nozzle systems use multiple nozzles and sensors to detect the temperature and condition of the object's surface and adjust the operation of each nozzle for more accurate de-icing.

[0053] i. The problem of complex surface structures: Some objects have very complex surface structures, such as airplane wings and helicopter rotor blades. Traditional fixed nozzle systems struggle to cover these areas because their shapes and angles vary greatly. Reconfigurable intelligent de-icing nozzle systems can adaptively adjust the position and orientation of each nozzle based on the surface structure, allowing the nozzles to effectively cover the entire surface.

[0054] k. Traditional de-icing operations, to achieve efficient de-icing, require manual operation using a lifting platform to visually inspect the aircraft's icing condition and control the spraying of de-icing fluid from individual nozzles. However, this does not effectively reduce de-icing fluid waste, and the spray volume, direction, and range all need to be manually adjusted during operation, making it complex and inefficient. Reconfigurable de-icing systems, on the other hand, employ intelligent control technology to achieve precise coordination and automatic adjustment between multiple nozzles. The spray range and volume can be adjusted in real time, improving the efficiency and accuracy of de-icing operations. By arranging and combining multiple nozzles, reconfigurable de-icing systems successfully overcome the technical bias of traditional de-icing operations requiring manual operation, achieving more efficient, accurate, and flexible de-icing operations. Attached Figure Description

[0055] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure;

[0056] Figure 1 This is a schematic diagram of a reconfigurable intelligent aircraft de-icing system provided in an embodiment of the present invention;

[0057] Figure 2 This is a diagram showing the distribution of the five de-icing areas and the distribution of the de-icing waste liquid detection unit provided in this embodiment of the invention.

[0058] Figure 3(a) is a schematic diagram of a concealable sliding rail movable nozzle (high pressure nozzle assembly; or medium pressure nozzle assembly) provided in an embodiment of the present invention;

[0059] Figure 3(b) is a schematic diagram of a retractable fixed nozzle (low-pressure nozzle assembly) provided in an embodiment of the present invention;

[0060] Figure 3(c) is a schematic diagram of the refractive index sensor, temperature sensor, and viscosity sensor in the de-icing waste liquid detection unit provided in the embodiment of the present invention.

[0061] Figure 4 This is a flowchart of the reconfigurable intelligent aircraft de-icing method provided in an embodiment of the present invention;

[0062] Figure 5(a) is a schematic diagram of the jet flow lines of the low-pressure nozzle assembly installed in the III de-icing zone and the high-pressure nozzle assembly installed in the V de-icing zone provided in the embodiment of the present invention.

[0063] Figure 5(b) is a schematic diagram of the jet flow lines of the medium-pressure nozzle assembly installed in the I de-icing area, the high-pressure nozzle assembly installed in the II de-icing area, and the high-pressure nozzle assembly installed in the IV de-icing area provided in the embodiments of the present invention.

[0064] Figure 6 This is an image detection flowchart provided in an embodiment of the present invention;

[0065] Figure 7 This is a flowchart of the control algorithm provided in an embodiment of the present invention;

[0066] In the diagram: 1. De-icing fluid concealed nozzle unit; 2. De-icing detection unit; 3. De-icing waste fluid detection unit; 4. Intelligent control unit; 5. De-icing fluid supply unit; 6. De-icing fluid transport unit; 7. De-icing fluid recovery unit; 8. Water tank; 9. Water flow control valve; 10. Propylene glycol solution tank; 11. Propylene glycol solution flow control valve; 12. De-icing fluid mixing tank; 13. De-icing fluid mixing controller; 14. Concentration detection device; 15. High-pressure water pump; 6. Heater; 17. High-pressure nozzle assembly; 18. Medium-pressure nozzle assembly; 19. Low-pressure nozzle assembly; 20. De-icing fluid recovery ditch; 21. Filter drain; 22. De-icing fluid recovery pipeline; 23. De-icing fluid recovery tank; 24. Filter screen; 25. Filter tank; 26. Water pump; 27. Recovered liquid purification device; 28. Refractive index sensor; 29. ​​Temperature sensor; 30. Viscosity sensor; 31. Position sensor; 32. Image acquisition device. Detailed Implementation

[0067] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of the present invention. However, the present invention can be practiced in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0068] Example 1, such as Figure 1 As shown, the reconfigurable intelligent aircraft de-icing system provided in this embodiment of the invention includes: a de-icing fluid concealed nozzle unit 1, a de-icing detection unit 2, a de-icing waste fluid detection unit 3, an intelligent control unit 4, a de-icing fluid supply unit 5, a de-icing fluid transport unit 6, and a de-icing fluid recovery unit 7.

[0069] The de-icing fluid concealed nozzle unit 1 includes: a high-pressure nozzle assembly 17, a medium-pressure nozzle assembly 18, and a low-pressure nozzle assembly 19.

[0070] like Figure 2 As shown, a de-icing pad is divided into five areas: I. The de-icing area is located at the front end of the de-icing pad and is equipped with medium-pressure nozzle assemblies 18, which are distributed in an arc. A track is laid below the medium-pressure nozzle assemblies 18, which can slide longitudinally along the track to spray de-icing fluid to complete the de-icing operation of the aircraft nose; the track here is arranged longitudinally.

[0071] II. The de-icing area is located in the front middle of the de-icing pad. High-pressure nozzle assembly 17 is installed there. The nozzles of the high-pressure nozzle assembly 17 are arranged in two rows along the horizontal direction, with each row of high-pressure nozzle assembly 17 arranged on the left and right sides (no installation in the middle area). A track is laid under the high-pressure nozzle assembly 17. The high-pressure nozzle assembly 17 can slide longitudinally along the track and spray de-icing fluid to complete the de-icing operation of the aircraft wing. The track here is arranged longitudinally.

[0072] The III de-icing zone is located in the middle of the de-icing pad and is equipped with low-pressure nozzle assembly 19. The III de-icing zone is located between the two rows of high-pressure nozzle assembly 17 in the II de-icing zone. The low-pressure nozzle assembly 19 is arranged in an array within two rectangles on the left and right, and can spray de-icing fluid to complete the aircraft engine de-icing operation.

[0073] IV De-icing area is located behind III De-icing area. High-pressure nozzle assembly 17 is installed. The high-pressure nozzle assembly 17 on the left and right sides is arranged in two columns along the longitudinal direction. A track is laid under the high-pressure nozzle assembly 17. The high-pressure nozzle assembly 17 can slide longitudinally along the track and spray de-icing fluid to complete the aircraft tail de-icing operation. The track is arranged longitudinally here.

[0074] V. The de-icing area is located on the left and right sides of the de-icing pad. High-pressure nozzle assemblies 17 are installed longitudinally, one row on each side. A track is laid below the high-pressure nozzle assembly 17. The high-pressure nozzle assembly 17 can slide laterally along the track to spray de-icing fluid to complete the de-icing operation on the aircraft cabin surface. The track here is arranged laterally.

[0075] For example, as shown in Figure 3(a), the high-pressure nozzle assembly 17 adopts a retractable sliding rail movable nozzle assembly. A linkage cover plate is installed on the ground surface above the high-pressure nozzle assembly 17, and a rail for controlling the sliding of the high-pressure nozzle assembly 17 is connected below the high-pressure nozzle assembly 17. The rail is installed on a base that can control the lifting and lowering.

[0076] The medium-pressure nozzle assembly 18 also adopts a retractable sliding rail movable nozzle assembly. A linkage cover plate is installed on the ground surface above the medium-pressure nozzle assembly 18, and a rail for controlling the sliding of the medium-pressure nozzle assembly 18 is connected below the medium-pressure nozzle assembly 18. The rail is installed on a base that can control the lifting and lowering.

[0077] As shown in Figure 3(b), the low-pressure nozzle assembly 19 is a fixed nozzle assembly. The low-pressure nozzle assembly 19 is fixedly installed on a base that can be raised and lowered, and a linkage cover plate is installed above each low-pressure nozzle assembly 19.

[0078] In embodiments of the present invention, such as Figure 2As shown, the de-icing detection unit 2 includes an image acquisition device 32 installed at the front end of the de-icing pad and a position sensor 31 integrated into the de-icing waste liquid detection unit 3 (as shown in Figure 3(c)). The image acquisition device 32 is used to collect real-time data on the area, thickness, and type of ice and snow coverage on the aircraft fuselage, and works with the position sensor 31 to determine the aircraft type and parking position. The image detection process of the image acquisition device 32 is as follows: Figure 6 As shown;

[0079] The de-icing waste liquid detection unit 3 is arranged on the ground below the nose of the aircraft, the two wings, the fuselage, and the tail of the aircraft, respectively, to detect the physical properties of the de-icing waste liquid during de-icing operations in real time.

[0080] As shown in Figure 3(c), the de-icing waste liquid detection unit 3 integrates a refractive index sensor 28, a temperature sensor 29, and a viscosity sensor 30. Similar to the low-pressure nozzle assembly 19, a linkage cover plate is installed on the ground above the detection unit. The entire detection unit is fixedly installed on a base that can be raised and lowered. When not in operation, it is hidden below the ground. When de-icing is performed, the de-icing waste liquid detection unit 3 rises above the ground.

[0081] The intelligent control unit 4, as the core control unit of the reconfigurable intelligent aircraft de-icing system, will perform de-icing operations in accordance with... Figure 4 The reconfigurable intelligent aircraft de-icing method shown includes the following steps:

[0082] The first step is for the image acquisition device 32 to acquire image information on the de-icing pad in real time and detect whether there are any aircraft parked on the de-icing pad;

[0083] The second step, after confirming the aircraft has stopped, is to activate the de-icing system. De-icing detection unit 2 detects the aircraft type and parking location, and collects icing data; the image detection process is as follows: Figure 6 As shown;

[0084] The third step is for the intelligent control unit 4 to determine the de-icing working area based on the collected images and location information, and to select the de-icing parameters and de-icing nozzle configuration scheme.

[0085] The fourth step involves activating the de-icing fluid supply and transport system. The intelligent control unit 4 transmits control information to the high-pressure nozzle assembly 17, medium-pressure nozzle assembly 18, and low-pressure nozzle assembly 19 via the control bus. This opens the corresponding linkage covers, adjusts the high-pressure nozzle assembly 17, medium-pressure nozzle assembly 18, and low-pressure nozzle assembly 19 to their respective spray positions, and raises the corresponding high-pressure nozzle assembly 17, medium-pressure nozzle assembly 18, and low-pressure nozzle assembly 19 in the de-icing fluid concealed nozzle unit 1 above the ground. The spray angles of the high-pressure nozzle assembly 17, medium-pressure nozzle assembly 18, and low-pressure nozzle assembly 19 are adjusted. De-icing is performed according to the jet streamlines of the low-pressure nozzle assembly 19 installed in de-icing zone III and the high-pressure nozzle assembly 17 installed in de-icing zone V provided in this embodiment of the invention, as shown in Figure 5(a), and the jet streamline trajectories of the medium-pressure nozzle assembly 18 installed in de-icing zone I, the high-pressure nozzle assembly 17 installed in de-icing zone II, and the high-pressure nozzle assembly 17 installed in de-icing zone IV provided in this embodiment of the invention. The de-icing control algorithm of the intelligent control unit 4 is as follows: Figure 7 As shown.

[0086] Fifth, the de-icing waste liquid detection unit 3 extends out of the ground to collect the concentration and temperature information of the de-icing waste liquid in real time during the de-icing process, and feeds it back to the intelligent control unit 4 (controller) to adjust the flow rate of the de-icing liquid during spraying in real time, reduce the waste of de-icing liquid, and adjust the temperature of the heater 16 to ensure that the sprayed de-icing liquid is at a suitable temperature.

[0087] Step 6: After the ice buildup is cleared, the de-icing spray system is turned off and the nozzles are lowered and hidden.

[0088] After completing the corresponding de-icing work, the de-icing fluid recovery unit 7 begins to collect and filter the de-icing waste fluid. Due to the slope design of the de-icing pad, the sprayed de-icing waste fluid automatically flows into the de-icing fluid recovery ditches 20 on both sides. The collected de-icing fluid enters the de-icing fluid recovery pipeline 22 after being filtered once by the filter drain 21. The de-icing waste fluid recovered from each part flows into the de-icing fluid recovery pool 23 through the de-icing fluid recovery pipeline 22. The de-icing waste fluid flowing into the recovery pool is filtered twice by the filter screen 24 and stored in the filter pool 25. The filtered de-icing waste fluid flows into the recovery liquid purification device 27 on the ground for distillation and concentration by the action of the water pump 26. The purified propylene glycol solution is stored in the propylene glycol solution tank 10.

[0089] The de-icing supply unit 5 includes a water tank 8 and a propylene glycol solution tank 10. The outlet of the water tank 8 is connected to a water flow control valve 9, and the outlet of the propylene glycol solution tank 10 is connected to a propylene glycol solution flow control valve 11. The outlets of the two flow control valves are connected to a de-icing fluid mixing tank 12. The de-icing fluid mixing controller 13 controls the two flow control valves. By processing the concentration information of the de-icing fluid mixing tank 12 detected by the concentration detection device 14, the ratio of water to propylene glycol solution is calculated, thereby controlling the flow rates of the two liquids. The outlet of the de-icing fluid mixing tank 12 is connected to a high-pressure water pump 15 on the de-icing fluid transport unit 6. The power provided by the high-pressure water pump 15 is used to transport the de-icing fluid from the de-icing fluid supply unit 5 to the de-icing fluid concealed nozzle units 1 on each de-icing pad.

[0090] Example 2, as another embodiment of the present invention, the reconfigurable intelligent aircraft de-icing system provided in this embodiment includes several de-icing positions, each de-icing position is equipped with a de-icing hidden nozzle unit 1, a de-icing detection unit 2, a de-icing waste liquid detection unit 3, and an intelligent control unit 4; the several de-icing positions share a de-icing fluid supply unit 5, a de-icing fluid transport unit 6, and a de-icing fluid recovery unit 7.

[0091] Each de-icing station consists of five de-icing nozzle areas, including a first medium-pressure retractable sliding movable nozzle area, a second medium-pressure retractable sliding movable nozzle area, a third low-pressure retractable fixed dot matrix nozzle area, a fourth high-pressure retractable sliding movable nozzle area, and a fifth high-pressure retractable sliding movable nozzle area.

[0092] The third low-pressure concealable fixed dot matrix nozzle area includes a linkage cover plate, a low-pressure nozzle assembly 19, and a rise-and-sink base.

[0093] Both the first medium-pressure retractable sliding movable nozzle area and the second medium-pressure retractable sliding movable nozzle area include a linkage cover plate, a medium-pressure nozzle assembly 18, a nozzle sliding control rail, and a rise-and-sink base.

[0094] Both the fourth and fifth high-pressure retractable sliding movable nozzle areas include a linkage cover plate, a high-pressure nozzle assembly 17, a nozzle sliding control rail, and a rise-and-sink base.

[0095] The high-pressure nozzle assembly 17, the medium-pressure nozzle assembly 18, and the low-pressure nozzle assembly 19 all include a rotation control device to control the rotation angle of the nozzle.

[0096] The adjustable base includes a de-icing fluid buffer, a power unit, and a lifting mechanism to control the de-icing fluid flow rate, pressure, and nozzle height.

[0097] The de-icing detection unit 2 uses an image recognition device located around the apron. Its lifting structure allows it to be hidden underground when not in operation. It can perform real-time position detection of the aircraft to be de-iced, ensuring that the aircraft enters the appropriate de-icing operation position, thereby coordinating the positions of the high-pressure nozzle assembly 17, medium-pressure nozzle assembly 18, and low-pressure nozzle assembly 19 as well as the number of operations of the high-pressure nozzle assembly 17, medium-pressure nozzle assembly 18, and low-pressure nozzle assembly 19.

[0098] The de-icing waste liquid detection unit 3 includes a refractive index sensor 28, a temperature sensor 29, and a viscosity sensor 30, all of which are located in a concealable underground integrated detection device. It can detect the temperature and concentration of the waste liquid in real time and feed the data back to the intelligent control unit 4 to regulate the operation of the nozzles.

[0099] The intelligent control unit 4 can control the flow rate, temperature, pressure, and angle of the high-pressure nozzle assembly 17, medium-pressure nozzle assembly 18, and low-pressure nozzle assembly 19 in real time based on the detection data, thereby optimizing the de-icing efficiency. The control algorithm flow is as follows: Figure 7 As shown.

[0100] The de-icing fluid supply unit 5 includes an alcohol supply device, a water supply device, a mixing tank, and a concentration detection device 14. Preferably, it consists of a propylene glycol solution tank 10, a water tank 8, and a de-icing fluid mixing tank 12, which can realize the preparation and mixing of de-icing fluids of different concentrations.

[0101] The de-icing fluid delivery unit 6 includes a de-icing fluid delivery power unit and a de-icing fluid heating unit, preferably a high-pressure water pump 15 and a heater 16, respectively; providing heated de-icing fluid for different de-icing positions.

[0102] The de-icing fluid recovery unit 7 includes an underground drainage trough, a floor drain, a filter tank 25, and a waste liquid distillation device. The underground drainage trough may include a de-icing fluid recovery ditch 20 and a de-icing fluid recovery pipeline 22. The floor drain may be a filtered floor drain 21. The waste liquid distillation device may be a combination of a water pump 26 and a recovered liquid purification device 27; used to achieve the filtration and repurification of waste liquid residue. The de-icing fluid supply unit 5, the de-icing fluid transportation unit 6, and the de-icing fluid recovery unit 7 together achieve uninterrupted supply and recycling of de-icing fluid, reducing waste.

[0103] Example 3, as another embodiment of the present invention, provides a reconfigurable intelligent aircraft de-icing system that can be used for intelligent spraying of de-icing fluid in centralized de-icing operations at airports. De-icing fluid is a mixture of alcohols or olefins and water in a certain proportion. Upon contact with ice and snow, its physical properties, such as temperature, viscosity, and density, will change. The reconfigurable intelligent aircraft de-icing system of the present invention is buried underground on the surface of the airport's centralized de-icing pad. It can intelligently sense takeoff and landing starts and stops. After the aircraft is parked without obstruction, the reconfigurable intelligent aircraft de-icing system rises to initiate de-icing operations. After the de-icing operation is completed, the reconfigurable intelligent aircraft de-icing system sinks and hides below ground level. It can intelligently move and assemble the nozzle array, making it suitable for de-icing operations on various aircraft types. It can use a particle swarm optimization algorithm to iteratively calculate and configure optimal de-icing parameters (nozzle number and position, spray pressure and angle, de-icing fluid concentration, flow rate, and temperature) in real time according to the aircraft's de-icing requirements, based on the principle of minimizing energy dissipation. Figure 7 As shown, the de-icing information (waste liquid temperature and concentration) can be fed back based on the physical properties of the de-icing fluid waste liquid, and the de-icing fluid supply parameters (temperature, concentration, flow rate) can be adjusted in real time.

[0104] The reconfigurable intelligent aircraft de-icing system includes a de-icing fluid concealed nozzle unit 1, a de-icing detection unit 2, a de-icing waste fluid detection unit 3, an intelligent control unit 4, a de-icing fluid supply unit 5, a de-icing fluid transport unit 6, and a de-icing fluid recovery unit 7.

[0105] The de-icing fluid concealed nozzle unit 1 is an embedded nozzle assembly installed under the de-icing floor. It can be raised and lowered, can move along a track, and the nozzle head can rotate 360°.

[0106] The nozzle assembly includes a high-pressure nozzle assembly 17, a medium-pressure nozzle assembly 18, and a low-pressure nozzle assembly 19. The high-pressure nozzle assembly 17 and the medium-pressure nozzle assembly 18 are movable nozzle assemblies, and their movement coordinates are calculated based on the structural parameters of the aircraft to be de-iced and the spray trajectory of the nozzles.

[0107] The de-icing detection unit 2 determines the aircraft type and parking position. The intelligent control unit 4 uses the Runge-Kutta algorithm based on the motion differential equations of fluid mass micro-elements to iteratively solve the spray trajectories of the high-pressure nozzle assembly 17 and the medium-pressure nozzle assembly 18 at different angles, and compares them to obtain the trajectory with the least kinetic energy loss. This allows the corresponding starting point coordinates and landing point coordinates of the high-pressure nozzle assembly 17, the medium-pressure nozzle assembly 18, and the low-pressure nozzle assembly 19 to be obtained. Finally, the components move to the corresponding positions with the help of the slide rail.

[0108] A low-pressure nozzle array, consisting of multiple low-pressure nozzle assemblies 19, is embedded and installed in the subsurface layer. Based on the three-dimensional coordinates of the icing on the aircraft engine and the effective working distance of the nozzles, the corresponding low-pressure nozzle assembly 19 is numbered, and the corresponding low-pressure nozzle assembly 19 is activated to perform de-icing operations on the aircraft engine area under the wing. The spray angle of the low-pressure nozzle assembly 19 can be adjusted in real time by a swing motor. The intelligent control unit 4, based on the fluid motion trajectory equation and the three-dimensional aircraft information obtained by the de-icing detection unit 2, adjusts the angle to ensure that the de-icing fluid can be sprayed to the centerline of the de-icing area. Then, the swing motor gradually increases the spray angle of the low-pressure nozzle assembly 19, causing the spray point of the low-pressure nozzle assemblies 19 on both sides to move outwards from the centerline of the de-icing area. The spray point of the medium-pressure nozzle assembly 18, used for de-icing operations on the aircraft nose, moves downwards from the top of the aircraft.

[0109] The de-icing detection unit 2 includes an image acquisition device 32 for the aircraft model and aircraft ice accumulation. The image acquisition device 32 is installed around the de-icing pad, collecting image information of the aircraft to be de-iced from multiple angles. First, a linear relationship between the camera and the aircraft is established based on the camera's intrinsic and extrinsic parameters to determine the proportional relationship between the image and the actual object. Then, the acquired images undergo preprocessing, image segmentation, and edge detection to obtain the boundary features of the ice layer. Finally, combined with the 3D reconstructed aircraft model, the area, thickness, and type of ice and snow coverage on the fuselage are obtained, such as... Figure 6 As shown.

[0110] The de-icing fluid waste detection unit 3 is an integrated sensing system installed on the ground below the aircraft nose, both sides of the wings, and the tail, to collect the temperature T of the de-icing fluid in real time. ac Refractive index W ac Viscosity η ac During the de-icing process, the collected de-icing waste liquid information is fed back to the intelligent control unit 4, based on Q. in =m L C L (T in -T ac Adjust the temperature T of the de-icing fluid supply in real time. in The amount of de-icing fluid used during spraying (m) L Q in and C L The input energy to the system and the specific heat capacity of the de-icing fluid are respectively expressed as a function of refractive index and viscosity, f(W). ac ,η ac To determine the loss of de-icing fluid, the concentration of de-icing fluid can be adjusted accordingly.

[0111] The intelligent control unit 4 operates according to the following steps to carry out aircraft de-icing operations:

[0112] 1) Check if there are any aircraft parked on the de-icing pad;

[0113] 2) Activate the de-icing system to detect aircraft type, parking location, and collect icing data;

[0114] 3) Based on the collected data, the particle swarm optimization algorithm is used to perform iterative calculations with the principle of minimizing energy dissipation in order to obtain the optimal parameters for de-icing;

[0115] 4) The high-pressure nozzle assembly 17, medium-pressure nozzle assembly 18, and low-pressure nozzle assembly 19 are controlled by the central control system in the intelligent control unit 4 to rise to the designated position and rotate to the designated angle, and the de-icing fluid supply and transportation system is turned on to carry out the spraying operation.

[0116] 5) Monitor the physical properties of the de-icing fluid waste liquid and the aircraft icing situation in real time, and feed the data back to the central control system to obtain the optimal parameter configuration for de-icing;

[0117] 6) After the ice buildup is cleared, the de-icing spray system is turned off and the nozzle is lowered and hidden.

[0118] The de-icing fluid supply unit 5 is equipped with a de-icing fluid mixing tank 12 whose concentration can be adjusted by the de-icing fluid mixing controller 13. The inlet of the de-icing fluid mixing tank 12 is connected to the water tank 8 and the propylene glycol solution tank 10 through the water flow control valve 9 and the propylene glycol solution flow control valve 11, respectively. The outlet of the de-icing fluid mixing tank 12 is connected to the main supply pipeline of the de-icing fluid transport unit 6. The main supply pipeline is equipped with a high-pressure water pump 15 and a heater 16 with adjustable pressure and temperature.

[0119] The de-icing fluid recovery unit 7 includes de-icing fluid recovery ditches 20 set on both sides of the de-icing pad. Each de-icing fluid recovery ditch 20 is connected to the de-icing fluid recovery pipeline 22 through a filter drain 21. The de-icing waste fluid after the de-icing operation eventually flows into the de-icing fluid recovery pool 23, is filtered by the filter screen 24 and enters the filter pool 25, and then enters the recovery liquid purification device 27 through the water pump 26, and is finally stored in the propylene glycol solution tank 10 connected to the recovery liquid purification device 27.

[0120] In the above embodiments, the descriptions of each embodiment have different focuses. For parts that are not described in detail or recorded in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0121] The information interaction and execution process between the above-mentioned devices / units are based on the same concept as the method embodiments of the present invention. For details on their specific functions and technical effects, please refer to the method embodiments section, and they will not be repeated here.

[0122] Those skilled in the art will understand that, for the sake of convenience and brevity, the above-described division of functional units and modules is merely an example. In practical applications, the functions described above can be assigned to different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiments can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit. Furthermore, the specific names of the functional units and modules are only for easy differentiation and are not intended to limit the scope of protection of this invention. The specific working process of the units and modules in the above system can be referred to the corresponding process in the foregoing method embodiments.

[0123] Based on the technical solutions described in the above embodiments of the present invention, the following application examples can be further proposed.

[0124] According to embodiments of this application, the present invention also provides a computer device comprising: at least one processor, a memory, and a computer program stored in the memory and executable on the at least one processor, wherein the processor executes the computer program to implement the steps in any of the above-described method embodiments.

[0125] This invention also provides a computer-readable storage medium storing a computer program that, when executed by a processor, can implement the steps described in the various method embodiments above.

[0126] This invention also provides an information data processing terminal, which, when executed on an electronic device, provides a user input interface to implement the steps described in the above method embodiments. The information data processing terminal is not limited to mobile phones, computers, or switches.

[0127] This invention also provides a server that, when executed on an electronic device, provides a user input interface to implement the steps described in the above method embodiments.

[0128] This invention also provides a computer program product that, when run on an electronic device, enables the electronic device to implement the steps described in the various method embodiments above.

[0129] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, all or part of the processes in the methods of the above embodiments of this application can be implemented by a computer program instructing related hardware. The computer program can be stored in a computer-readable storage medium, and when executed by a processor, it can implement the steps of the various method embodiments described above. The computer program includes computer program code, which can be in the form of source code, object code, executable files, or certain intermediate forms. The computer-readable medium can include at least: any entity or device capable of carrying the computer program code to a photographing device / terminal device, a recording medium, a computer memory, a read-only memory (ROM), a random access memory (RAM), an electrical carrier signal, a telecommunication signal, and a software distribution medium. Examples include USB flash drives, portable hard drives, magnetic disks, or optical disks.

[0130] In the above embodiments, the descriptions of each embodiment have different focuses. For parts that are not described in detail or recorded in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0131] To further demonstrate the positive effects of the above embodiments, the present invention conducts the following experiments based on the following technical solutions.

[0132] Experimental objective: To verify that the nozzles of the reconfigurable concealed nozzle de-icing system can precisely control the contact time between ice and snow and the aircraft surface in different environments, thereby achieving efficient, automated, and reliable de-icing services.

[0133] Experimental procedure:

[0134] Experimental equipment: This invention selected a commonly used reconfigurable concealed nozzle de-icing system and installed it on a simulated aircraft model. The outer shell of the simulated aircraft model was covered with a layer of simulated ice.

[0135] Environmental simulation: This invention uses laboratory air conditioners, humidifiers and other equipment to simulate different environments, such as low temperature and high humidity environments, low temperature and low humidity environments, etc., and records the specific environmental parameters of the simulator.

[0136] System testing: This invention sets the nozzle parameters to automatic control mode and conducts system tests in various environments, recording parameters such as the concentration, flow rate, and pressure of the de-icing fluid sprayed from the nozzle to ensure optimal de-icing effect.

[0137] Results Analysis: Real-time data recording and results analysis were performed for different test environments and nozzle parameter settings to verify the effectiveness and reliability of the system.

[0138] The experimental results led to the following conclusions:

[0139] The reconfigurable concealed nozzle de-icing system can achieve de-icing goals in different environments.

[0140] Under different environments, the system can automatically adjust parameters such as the concentration, flow rate, and pressure of the de-icing fluid sprayed from the nozzle to ensure the best de-icing effect.

[0141] The system can automatically detect and ensure the safety and normal operation of the flight de-icing process.

[0142] The system is easy to operate, safe and reliable, and can be widely used in various types of aircraft.

[0143] Furthermore, this invention utilizes mathematical formulas to perform a more precise analysis of the system, demonstrating its advantages:

[0144] (1) Control parameter detection and optimization:

[0145] Assuming the environmental parameter is Θ, the reliability is R, the control algorithm used is A, and the real-time detected nozzle flow rate and pressure are F and P respectively, the optimal values ​​of the nozzle parameters need to be determined. The following optimization model can be calculated using mathematical formulas such as the maximum entropy principle and the least squares method:

[0146]

[0147] The first term is the entropy calculation, the second is the rate of change of flow rate, and the third is the sum of squares of pressure. H represents the model's entropy or cross-entropy, used to measure the difference between the model's predictions and actual results; a smaller value indicates a better model fit. β represents the model's weight parameters, used to balance the model's fitting ability and generalization ability. γ represents the regularization coefficient, used to control the model's complexity and avoid overfitting.

[0148] (2) Analysis of the de-icing process of the de-icing fluid:

[0149] Assume the ice layer thickness is L, the temperature is T, and the ambient temperature is T. env The density of ice and snow is ρ, and its specific heat capacity is C. p If the thermal conductivity is λ, then the temperature change ΔT on the surface of the ice layer can be described by the following heat conduction equation:

[0150]

[0151] T(0,t)=T env

[0152] T(L,t)=T

[0153] Where x represents the distance from the top of the ice layer, and t represents the time during the melting process of the ice and snow. It represents the rate of change of temperature over time, that is, the speed at which temperature changes. This represents the second derivative of temperature with respect to the vertical position x in space, which is the rate of change of temperature in space. It represents the process of heat transfer from a high-temperature region to a low-temperature region. T(0,t) represents the temperature at the top of the ice layer at time t, and its value is equal to the ambient temperature T. env T(L,t) represents the temperature at the bottom of the ice layer at time t, and its value is equal to T.

[0154] (3) Analysis of system reconfigurability:

[0155] Assuming the system's scalability is E, usability is U, hardware reconfigurability is H, and software reconfigurability is S, meaning the existing system can be quickly combined, coordinated, operated, and controlled under various strains, and possesses usability, scalability, repairability, and customizability, then the system's reconfigurability can be calculated using the following formula:

[0156] R = E·U·H·S

[0157] Here, R represents the system's reconfigurability.

[0158] In summary, the experiment verified the effectiveness and reliability of the reconfigurable concealed nozzle de-icing system. By applying mathematical formulas, the advantages of the reconfigurable concealed nozzle de-icing system can be analyzed more comprehensively and accurately, thereby further strengthening the performance analysis and optimization of the system. It can meet the requirements of high efficiency, automation and reliability in the flight de-icing process, has a wide range of applications, and safeguards flight safety.

[0159] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any modifications, equivalent substitutions and improvements made by those skilled in the art within the scope of the technology disclosed in the present invention and within the spirit and principles of the present invention should be covered within the scope of protection of the present invention.

Claims

1. A reconfigurable intelligent aircraft de-icing system, characterized in that, The system includes: The de-icing fluid concealed nozzle unit (1) is used to achieve spray de-icing under different pressures in different de-icing areas, and automatically sinks and hides after de-icing is completed; The de-icing detection unit (2) is used to collect the area, thickness and type of ice and snow coverage on the fuselage in real time, and to determine the aircraft type and parking position. The de-icing waste liquid detection unit (3) is located on the ground below the nose of the aircraft, the wings on both sides of the aircraft, the fuselage of the aircraft, and the tail of the aircraft. It is used to detect the physical properties of the de-icing waste liquid during de-icing operations in real time. The intelligent control unit (4) is used to control the flow rate, temperature, pressure and angle of the nozzle assembly under different pressures in real time to optimize the de-icing efficiency. The de-icing fluid supply unit (5) is used for the preparation and mixing of de-icing fluids of different concentrations; De-icing fluid transport unit (6) is used to heat the de-icing fluid and transport it to different de-icing areas; The de-icing fluid recovery unit (7) is used for the filtration and repurification of waste liquid residues; Among them, the de-icing fluid supply unit (5), the de-icing fluid transportation unit (6) and the de-icing fluid recovery unit (7) work together to provide uninterrupted supply and recycling of de-icing fluid; The de-icing fluid concealed nozzle unit (1) includes: a high-pressure nozzle assembly (17), a medium-pressure nozzle assembly (18), and a low-pressure nozzle assembly (19); The different de-icing areas include: Ⅰ De-icing area, located at the front end of the de-icing pad, is equipped with medium-pressure nozzle assemblies (18) and is distributed in an arc; II. De-icing area, located in the middle of the front of the de-icing pad, is equipped with a high-pressure nozzle assembly (17). The nozzles of the high-pressure nozzle assembly (17) are arranged in two rows along the horizontal direction, and each row of high-pressure nozzle assemblies (17) is arranged on the left and right sides. The III de-icing zone is located in the middle of the de-icing pad and is equipped with a low-pressure nozzle assembly (19). The III de-icing zone is located between the two rows of high-pressure nozzle assemblies (17) in the II de-icing zone. The IV de-icing area is located behind the III de-icing area and is equipped with a high-pressure nozzle assembly (17). The high-pressure nozzle assemblies (17) on the left and right sides are arranged in two columns along the longitudinal direction. V. The de-icing area is located on the left and right sides of the de-icing pad, and high-pressure nozzle assemblies (17) are installed, arranged longitudinally, with one row on each side.

2. The reconfigurable intelligent aircraft de-icing system according to claim 1, characterized in that, The medium-pressure nozzle assembly (18) is laid on a track and slides longitudinally along the track to spray de-icing fluid to complete the de-icing operation of the aircraft nose.

3. The reconfigurable intelligent aircraft de-icing system according to claim 1, characterized in that, The high-pressure nozzle assembly (17) installed in the II de-icing area is laid on a track and slides longitudinally along the track to spray de-icing fluid to complete the de-icing operation of the aircraft wing.

4. The reconfigurable intelligent aircraft de-icing system according to claim 1, characterized in that, The low-pressure nozzle assembly (19) is arranged in an array within two rectangles on the left and right sides to spray de-icing fluid to complete the de-icing operation of the aircraft engine; The high-pressure nozzle assembly (17) installed in the IV de-icing zone slides longitudinally along the track to spray de-icing fluid to complete the aircraft tail de-icing operation; The high-pressure nozzle assembly (17) installed in the V de-icing area slides laterally along the track to spray de-icing fluid to complete the de-icing operation on the aircraft cabin surface; The high-pressure nozzle assembly (17) and the medium-pressure nozzle assembly (18) both adopt concealable sliding rail type and movable nozzle assembly, with a linkage cover plate installed on the ground surface above and a track for controlling the sliding connected below. The track is installed on the lifting base. The low-pressure nozzle assembly (19) is a fixed nozzle assembly, which is fixedly installed on the lifting base and has a linkage cover plate installed on top.

5. The reconfigurable intelligent aircraft de-icing system according to claim 1, characterized in that, The de-icing detection unit (2) includes an image acquisition device (32) installed at the front end of the de-icing pad and a position sensor (31) integrated in the de-icing waste liquid detection unit (3). The image acquisition device (32) is used to collect the area, thickness and type of ice and snow covering the fuselage in real time, and to cooperate with the position sensor (31) to determine the aircraft type and parking position. The de-icing waste liquid detection unit (3) integrates a refractive index sensor (28), a temperature sensor (29), and a viscosity sensor (30). A linkage cover plate is installed on the ground above the de-icing waste liquid detection unit (3) and is fixedly installed on the base that controls the lifting. The de-icing fluid supply unit (5) includes: a water tank (8) and a propylene glycol solution tank (10). The outlet of the water tank (8) is connected to a water flow control valve (9), and the outlet of the propylene glycol solution tank (10) is connected to a propylene glycol solution flow control valve (11). The outlets of the two flow control valves are connected to a de-icing fluid mixing tank (12). The de-icing fluid mixing controller (13) controls the two flow control valves. By processing the concentration information of the de-icing fluid mixing tank (12) detected by the concentration detection device (14), the ratio of water and propylene glycol solution is calculated, and the flow rates of the two liquids are controlled. The outlet of the de-icing fluid mixing tank (12) is connected to a high-pressure water pump (15) on the de-icing fluid transport unit (6). The power provided by the high-pressure water pump (15) is used to transport the de-icing fluid from the de-icing fluid supply unit (5) to the de-icing fluid concealed nozzle unit (1) on each de-icing pad.

6. A reconfigurable intelligent aircraft de-icing method, characterized in that, The method of using the reconfigurable intelligent aircraft de-icing system according to any one of claims 1 to 5 includes the following steps: S1, check if there are any aircraft parked on the de-icing pad; S2, activate the de-icing system to detect aircraft type and parking location and collect icing data; S3. Based on the collected data, the particle swarm optimization algorithm is used to perform iterative calculations with the principle of minimizing energy dissipation in order to obtain the optimal parameters for de-icing. S4, through the central control system in the intelligent control unit (4), the high pressure nozzle assembly (17), medium pressure nozzle assembly (18) and low pressure nozzle assembly (19) are controlled to rise and move to the designated position and rotate to the designated angle, and the de-icing fluid supply and transportation system is turned on to carry out spraying operation; S5 monitors the physical properties of the de-icing fluid waste liquid and the aircraft icing situation in real time, and feeds the data back to the central control system to obtain the optimal parameter configuration for de-icing; S6. After the ice buildup is cleared, the high-pressure nozzle assembly (17), medium-pressure nozzle assembly (18), and low-pressure nozzle assembly (19) are lowered and hidden.

7. The reconfigurable intelligent aircraft de-icing method according to claim 6, characterized in that, In step S1, the image acquisition device (32) acquires image information on the de-icing pad in real time and detects whether there is an aircraft parked on the de-icing pad; In step S2, the de-icing detection unit (2) detects the aircraft type and parking position and collects ice accumulation data. First, it establishes a linear relationship between the camera and the aircraft based on the camera's internal and external parameters to determine the proportional relationship between the image and the actual object. Then, it performs preprocessing, image segmentation, and edge detection on the acquired image to obtain the boundary features of the ice layer. Finally, by combining the 3D reconstructed aircraft model, the area, thickness, and type of ice and snow coverage on the fuselage are obtained.

8. The reconfigurable intelligent aircraft de-icing method according to claim 6, characterized in that, In step S4, the intelligent control unit (4) uses the Runge-Kutta algorithm to iteratively solve the jet trajectories of the high-pressure nozzle assembly (17), medium-pressure nozzle assembly (18), and low-pressure nozzle assembly (19) at different angles based on the set of differential equations of motion of fluid mass micro-elements, and compares them to obtain the trajectory with the least kinetic energy loss. It then obtains the starting point coordinates and landing point coordinates of the corresponding high-pressure nozzle assembly (17), medium-pressure nozzle assembly (18), and low-pressure nozzle assembly (19), and controls them to move to the corresponding positions.

9. The reconfigurable intelligent aircraft de-icing method according to claim 6, characterized in that, In step S5, the temperature T of the de-icing waste liquid is collected in real time by installing the de-icing waste liquid detection unit (3) on the ground at the nose, both sides of the wings, and under the tail of the aircraft. ac Refractive index W ac Viscosity η ac During the de-icing process, the collected de-icing waste liquid information is fed back to the intelligent control unit (4); According to Q in =m L C L (T in -T ac ) Adjust the temperature of the de-icing fluid supply and the amount of de-icing fluid injected in real time, wherein T in m L and C L Q represents the temperature, volume, and specific heat capacity of the input de-icing fluid, respectively. in Energy is input to the system through a function f(W) of refractive index and viscosity. ac ,η ac To determine the loss of de-icing fluid, the concentration of de-icing fluid can be adjusted accordingly.

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