Anti-icing system of aircraft windshield

Abstract

The utility model provides an anti-icing system of an aircraft windshield, relates to the technical field of aircraft electric environment control, and is used for improving the anti-icing efficiency of the aircraft windshield. The system comprises a one-way valve, an airflow rectifier and an air film slit, an air inlet of the air film slit is located in a cockpit, and an air outlet of the air film slit is located at the bottom of an aircraft windshield. The airflow rectifier and the one-way valve are located in a cockpit, one end of the airflow rectifier is connected with an air inlet of the air film slit, and the other end of the airflow rectifier is connected with the one-way valve; the airflow rectifier is used for reducing the turbulence degree of airflow flowing in through the one-way valve.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft electric environmental control technology, and in particular to an anti-icing system of an aircraft windshield. BACKGROUND

[0002] Ice formation on an aircraft during flight can threaten flight safety, increase the weight of the aircraft, damage the aerodynamic shape of the aircraft, and affect the normal operation of aircraft components. The parts of the aircraft prone to icing include the windshield, the wings, and the lip of the engine nacelle, etc. The existing anti-icing methods can be divided into the following five types: liquid anti-icing technology, mechanical anti-icing technology, super-hydrophobic material anti-icing technology, electric heating anti-icing technology, and gas heating anti-icing technology.

[0003] At present, the electric heating anti-icing technology can be applied to the deicing of the aircraft windshield. The electric heating anti-icing technology is to heat the surface of the icing area by power heating, and then heat the surface of the ice layer through heat conduction. However, this technology has problems such as high power consumption and low anti-icing efficiency. CONTENT OF THE INVENTION

[0004] The embodiment of the present application provides an anti-icing system of an aircraft windshield, which is used for improving the anti-icing efficiency of the aircraft windshield.

[0005] The embodiment of the present application provides an anti-icing system of an aircraft windshield, which comprises a one-way valve, an airflow rectifier, and an air film slit.

[0006] The air inlet of the air film slit is located inside the cockpit, and the air outlet of the air film slit is located at the bottom of the aircraft windshield.

[0007] The airflow rectifier and the one-way valve are located inside the cockpit. One end of the airflow rectifier is connected to the air inlet of the air film slit, and the other end of the airflow rectifier is connected to the one-way valve. The airflow rectifier is used to reduce the turbulence of the airflow flowing through the one-way valve.

[0008] In an optional embodiment, the system further comprises an anti-icing controller.

[0009] The anti-icing controller is used to control the opening and closing of the one-way valve.

[0010] When the anti-icing controller controls the opening of the one-way valve, the pressurized air in the cockpit flows through the one-way valve, the airflow rectifier, and the air film slit to the outside of the aircraft in sequence.

[0011] In an optional embodiment, the system further comprises a temperature sensor, a humidity sensor, and an icing sensor.

[0012] The anti-icing controller is further configured to acquire sensor data corresponding to the temperature sensor, the humidity sensor and the icing sensor respectively, and determine opening or closing of the one-way valve according to the sensor data.

[0013] In an optional embodiment, the system further comprises: an airflow duct.

[0014] The airflow duct is arranged at the bottom of the airflow baffle, and the airflow duct is connected to the air outlet of the air film slit. An air outlet device is arranged on the airflow duct, so that the airflow flowing into the airflow duct through the air outlet flows out through the air outlet device to generate an air film.

[0015] In an optional embodiment, each airflow duct corresponds to an aircraft windshield, and the length and structure of each airflow duct are matched with the length and structure of the corresponding aircraft windshield.

[0016] In an optional embodiment, each airflow duct corresponds to an air film slit, and the two ends of the airflow duct are respectively connected to the air outlets of the corresponding air film slit.

[0017] In an optional embodiment, the air outlet device on the airflow duct is an air outlet slit with a width less than a preset value, or the air outlet device on the airflow duct is a flow regulation net. The air outlet slit and the flow regulation net are arranged in a direction facing the aircraft windshield, so that the airflow flowing out of the air outlet slit or the flow regulation net uniformly generates an air film on the surface of the aircraft windshield.

[0018] In an optional embodiment, the system further comprises: a simulation model.

[0019] The simulation model is configured to acquire a simulation result of icing, and determine the structural parameters of the airflow regulator and the air film slit according to the simulation result of icing.

[0020] In an optional embodiment, the structural parameters of the air film slit include: a slit size, a slit outlet position and an included angle between a slit outlet section and the windshield. The structural parameters of the airflow regulator include: a cross-sectional shape of the flow regulation grid and a length-diameter ratio of the flow regulation grid.

[0021] The utility model provides a kind of aircraft windshield's anti-icing system, and the system includes: one-way valve, airflow rectifier and air film slit. Among them, the air inlet of the air film slit is located inside the cockpit, and the air outlet of the air film slit is located at the bottom of the aircraft windshield;The airflow rectifier and the one-way valve are located inside the cockpit, one end of the airflow rectifier is connected with the air inlet of the air film slit, and the other end of the airflow rectifier is connected with the one-way valve;The airflow rectifier is used to reduce the turbulence of the airflow flowing through the one-way valve.This one-way valve in the application is opened, and the pressurized air in the cockpit flows through the one-way valve, airflow rectifier and air film slit to the outside of the aircraft in sequence, thereby forming an air film on the surface of the aircraft windshield, isolating the windshield from the external cold air, so as to realize the anti-icing effect of the aircraft windshield. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 A structural diagram of an anti-icing system for an aircraft windshield is provided in the present application.

[0023] Figure 2 A schematic diagram of an anti-icing system for an aircraft windshield is provided in the present application.

[0024] Figure 3 An example diagram of the location of an air film slit is provided in the present application.

[0025] Figure 4 An application architecture diagram of an anti-icing system for an aircraft windshield is provided in the present application.

[0026] Figure 5 A simulation flowchart of an anti-icing system for an aircraft windshield is provided in the present application.

[0027] Figure 6 An anti-icing effect diagram is provided in the present application. DETAILED DESCRIPTION

[0028] In order to better understand the above technical solutions, the technical solutions of the embodiments of the present application will be described in detail below with the help of the drawings and specific embodiments. It should be understood that the specific features in the embodiments of the present application and the embodiments are detailed descriptions of the technical solutions of the embodiments of the present application, and not limitations of the technical solutions of the present application. In the case of no conflict, the technical features in the embodiments of the present application and the embodiments can be combined with each other.

[0029] Please refer to Figure 1 An anti-icing system for an aircraft windshield is provided in the present application, and the system includes: one-way valve, airflow rectifier and air film slit.

[0030] Specifically, the air inlet of the air film slot is located inside the cockpit, and the air outlet of the air film slot is located at the bottom of the aircraft windshield; the airflow regulator and the one-way valve are located inside the cockpit, one end of the airflow regulator is connected to the air inlet of the air film slot, and the other end of the airflow regulator is connected to the one-way valve; the airflow regulator is used to reduce the turbulence of the airflow flowing through the one-way valve.

[0031] In this embodiment, the air film slot directly penetrates the aircraft skin, and the specific structure is as shown in Figures 1 to 3 The air film slot directly opens on the surface of the cockpit skin, the air inlet of the air film slot is located inside the cockpit, and the air outlet of the air film slot is located outside the aircraft. The hot air is the cabin pressurization air, the airflow regulator is located inside the cockpit, and the two ends are connected to the air inlet of the air film slot and the one-way valve respectively, and the one-way valve is located inside the cockpit and exposed to the cabin pressurization air environment. When the one-way valve is opened, the cabin pressurization air flows through the one-way valve, the airflow regulator and the air film slot in sequence to the outside of the aircraft, thereby forming an air film on the surface of the aircraft windshield, thereby achieving the anti-icing effect of the aircraft windshield.

[0032] As shown in Figure 4 In an optional embodiment, the system provided by the present embodiment further comprises an anti-icing controller. The anti-icing controller is used to control the opening and closing of the one-way valve; when the anti-icing controller controls the opening of the one-way valve, the cabin pressurization air flows through the one-way valve, the airflow regulator and the air film slot in sequence to the outside of the aircraft. It should be noted that in this embodiment, the one-way valve can be manually controlled by the pilot according to the actual situation in addition to being automatically controlled by the anti-icing controller.

[0033] Further, in order to automatically control the opening or closing of the one-way valve by the anti-icing controller, the system provided by the present embodiment further comprises a temperature sensor, a humidity sensor and an icing sensor. The anti-icing controller is used to obtain sensor data corresponding to the temperature sensor, the humidity sensor and the icing sensor respectively, and to determine the opening or closing of the one-way valve according to the sensor data.

[0034] As shown in Figure 4As shown, the anti-icing system of the aircraft windshield provided by the embodiment of the application mainly comprises an anti-icing controller, a nose sensor, a front windshield actuator, an air conditioning system, an airflow rectifier and an air film slit. The anti-icing controller, the nose sensor, the front windshield actuator and the air conditioning system are all original equipment of the aircraft. The anti-icing controller is generally located inside the aircraft and is installed on the front equipment rack of the aircraft. The nose sensor refers to a pressure sensor, a temperature sensor, a speed sensor and an icing detection sensor, which is generally installed outside the nose of the aircraft and is generally a probe type sensor extending out of the aircraft. The front windshield actuator refers to a windshield wiper and a windshield cleaning device, which is generally located in front of the windshield of the aircraft. The air conditioning system is generally installed in each pressurized area inside the cabin of the aircraft.

[0035] In actual use, the front windshield sensor collects temperature data, humidity data and icing condition data. When the temperature sensor, humidity sensor and icing sensor installed on the front windshield detect that the icing weather conditions are met or icing has occurred, a signal is input to the anti-icing controller. The anti-icing controller controls the opening of the one-way valve, so that hot air flows through the one-way valve, the airflow rectifier and the air film slit in turn to generate an air film. The function of the airflow rectifier is to reduce the turbulence of the airflow, so that the air film outflow is more uniform and stays farther away from the surface of the aircraft windshield.

[0036] Specifically, during the flight of the aircraft, the icing detector will continuously read the data of the temperature sensor, pressure sensor, speed sensor and icing sensor of the aircraft. When a specific combination of temperature, pressure, speed and icing detection signals is met, the icing detector will determine that the aircraft is currently in an icing state and the anti-icing system should be turned on, that is, the anti-icing controller controls the opening of the one-way valve. The one-way valve is located inside the cockpit and directly connects the airflow rectifier and the pressurized air in the pressurized area inside the aircraft. The opening and closing of the air film slit is controlled by the one-way valve. When the air film slit is opened, the pressurized air in the cockpit flows through the one-way valve, the airflow rectifier and the air film slit in turn to the outside of the aircraft. The airflow rectifier is a honeycomb rectifier, which is a flow rectifying device that can divide large-scale vortexes into small-scale vortexes. The embodiment can change the length-diameter ratio of the honeycomb unit to change the inertial force and viscous dissipation to reduce the size and energy of the vortex, thereby improving the flow rectifying effect of the honeycomb.

[0037] In an optional embodiment, the system further comprises an airflow duct, which is arranged at the bottom of the airflow windshield, is connected to the air outlet of the air film slit and is provided with an air outlet device, so that the airflow flowing into the airflow duct through the air outlet flows out through the air outlet device to generate an air film.

[0038] Each of the airflow ducts corresponds to an aircraft windshield, and the length and structure of each of the airflow ducts are the same as the length and structure of the corresponding aircraft windshield. Each of the airflow ducts corresponds to a film slot, and the two ends of the airflow duct are connected to the air outlets of the corresponding film slot.

[0039] The air outlet device on the airflow duct is an air outlet slot with a width less than a preset value, or the air outlet device on the airflow duct is a flow straightener net, and the air outlet slot or the flow straightener net is directed to the aircraft windshield, so that the airflow flowing out of the air outlet slot or the flow straightener net uniformly forms a film on the surface of the aircraft windshield.

[0040] In the embodiment, the pressurized air in the cockpit flows through the one-way valve, the airflow straightener and the film slot in sequence through the airflow duct to the outside of the aircraft, and uniformly forms a film on the surface of the aircraft windshield, so that the windshield is isolated from the external cold air, thereby improving the anti-icing effect of the aircraft windshield.

[0041] In an optional embodiment, the system further comprises a simulation model, and the simulation model is configured to obtain icing simulation results and determine the structure parameters of the airflow straightener and the film slot according to the icing simulation results. The structure parameters of the film slot include the slot size, the slot outlet position and the angle between the slot outlet section and the windshield, and the structure parameters of the airflow straightener include the cross-sectional shape of the flow straightener grid and the length-diameter ratio of the flow straightener grid.

[0042] Specifically, as shown in Figure 5 The embodiment can determine the structure parameters of the airflow straightener and the film slot by the following steps:

[0043] Step 1: Aircraft modeling. Model a certain type of aircraft, and the final model for numerical simulation is a model of the front part of the aircraft body with a film slot.

[0044] Step 2: Flow field simulation. Perform flow field simulation on the model in step 1 using three-dimensional simulation software.

[0045] Step 3: Icing simulation. Perform icing simulation on the flow field obtained in step 2 using three-dimensional icing simulation software.

[0046] Step 4: Result evaluation and parameter modification. Extract the icing simulation results obtained in step 3, determine whether the current film parameters can meet the anti-icing requirements, output the existing parameter combination if the requirements are met, or modify the slot width and other parameters and repeat steps 1 to 3 until the slot size and other parameters are finally determined if the anti-icing effect is not achieved.

[0047] Specifically, as shown in Figure 5As shown, the parameter modification in step four mainly includes three parts: air film slit structure parameters, hot air parameters, and air flow straightener parameters. Among them, the air film slit structure parameters include slit size, slit outlet position, and the angle between the slit outlet section and the windscreen, and the adjustment of these three parameters is realized by changing the geometric structure of the air film slit, and these three parameters will directly affect the air film coverage effect; the air flow straightener parameters include the cross-sectional shape of the straightening grid and the length-diameter ratio of the straightening grid, and these two parameters will affect the turbulence of the air flow at the inlet of the air film slit, thereby affecting the air film coverage effect; the hot air parameters include air temperature, pressure, and humidity, and the adjustment of these three parameters is realized by changing the design of the one-way valve, and these three parameters will affect the density ratio and momentum ratio of the air film outflow and external air, which will directly affect the air film coverage effect. It should be noted that the parameter modification in the embodiment can be continuously adjusted and set by human experience, and then the final parameters of the simulation results are determined as the final parameters of the air flow straightener and the air film slit.

[0048] The embodiment provides an anti-icing system of an aircraft windshield, which comprises a one-way valve, an air flow straightener and an air film slit. The air inlet of the air film slit is located in the cockpit, and the air outlet of the air film slit is located at the bottom of the aircraft windshield. The air flow straightener and the one-way valve are located in the cockpit, one end of the air flow straightener is connected to the air inlet of the air film slit, and the other end of the air flow straightener is connected to the one-way valve. The air flow straightener is used to reduce the turbulence of the air flow flowing through the one-way valve. When the one-way valve in the application is opened, the pressurized air in the cockpit flows through the one-way valve, the air flow straightener and the air film slit to the outside of the aircraft in sequence, thereby forming an air film on the surface of the aircraft windshield, isolating the windshield from the external cold air, and realizing the anti-icing effect of the aircraft windshield.

[0049] To verify the effectiveness of the anti-icing system of the aircraft windshield provided in the application, numerical simulation can be performed on the above embodiment using the corresponding aircraft flight envelope working condition of 3000m and 140m / s, and the icing rate distribution along the flow direction of the windshield surface obtained is as shown in the figure. Figure 6 Figure 6 The icing conditions of the aircraft windshield with and without air film are given in the figure. It can be seen that the anti-icing system of the aircraft windshield provided in the embodiment can achieve good anti-icing effect on the surface of the windshield.

[0050] ​Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program. The computer program can be stored in a non-volatile computer readable storage medium, and when executed, can include the processes of the above-mentioned embodiment methods. Any reference to memory, storage, database or other medium used in the embodiments provided by the present application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration but not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDR SDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synch link) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0051] Those skilled in the art can clearly understand that, for the convenience and brevity of description, only the above-mentioned division of functional units and modules is exemplified, and in actual application, the above-mentioned functions can be completed by different functional units and modules according to needs, that is, the internal structure of the device is divided into different functional units or modules to complete all or part of the above-described functions.

[0052] The above embodiments are only used to illustrate the technical solutions of the present application, but not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should be included in the protection scope of the present application.

Claims

1. An anti-icing system for an aircraft windshield, characterized in that, The system includes: a one-way valve, an airflow rectifier, and an air film slit; The air inlet of the air film slit is located inside the cockpit, and the air outlet of the air film slit is located at the bottom of the aircraft windshield. The airflow rectifier and the one-way valve are located inside the cockpit. One end of the airflow rectifier is connected to the air inlet of the film slit, and the other end of the airflow rectifier is connected to the one-way valve. The airflow rectifier is used to reduce the turbulence of the airflow flowing in through the one-way valve.

2. The system according to claim 1, characterized in that, The system also includes: an anti-icing controller; The anti-icing controller is used to control the opening and closing of the one-way valve; When the anti-icing controller controls the one-way valve to open, the pressurized air in the cockpit flows through the one-way valve, the airflow rectifier, and the air film slit to the outside of the aircraft.

3. The system according to claim 2, characterized in that, The system also includes: a temperature sensor, a humidity sensor, and an icing sensor; The anti-icing controller is also used to acquire sensor data corresponding to the temperature sensor, humidity sensor and icing sensor respectively, and determine the opening or closing of the one-way valve based on the sensor data.

4. The system according to claim 1, characterized in that, The system also includes: an airflow duct; The airflow duct is located at the bottom of the airflow windshield. The airflow duct is connected to the air outlet of the air film slit. An air outlet device is provided on the airflow duct so that the airflow flowing into the airflow duct through the air outlet flows out through the air outlet device to generate an air film.

5. The system according to claim 4, characterized in that, Each airflow duct corresponds to an aircraft windshield, and the length and structural orientation of each airflow duct are matched with the length and structural orientation of its corresponding aircraft windshield.

6. The system according to claim 5, characterized in that, Each of the airflow ducts corresponds to an air film slit, and the two ends of the airflow duct are respectively connected to the air outlet of its corresponding air film slit.

7. The system according to claim 6, characterized in that, The air outlet device on the airflow duct is an air outlet slit with a width smaller than a preset value, or the air outlet device on the airflow duct is a rectifier mesh. The air outlet slit and the rectifier mesh are oriented towards the aircraft windshield, so that the airflow flowing out through the air outlet slit or the rectifier mesh uniformly generates an air film on the surface of the aircraft windshield.

8. The system according to any one of claims 1-7, characterized in that, The system also includes: a simulation model; The simulation model is used to obtain icing simulation results, and to determine the structural parameters corresponding to the airflow rectifier and the air film slit based on the icing simulation results.

9. The system according to claim 8, characterized in that, The structural parameters of the air film slit include: slit size, slit outlet position, and the angle between the slit outlet section and the windshield; the structural parameters of the airflow rectifier include: the cross-sectional shape of the rectifier grid and the length-to-diameter ratio of the rectifier grid.

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