Anti-icing system of aircraft windshield

Abstract

The invention 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 technical field of aircraft electric environmental control, and in particular to an anti-icing system for an aircraft windshield. Background Art

[0002] Ice formation during flight will threaten flight safety. Ice formation will increase the weight of the aircraft, damage the aerodynamic shape of the aircraft, and affect the normal operation of aircraft components. Aircraft parts prone to ice formation include windshields, wings, and engine nacelle lips. 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 heat anti-icing technology, and gas heat anti-icing technology.

[0003] At present, electric heating anti-icing technology can be used to de-ice aircraft windshields. This electric heating anti-icing technology heats the surface of the iced area by electric heating, and then transfers the heat to the surface of the ice layer by conduction. However, this technology has problems such as high power consumption and anti-icing efficiency. Summary of the invention

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

[0005] An embodiment of the present invention provides an anti-icing system for an aircraft windshield, the system comprising: a one-way valve, an airflow straightener 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 windshield of the aircraft;

[0007] The airflow straightener and the one-way valve are located inside the cockpit, one end of the airflow straightener is connected to the air inlet of the air film slit, and the other end of the airflow straightener is connected to the one-way valve; the airflow straightener is used to reduce the turbulence of the airflow flowing in 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 one-way valve to open, the pressurized air in the cockpit flows through the one-way valve, the airflow straightener and the air film slit in sequence to the outside of the aircraft.

[0011] In an optional embodiment, the system further comprises: a temperature sensor, a humidity sensor and an ice sensor;

[0012] The anti-icing controller is also used to obtain sensor data corresponding to the temperature sensor, the humidity sensor and the icing sensor respectively, and determine the 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 windshield, the airflow duct is connected to the air outlet of the air film slit, and 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 of the airflow ducts corresponds to an aircraft windshield, and the length and structural orientation of each airflow duct match the length and structural orientation of the corresponding aircraft windshield.

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

[0017] In an optional embodiment, the air outlet device on the airflow duct is a narrow air outlet slit with a width less than a preset value, or the air outlet device on the airflow duct is a rectifying net, and the direction of the narrow air outlet slit and the rectifying net faces the aircraft windshield, so that the airflow flowing out through the narrow air outlet slit or the rectifying net uniformly forms 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 used to obtain icing simulation results, and determine the structural parameters corresponding to the airflow straightener and the air film slit respectively according to the icing simulation results.

[0020] In an optional embodiment, the structural parameters of the air film slit include: slit size, slit outlet position and angle between the slit outlet section and the windshield; the structural parameters of the airflow straightener include: cross-sectional shape of the straightening grid and aspect ratio of the straightening grid.

[0021] The present invention provides an anti-icing system for an aircraft windshield, which includes: a one-way valve, an airflow straightener, 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 straightener and the one-way valve are located inside the cockpit, one end of the airflow straightener is connected to the air inlet of the air film slit, and the other end of the airflow straightener is connected to the one-way valve; the airflow straightener is used to reduce the turbulence of the airflow flowing in through the one-way valve. When the one-way valve in the present application is opened, the pressurized air in the cockpit flows through the one-way valve, the airflow straightener, and the air film slit in turn to the outside of the aircraft, thereby forming a layer of air film on the surface of the aircraft windshield, isolating the windshield from the external cold air, thereby achieving an anti-icing effect on the aircraft windshield. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 A structural diagram of an aircraft windshield anti-icing system provided in this application;

[0023] Figure 2 A schematic diagram of an anti-icing system for an aircraft windshield provided in this application;

[0024] Figure 3 An example diagram of the location of an air film slit provided in this application;

[0025] Figure 4 An application architecture diagram of an aircraft windshield anti-icing system provided in this application;

[0026] Figure 5 A simulation flow chart of an aircraft windshield anti-icing system provided in this application;

[0027] Figure 6 A schematic diagram of an anti-icing effect provided for this application. DETAILED DESCRIPTION

[0028] In order to better understand the above-mentioned technical scheme, the technical scheme of the embodiments of the present application is described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present application and the specific features in the embodiments are detailed descriptions of the technical scheme of the embodiments of the present application, rather than limitations on the technical scheme of the present application. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments may be combined with each other.

[0029] See also Figure 1 , an anti-icing system for an aircraft windshield is provided in an embodiment of the present invention, the system comprising: a one-way valve, an airflow straightener and an air film slit.

[0030] Specifically, 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 straightener and the one-way valve are located inside the cockpit, one end of the airflow straightener is connected to the air inlet of the air film slit, and the other end of the airflow straightener is connected to the one-way valve; the airflow straightener is used to reduce the turbulence of the airflow flowing in through the one-way valve.

[0031] In this embodiment, the air film slit directly penetrates the aircraft skin. The specific structure is as follows Figures 1 to 3 As shown. The air film slit will open directly on the surface of the cockpit skin, the air film slit air inlet is located inside the cockpit, and the air film slit air outlet is located outside the aircraft. Hot air is the pressurized air in the cabin. The airflow rectifier is located inside the cockpit, and the two ends are connected to the air film slit air inlet and the one-way valve respectively. The one-way valve is located inside the cockpit and is exposed to the pressurized air environment in the cockpit. When the one-way valve is opened, 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, thereby forming a layer of air film on the surface of the aircraft windshield, thereby achieving an anti-icing effect on the aircraft windshield.

[0032] like Figure 4 As shown, in an optional embodiment, the system provided in this embodiment further 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. It should be noted that in this embodiment, in addition to being automatically controlled by the anti-icing controller, the one-way valve can also be manually controlled by the driver according to actual conditions.

[0033] Furthermore, in order to realize automatic control of the opening or closing of the one-way valve by the anti-icing controller, the system provided in this embodiment further includes: a temperature sensor, a humidity sensor and an ice sensor. The anti-icing controller is used to obtain sensor data corresponding to the temperature sensor, the humidity sensor and the ice sensor respectively, and determine the opening or closing of the one-way valve according to the sensor data.

[0034] like Figure 4As shown, an anti-icing system for an aircraft windshield provided in an embodiment of the present application has as its main components an anti-icing controller, a nose sensor, a front windshield actuator, an air conditioning system, an airflow rectifier and an air film slit. Among them, 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 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 ice detection sensor, which are generally installed on the outside of the aircraft nose and are generally probe-type sensors extending out of the aircraft. The front windshield actuator refers to a windshield wiper and a windshield cleaning device, which are generally located in front of the aircraft windshield. The air conditioning system is generally installed in various pressurized areas inside the aircraft cabin.

[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 meteorological conditions are met or icing has occurred, they input signals to the anti-icing controller. The anti-icing controller controls the one-way valve to open, so that the hot air flows through the one-way valve, the airflow rectifier and the air film slit flow in turn to generate an air film. The function of the airflow rectifier is to reduce the turbulence of the airflow, making the air film outflow more uniform and staying farther on the aircraft windshield surface.

[0036] Specifically, during the flight of the aircraft, the ice detector will always read the data of the aircraft temperature sensor, pressure sensor, speed sensor and ice sensor. When a specific temperature, pressure, speed and ice detection signal combination is met, the ice 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 one-way valve to open. Among them, the one-way valve is located inside the cockpit, directly connecting 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 to the outside of the aircraft. The airflow rectifier is a honeycomb rectifier, which is a rectifier that can divide large-scale vortices into small-scale vortices. This embodiment can change the aspect ratio of the honeycomb unit to change the inertial force and viscous dissipation to reduce the scale and energy of the vortex, so as to improve the rectification effect of the honeycomb.

[0037] In an optional embodiment, the system also includes: an airflow duct; the airflow duct is arranged at the bottom of the airflow windshield, the airflow duct is connected to the air outlet of the air film slit, and 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.

[0038] Each of the airflow ducts corresponds to an aircraft windshield, and the length and structural orientation of each airflow duct are the same as the length and structural orientation of the corresponding aircraft windshield. 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 the corresponding air film slit.

[0039] The air outlet device on the airflow duct is a narrow air outlet slit with a width smaller than a preset value, or the air outlet device on the airflow duct is a rectifying net, and the direction of the narrow air outlet slit and the rectifying net faces the aircraft windshield, so that the airflow flowing out through the narrow air outlet slit or the rectifying net uniformly forms an air film on the surface of the aircraft windshield.

[0040] In this embodiment, 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 through the airflow duct, and a layer of air film is evenly formed on the surface of the aircraft windshield to isolate the windshield from the external cold air, thereby achieving improved anti-icing effect on the aircraft windshield through this embodiment.

[0041] In an optional embodiment, the system further includes: a simulation model; the simulation model is used to obtain icing simulation results, and determine the structural parameters corresponding to the airflow rectifier and the air film slit according to the icing simulation results. 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 aspect ratio of the rectifier grid.

[0042] Specific as Figure 5 As shown, in this embodiment, the structural parameters corresponding to the airflow straightener and the air film slit can be determined by the following steps:

[0043] Step 1: Aircraft modeling. Model a certain type of aircraft, and the model finally used for numerical simulation includes the front fuselage of the aircraft with air film slits.

[0044] Step 2: Flow field simulation: Use 3D simulation software to perform flow field simulation on the model described in step 1.

[0045] Step 3: Icing simulation: The flow field obtained in step 2 is simulated using three-dimensional icing simulation software to simulate the icing condition of the nose.

[0046] Step 4: Result evaluation and parameter modification. Extract the icing simulation results obtained in step 3 to determine whether the current air film parameters can meet the anti-icing requirements. If they can, output the existing parameter combination. If they cannot achieve the anti-icing effect, modify the slit width and other parameters and repeat the above steps 1 to 3 until the slit size and other parameters are finally determined.

[0047] Specifically, Figure 5As shown, the parameter modification in step 4 mainly includes three parts: air film slit structural parameters, hot air parameters, and airflow rectifier parameters. Among them, the air film slit structural parameters include slit size, slit outlet position, and the angle between the slit outlet section and the windshield. The adjustment of these three parameters is achieved by changing the geometric structure of the air film slit. These three parameters will directly affect the air film covering effect; the airflow rectifier parameters include the cross-sectional shape of the rectifier grid and the aspect ratio of the rectifier grid. These two parameters will affect the airflow turbulence at the inlet of the air film slit, thereby affecting the air film covering effect; the hot air parameters include air temperature, pressure and humidity. The adjustment of these three parameters is achieved by changing the design of the one-way valve. These three parameters will affect the density ratio and momentum ratio of the air film outflow and the external air, which will directly affect the air film covering effect. It should be noted that the parameter modification in this embodiment can be continuously adjusted and set by manual experience, and then the final parameters of the simulation results are determined as the final parameters of the airflow rectifier and the air film slit.

[0048] The present embodiment provides an anti-icing system for an aircraft windshield, the system comprising: a one-way valve, an airflow straightener 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 straightener and the one-way valve are located inside the cockpit, one end of the airflow straightener is connected to the air inlet of the air film slit, and the other end of the airflow straightener is connected to the one-way valve; the airflow straightener is used to reduce the turbulence of the airflow flowing in through the one-way valve. When the one-way valve in the present application is opened, the pressurized air in the cockpit flows through the one-way valve, the airflow straightener and the air film slit successively to the outside of the aircraft, thereby forming a layer of air film on the surface of the aircraft windshield, isolating the windshield from the external cold air, thereby achieving an anti-icing effect on the aircraft windshield.

[0049] In order to verify the effectiveness of the anti-icing system for the aircraft windshield described in the present application, the above embodiment can be numerically simulated using the aircraft flight envelope conditions corresponding to 3000m and 140m / s. The distribution of the windshield surface icing rate along the flow direction is as follows: Figure 6 shown. Figure 6 The icing conditions of the aircraft windshield with and without air film are given in FIG. 1 . It can be seen that the anti-icing system for the aircraft windshield provided in this embodiment can achieve a good anti-icing effect on the windshield surface.

[0050] Those of ordinary skill in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing related hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application may include non-volatile and / or volatile memory. Non-volatile memory may include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory may include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), RAMbus direct RAM (RDRAM), direct RAMbus dynamic RAM (DRDRAM), and RAMbus dynamic RAM (RDRAM), etc.

[0051] Those skilled in the art can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional units and modules is used as an example. In actual applications, the above-mentioned functions can be distributed and completed by 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.

[0052] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the protection scope of the present invention.

Claims

1. An anti-icing system for an aircraft windshield, characterized in that: The system comprises: a one-way valve, an airflow straightener 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 windshield of the aircraft; The airflow straightener and the one-way valve are located inside the cockpit, one end of the airflow straightener is connected to the air inlet of the air film slit, and the other end of the airflow straightener is connected to the one-way valve; the airflow straightener 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 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 one-way valve to open, the pressurized air in the cockpit flows through the one-way valve, the airflow straightener and the air film slit in sequence 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 ice sensor; The anti-icing controller is also used to obtain sensor data corresponding to the temperature sensor, the humidity sensor and the icing sensor respectively, and determine the opening or closing of the one-way valve according to the sensor data.

4. The system according to claim 1, characterized in that The system further comprises: an airflow duct; The airflow duct is arranged at the bottom of the airflow windshield, the airflow duct is connected to the air outlet of the air film slit, and 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.

5. The system according to claim 4, characterized in that Each of the airflow ducts corresponds to an aircraft windshield, and the length and structural orientation of each airflow duct match the length and structural orientation of the 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 two ends of the airflow duct are respectively connected to the air outlets of the corresponding air film slits.

7. The system according to claim 6, characterized in that The air outlet device on the airflow duct is a narrow air outlet slit with a width smaller than a preset value, or the air outlet device on the airflow duct is a rectifying net, and the direction of the narrow air outlet slit and the rectifying net faces the aircraft windshield, so that the airflow flowing out through the narrow air outlet slit or the rectifying net uniformly forms an air film on the surface of the aircraft windshield.

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

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