Electric heating anti-icing and deicing system and method based on distributed optical fiber temperature sensor

Abstract

The invention belongs to the field of aircraft anti-icing and de-icing, and particularly relates to an electric heating anti-icing and de-icing system and method based on a distributed optical fiber temperature sensor, and the system comprises the distributed optical fiber temperature sensor, a controller, and a heating assembly. The surface of the wing is divided into different subareas and numbered, and at least one heating assembly is arranged in each subarea; the distributed optical fiber temperature sensors are made of optical fibers, are pre-buried in the wing skin and pass through all the subareas, and each subarea is internally provided with at least two temperature measuring points; the distributed optical fiber temperature sensor is used for collecting temperature data of the surface of the wing and sending the temperature data to the controller; and the controller compares the temperature of each subarea with a theoretical temperature, when the temperature of each subarea is lower than the lower limit of the theoretical temperature, the heating assembly of the corresponding subarea is controlled to start heating, and when the temperature of each subarea is higher than the upper limit of the theoretical temperature, the heating assembly of the corresponding subarea is controlled to stop heating.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft anti-icing and deicing, and relates to a novel anti-icing and deicing system and method, which is mainly used for aircraft wing anti-icing and deicing, and specifically relates to an electric heating anti-icing and deicing system and method based on distributed optical fiber temperature sensors. Background Art

[0002] Aircraft icing is one of the serious problems that threaten flight safety, and flight accidents caused by icing occur from time to time. Specifically, ice on the leading edge of the aircraft wing affects the lift characteristics of the aircraft, causes a large range of airflow separation on the upper wing surface of the aircraft, and destroys the design surface. Icing will reduce lift, increase drag, reduce the stall angle of attack, and increase the stall speed. Even relatively slight ice contamination on the leading edge of the wing can cause a significant deterioration in the aerodynamic characteristics of the aircraft. Ice in front of the aileron will also affect the normal operation of the aileron, and asymmetric ice on both sides of the wing can also cause the aircraft to roll uncommanded.

[0003] The electric thermal anti-icing system is to place heating elements such as resistance wires or thin film heaters in the wing skin, and heat the wing skin through the heating elements to prevent deicing. The disadvantage of electric thermal anti-icing is that it consumes a lot of power, and requires the aircraft to be equipped with high-power power generation equipment, which is difficult to apply to aircraft with relatively tight power consumption; and the traditional electric thermal anti-icing system cannot adjust the zone heating strategy in time according to the zone temperature, which is prone to uneven heating, leading to local overheating or overflow due to insufficient heating. Summary of the invention

[0004] In view of the shortcomings of the existing electric heating anti-icing technology, the present invention proposes an electric heating anti-icing system and method based on distributed optical fiber temperature sensors, which can be used for aircraft wing anti-icing. While achieving the anti-icing function, it can effectively reduce the energy consumption of the aircraft and avoid local overheating and overflow caused by uneven heating.

[0005] The technical solution of the present invention:

[0006] An electric heating anti-icing system based on a distributed optical fiber temperature sensor comprises: an optical fiber temperature sensor, a controller, and a heating component;

[0007] The wing surface is divided into different zones and numbered, and each zone has at least one heating element;

[0008] The optical fiber temperature sensor is embedded in the wing skin and passes through all the partitions. There are at least 4 temperature measurement points in each partition.

[0009] Distributed optical fiber temperature sensors are used to collect temperature data on the wing surface and send the temperature data to the controller;

[0010] The controller compares the temperature of each partition with the theoretical temperature zone. When the temperature of each partition is lower than the lower limit of the theoretical temperature zone, the controller controls the heating component of the corresponding partition to start heating. When the temperature of each partition is higher than the upper limit of the theoretical temperature zone, the controller controls the heating component of the corresponding partition to stop heating.

[0011] Furthermore, the optical fiber temperature sensor includes: a laser, a temperature-sensitive optical fiber, and an optical fiber temperature demodulator;

[0012] The laser is used to excite high-energy laser light and inject it into the temperature-sensitive optical fiber;

[0013] The temperature-sensing optical fiber is pre-buried in the wing skin and passes through all partitions to achieve distributed temperature measurement of the wing skin;

[0014] The optical fiber temperature demodulator is used to demodulate the optical signal into temperature data, and the demodulation accuracy is not less than 4 temperature data in each partition.

[0015] Furthermore, each slat skin is divided into a hot knife area, an upper wing surface area, and a lower wing surface area in the chord direction; and is divided into at least 6 partitions in the span direction.

[0016] Furthermore, a temperature-sensitive optical fiber is pre-buried in each slat of the aircraft wing; the temperature-sensitive optical fibers are distributed end to end in an S-shape in each slat, covering all partitions of the slat.

[0017] Further, the temperature-sensitive optical fiber is arranged in the center of the hot knife area, the upper wing surface area, and the lower wing surface area in the chord direction;

[0018] Furthermore, the heating component is a resistance wire, a heating film, or a heating pad.

[0019] Furthermore, the controller is a distributed controller having a plurality of control units, and each control unit is numbered in a one-to-one correspondence with each partition.

[0020] An electric heating anti-icing method based on distributed optical fiber temperature sensors is implemented based on the system, comprising the following steps:

[0021] Step 1: Divide the wing surface into different zones and number them;

[0022] Step 2: According to the slat skin partitioning, set the anti-icing theoretical temperature range for the hot knife area, the upper wing surface area, and the lower wing surface area respectively;

[0023] Step 3: Collect temperature data of different partitions through distributed optical fiber temperature sensors;

[0024] Step 4: Calculate the temperature value of each partition based on the temperature data of different partitions;

[0025] Step 4: Each control unit compares the temperature value of its own partition with the theoretical anti-icing temperature range of its own partition. If it is lower than the lower limit of the theoretical anti-icing temperature range, the heating component in its own partition is controlled to work; if it is higher than the upper limit of the theoretical anti-icing temperature range, the heating component in its own partition is controlled to stop working.

[0026] Furthermore, the single working time of the heating component is T; the value of T is 5min to 10min.

[0027] Furthermore, the temperature value of each partition is the average value of all temperature data in the corresponding partition.

[0028] Beneficial Effects

[0029] 1. The electric heating anti-icing system based on distributed optical fiber temperature sensors of the present invention realizes the measurement of skin temperature by embedding temperature-sensitive optical fibers in the skin. Compared with the traditional method of arranging surface-mounted temperature sensors on the skin surface to realize skin temperature measurement, it avoids the influence of ambient temperature on skin temperature measurement and can more accurately reflect the real temperature of the skin;

[0030] 2. The electric heating anti-icing system based on distributed optical fiber temperature sensors of the present invention realizes skin temperature measurement through partition setting and arrangement of temperature-sensitive optical fibers. Compared with the traditional method of arranging surface-mounted temperature sensors at specific positions on the skin surface to realize skin temperature measurement, multi-point measurement of skin temperature is realized, providing input for skin partition heating control strategy;

[0031] 3. The electric heating anti-icing system based on the distributed optical fiber temperature sensor of the present invention collects at least 4 temperature data in a single partition and takes the average value as the temperature value of each partition, thereby avoiding the wrong heating control caused by the error of single temperature data analysis;

[0032] 4. The electric heating anti-icing system based on distributed optical fiber temperature sensors of the present invention divides the skin in the chord direction and span direction, controls the heating components of each partition separately, and controls the temperature of each partition within the corresponding anti-icing theoretical temperature range. Compared with the overall heating of the non-partitioned electric heating anti-icing system, the heating power can be reduced, and the energy consumption of the aircraft can be reduced;

[0033] 5. The electric heating anti-icing system based on distributed optical fiber temperature sensors of the present invention controls the operation of the heating components of each partition separately. Compared with the overall heating of the non-partitioned electric heating anti-icing system, it can effectively avoid damage to the skin structure caused by regional overheating and overflow ice caused by regional overcooling. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 Schematic diagram of slat distribution of aircraft wing;

[0035] Figure 2 Schematic diagram of the partitioning of slat R3;

[0036] Figure 3 This is a schematic diagram of the layout of the temperature sensing optical fiber;

[0037] Figure 4 A schematic diagram of the cross-linking relationship of the electric heating anti-icing system based on the distributed optical fiber temperature sensor of the present invention;

[0038] Reference numerals: A is the hot knife area, B is the upper wing area, and C is the lower wing area;

[0039] 1 is the laser, 2 is the temperature-sensing optical fiber, 3 is the optical fiber temperature demodulator, 4 is the controller, 5 is the heating component, 6 is the skin, and 7 is the temperature measuring point. DETAILED DESCRIPTION

[0040] This section is an embodiment of the present invention, which is used to explain and illustrate the technical solution of the present invention.

[0041] An electric heating anti-icing system based on distributed optical fiber temperature sensors includes an optical fiber temperature sensor, a controller 4, a heating component 5 and a skin 6, wherein the optical fiber temperature sensor is composed of a laser 1, a temperature-sensitive optical fiber 2 and an optical fiber temperature demodulator 3.

[0042] Schematic diagram of the cross-linking relationship of the electric heating anti-icing system based on the distributed optical fiber temperature sensor of the present invention, the temperature sensing optical fiber 2 and the heating component 5 are embedded in the skin 6. The laser excites high-energy laser and injects it into the temperature sensing optical fiber, the optical fiber temperature demodulator 3 demodulates the optical signal into a temperature signal and sends it to the controller 4, and the controller 4 controls the operation of the heating component 5.

[0043] The controller 4 described in the present invention contains multiple control units, each of which controls the heating component 5 of the corresponding partition, and adopts a negative feedback regulation mechanism to compare the received skin 6 temperature value with the theoretical anti-icing temperature range of its own partition. If it is lower than the lower limit of the theoretical anti-icing temperature range, the heating component in its own partition is controlled to work; if it is higher than the upper limit of the theoretical anti-icing temperature range, the heating component in its own partition is controlled to stop working.

[0044] The specific implementation of the present invention is further described below in conjunction with the accompanying drawings.

[0045] like Figure 1 The figure shows the schematic diagram of the slat distribution of the aircraft wing. The slat on the left side of the aircraft wing is divided into L3, L4, and L5 in sequence, and the slat on the right side of the aircraft wing is divided into R3, R4, and R5 in sequence.

[0046] like Figure 2The partition diagram of the slat R3 shown in the figure shows that the slat is divided into a hot knife area A, an upper wing area B, and a lower wing area C along the chord direction, and the slat is equally divided into 6 areas along the span direction. Each slat is divided into 18 areas, which are marked as R3A1, R3A2, R3A3, R3A4, R3A5, R3A6, R3B1, R3B2, R3B3, R3B4, R3B5, R3B6, R3C1, R3C2, R3C3, R3C4, R3C5, and R3C6 respectively.

[0047] Figure 3 Figure 1 is a schematic diagram of the arrangement of temperature-sensitive optical fibers. Each slat skin is embedded with a temperature-sensitive optical fiber. The optical fibers are arranged in an S shape and pass through the 18 partitions of the slat in sequence. The temperature-sensitive optical fibers are arranged in the middle of the hot knife area A, the upper wing area B, and the lower wing area C in the chord direction. The accuracy setting of the optical fiber temperature demodulator 3 ensures that there are four temperature measurement points 7 in each partition.

[0048] Figure 4 The figure is a schematic diagram of the cross-linking relationship of the electric heating anti-icing and de-icing system based on the distributed optical fiber temperature sensor of the present invention. The temperature-sensing optical fiber 2 and the heating assembly 5 are embedded in the skin 6. The laser excites high-energy laser and injects it into the temperature-sensing optical fiber. The optical fiber temperature demodulator 3 demodulates the optical signal into a temperature signal and sends it to the controller 4. The controller 4 controls the operation of the heating assembly 5.

[0049] For R3 slats, the target temperature interval of hot knife zone A is set to 30℃~40℃, that is, the target temperature interval of R3A1, R3A2, R3A3, R3A4, R3A5, R3A6 partitions is set to 30℃~40℃; the target temperature interval of upper wing zone B is set to 20℃~30℃, that is, the target temperature interval of R3B1, R3B2, R3B3, R3B4, R3B5, R3B6 partitions is set to 20℃~30℃; the target temperature interval of lower wing surface C is set to 10℃~30℃, that is, the target temperature interval of R3C1, R3C2, R3C3, R3C4, R3C5, R3C6 partitions is set to 10℃~30℃. The target temperature interval settings for L3, L4, L5, R4, and R5 slats are consistent with those for R3 slats.

[0050] The controller 4 is set with a target temperature range for each partition. The optical fiber temperature sensor measures and demodulates the temperature signal in real time. The controller 4 calculates the average value of the four received temperature signals as the temperature value of the partition. Taking partition R3A1 as an example, its target temperature range is set to 30℃~40℃. When the temperature value measured by the optical fiber temperature sensor of the R3A1 partition is lower than 30℃, the heating component of the R3A1 partition is controlled to start working; when the temperature value measured by the optical fiber temperature sensor of the R3A1 partition is higher than 40℃, the heating component of the R3A1 partition is controlled to stop working. In order to avoid continuous start and stop of the heating components of each partition in a short period of time, the single working time of the heating component is 5min~10min.

[0051] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the scope disclosed in the present invention should be covered within the protection scope of the present invention.

Claims

1. An electric heating anti-icing system based on distributed optical fiber temperature sensors, characterized in that: The system includes: optical fiber temperature sensor, controller, heating component; The wing surface is divided into different zones and numbered, and each zone has at least one heating element; The optical fiber temperature sensor is embedded in the wing skin and passes through all the partitions. There are at least 4 temperature measurement points in each partition. Distributed optical fiber temperature sensors are used to collect temperature data on the wing surface and send the temperature data to the controller; The controller compares the temperature of each partition with the theoretical temperature zone. When the temperature of each partition is lower than the lower limit of the theoretical temperature zone, the controller controls the heating component of the corresponding partition to start heating. When the temperature of each partition is higher than the upper limit of the theoretical temperature zone, the controller controls the heating component of the corresponding partition to stop heating.

2. The system according to claim 1, characterized in that: The optical fiber temperature sensor includes: a laser, a temperature-sensing optical fiber, and an optical fiber temperature demodulator; The laser is used to excite high-energy laser light and inject it into the temperature-sensitive optical fiber; The temperature-sensing optical fiber is pre-buried in the wing skin and passes through all partitions to achieve distributed temperature measurement of the wing skin; The optical fiber temperature demodulator is used to demodulate the optical signal into temperature data, and the demodulation accuracy is not less than 4 temperature data in each partition.

3. The system according to claim 2, characterized in that: Each slat skin is divided into a hot knife area, an upper wing surface area, and a lower wing surface area in the chord direction; and is divided into at least 6 partitions in the span direction.

4. The system according to claim 3, characterized in that: A temperature-sensitive optical fiber is pre-buried in each slat of the aircraft wing; the temperature-sensitive optical fibers are distributed in an S-shape end to end in each slat, covering all partitions of the slat.

5. The system according to claim 4, characterized in that: The temperature-sensitive optical fiber is arranged in the center of the hot knife area, the upper wing surface area, and the lower wing surface area in the chord direction.

6. The system according to claim 5, characterized in that: The heating element is a resistance wire, a heating film, or a heating pad.

7. The system according to claim 6, characterized in that: The controller is a distributed controller, which is provided with a plurality of control units, and each control unit is numbered correspondingly to each partition.

8. An electric heating anti-icing method based on distributed optical fiber temperature sensors, implemented based on the system of any of the preceding claims, characterized in that: The following steps are involved: Step 1: Divide the wing surface into different zones and number them; Step 2: According to the slat skin partitioning, set the anti-icing theoretical temperature range for the hot knife area, the upper wing surface area, and the lower wing surface area respectively; Step 3: Collect temperature data of different partitions through distributed optical fiber temperature sensors; Step 4: Calculate the temperature value of each partition based on the temperature data of different partitions; Step 4: Each control unit compares the temperature value of its own partition with the theoretical anti-icing temperature range of its own partition. If it is lower than the lower limit of the theoretical anti-icing temperature range, the heating component in its own partition is controlled to work; if it is higher than the upper limit of the theoretical anti-icing temperature range, the heating component in its own partition is controlled to stop working.

9. The method according to claim 8, characterized in that: The single working time of the heating component is T; the value of T is 5min to 10min.

10. The method according to claim 2, characterized in that: The temperature value of each partition is the average value of all temperature data in the corresponding partition.

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