A wing surface monitoring system and sensor arrangement method thereof

Abstract

The present application discloses a wing surface monitoring system and a sensor arrangement method thereof, which relates to the technical field of wing surface monitoring, and is used to solve the technical problem in the prior art that when monitoring the wing surface, the wing surface cannot be monitored comprehensively and targetedly due to the single arrangement of sensors on the wing surface. The system includes a plurality of sensors, all installed on the wing surface, for monitoring the changing parameters of the wing surface, and the deformation of the wing between two adjacent sensors is the same; a power supply module, installed on the wing surface and electrically connected to the sensors, for supplying power to the sensors. Through the above technical solution, the present application arranges a plurality of sensors according to the actual deformation of the wing of the aircraft during flight, thus breaking the single arrangement of sensors on the wing surface in the prior art, so that the surface of the wing can be monitored more comprehensively and targetedly.

Description

Technical Field

[0001] The present application relates to the technical field of wing surface monitoring, and in particular to a wing surface monitoring system and a sensor arrangement method thereof. Background Art

[0002] The wing is the main load-bearing component of the aircraft's aerodynamic load and external load. It will produce significant deformation due to the action of external forces during flight. Therefore, monitoring the wing surface is related to flight safety.

[0003] At present, the surface of the wing is mainly monitored by pressure sensors and sensors, such as monitoring the pressure and deformation of the wing surface. The sensors are pasted on the wing surface, and batteries are installed on the wing surface to power the sensors. The sensors are generally arranged on the parts of the wing surface that need attention. Although this method can monitor the surface of the wing, due to the single arrangement of sensors on the wing surface, such as arranging sensors at equal intervals before the wing is deformed, or arranging only one or two sensors, it is not possible to monitor the surface of the wing comprehensively and specifically. Summary of the invention

[0004] The main purpose of the present application is to provide a wing surface monitoring system and a sensor arrangement method thereof, aiming to solve the technical problem in the prior art that when monitoring the wing surface, the sensor is arranged in a single manner on the wing surface, and therefore the wing surface cannot be monitored comprehensively and specifically.

[0005] To achieve the above objectives, the present application provides a wing surface monitoring system in a first aspect, the system comprising:

[0006] A plurality of sensors are mounted on the wing surface, and the actual deformation of the wing between two adjacent sensors is the same, and the sensors are used to monitor the change parameters of the wing surface, and the actual deformation is the deformation of the wing during the flight of the aircraft;

[0007] A power supply module is installed on the surface of the wing, and the power supply module is electrically connected to the multiple sensors, and the power supply module is used to supply power to the sensors.

[0008] Optionally, the system further comprises:

[0009] A voltage stabilizing module, electrically connected to the power supply module, for converting the electric energy of the power supply module into a stable voltage and outputting the stable voltage;

[0010] The energy storage module is electrically connected to the voltage stabilizing module and the sensor, and is used to store the stable voltage output by the voltage stabilizing module and to power the sensor through the stable voltage.

[0011] Optionally, there are multiple energy storage modules, and each energy storage module includes multiple polymer physical batteries.

[0012] Optionally, the power supply module is a solar panel, which is used to convert solar energy into electrical energy and supply power to the sensor.

[0013] Optionally, the solar panel comprises a flexible solar panel, and the flexible solar panel is adhered to the wing.

[0014] Optionally, the flexible solar cell panel comprises a plurality of solar cells, and the plurality of solar cells are connected in series in sequence.

[0015] Optionally, the plurality of solar cells are welded by copper foil.

[0016] Optionally, the changing parameters include pressure and deformation of the wing surface.

[0017] Optionally, the wing includes a fixed end, and a deformation gradient close to the fixed end is smaller than a deformation gradient far from the fixed end.

[0018] In a second aspect, the present application also provides a sensor arrangement method for a wing surface monitoring system, the method comprising:

[0019] Applying a fixed constraint at one end of the wing and applying an upward uniform load at the bottom of the wing to simulate the lift force on the wing during flight;

[0020] Performing static simulation on the wing to obtain a deformation diagram of the wing under a uniformly distributed load, wherein the deformation diagram includes a deformation gradient of the wing;

[0021] A plurality of sensors are arranged based on the magnitude of the deformation gradient, wherein the simulated deformation amounts of the wings between two adjacent sensors are the same.

[0022] Optionally, the wing includes a fixed end, and the deformation gradient close to the fixed end is smaller than the deformation gradient away from the fixed end;

[0023] The step of arranging a plurality of sensors based on the magnitude of the deformation gradient comprises:

[0024] Arrange a plurality of the sensors at a first spacing at a position close to the fixed end;

[0025] A plurality of the sensors are arranged at a second spacing at a position away from the fixed end, wherein the first spacing is smaller than the second spacing. Through the above technical solution, the present application has at least the following beneficial effects:

[0026] A wing surface monitoring system and a sensor arrangement method thereof proposed in an embodiment of the present application install multiple sensors on the surface of the wing and ensure that the deformation of the wing between two adjacent sensors is the same. Since multiple sensors are arranged according to the actual deformation of the wing during the flight of the aircraft, the single arrangement method of sensors on the wing surface in the prior art is broken, so that the surface of the wing can be monitored more comprehensively and specifically. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 A schematic diagram of a wing surface monitoring system provided for this application;

[0028] Figure 2 A schematic diagram of the constraints and loads on the wing in the system provided in this application;

[0029] Figure 3 A schematic diagram of the deformation of the wing under uniform load in the system provided in this application;

[0030] Figure 4 A schematic diagram of deformation curves of each point along the z direction of the wing under uniform load in the system provided by the present application;

[0031] Figure 5 A schematic diagram of the arrangement of sensors on the wing in the system provided in this application;

[0032] Figure 6 This is a schematic diagram of connecting multiple flexible solar cells in the system provided by this application.

[0033] Figure 7 A flow chart of a sensor arrangement method for a wing surface monitoring system provided in the present application;

[0034] Figure 8 The present invention provides a flow chart for arranging multiple sensors based on the magnitude of deformation gradient in the method provided by the present application.

[0035] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0036] It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0037] The wing generally has a large area, and the deformation of each part under flight load is not the same. This means that if fewer sensors are arranged on the wing surface, the deformation of the wing surface cannot be fully measured. If too many sensors are installed, the balance of the wing will be affected and the workload of arranging sensors will increase. In the prior art, sensors are arranged at equal intervals before the wing deforms, and only one or two sensors are used. In this way, the arrangement of sensors on the wing surface is single, and targeted measurements of certain areas of the wing surface with larger deformation cannot be achieved.

[0038] In order to solve the above technical problems, Figure 1 As shown, the present application provides a wing surface monitoring system, the system comprising:

[0039] Multiple sensors are installed on the surface of the wing, and the actual deformation of the wing between two adjacent sensors is the same, and the sensors are used to monitor the changing parameters of the wing surface, wherein the actual deformation is the deformation of the wing of the aircraft during flight; a power supply module is installed on the surface of the wing, and the power supply module is electrically connected to the multiple sensors, and the power supply module is used to power the sensors.

[0040] In this embodiment, the sensor may be a displacement sensor, and the power supply module supplies power to multiple sensors, and the sensors monitor the change parameters of the wing surface, where the change parameters include the pressure and deformation of the wing surface. Figure 2 As shown in the figure, a fixed constraint is applied to the left end of the wing, the right end is a free end, and an upward uniform load is applied to the bottom of the wing to simulate the lift of the wing during flight. Statics simulation is performed using abaqus to obtain the deformation diagram of the wing under uniform load, as shown in the figure below. Figure 3 For convenience of display, Figure 3 It is 200 times the actual deformation. It can be seen that the deformation gradient of the wing along the axial direction (i.e., the x direction) is not uniform. The deformation gradient on the side close to the fixed end is smaller, and the deformation gradient on the side far from the fixed end is larger. Therefore, sensors can be arranged according to the size of the deformation gradient to ensure that the deformation between adjacent sensors is the same. Assuming that the maximum deformation of the free end of the wing is d, and the number of sensors to be arranged is n, the deformation between adjacent sensors is d / n. Figure 4 As shown, Figure 4 The following is a schematic diagram of the deformation curve of each point of the wing along the z direction under uniform load. The wing length is 1m, the maximum deformation of the free end of the wing is 2.129mm, and the number of sensors is 10. The deformation between adjacent sensors should be 0.2129mm. The arrangement on the wing surface is as follows: Figure 5 As shown, the number of sensors close to the fixed end is relatively small, while the number of sensors far from the fixed end is relatively large, thereby ensuring that the deformation amounts between adjacent sensors are the same.

[0041] From the above analysis, it can be known that when arranging the sensors on the wings, the present embodiment arranges the sensors according to the actual deformation of the wings during the flight of the aircraft, and requires that the deformation of the wings between two adjacent sensors are the same, that is, multiple sensors are arranged in a manner according to equal deformation of the wings, rather than arranging the sensors at equal intervals before the wings are deformed, or only arranging one or two sensors. Therefore, the single arrangement of sensors on the wing surface in the prior art is broken, so that the surface of the wing can be monitored more comprehensively and more targeted, for example, targeted measurements can be achieved on certain areas of the wing surface with larger deformation.

[0042] In some embodiments, Figure 1 As shown, the system also includes:

[0043] The voltage stabilizing module is electrically connected to the power supply module, and is used to convert the electric energy of the power supply module into a stable voltage and output the stable voltage; the energy storage module is electrically connected to the voltage stabilizing module and the sensor, and is used to store the stable voltage output by the voltage stabilizing module and power the sensor through the stable voltage. Among them, the voltage stabilizing module is an integrated block composed of analog circuits with a complex structure. Its voltage stabilizing ability is stronger than that of the voltage stabilizing tube, and its voltage stabilizing range is smaller and its accuracy is higher. It can be selected independently according to actual conditions.

[0044] In this embodiment, during the flight of the aircraft, the angle between the wing and the sunlight is not fixed. In addition, due to factors such as weather changes, the current transmitted by the flexible solar cell will be unstable. If the sensor is powered directly at this time, the sensor voltage will be unstable, affecting the collection accuracy. Therefore, in this embodiment, a voltage stabilizing module and an energy storage module are added between the solar panel and the sensor. The voltage stabilizing module converts the voltage of the solar panel within a certain range into a fixed voltage and outputs it stably to the energy storage module. The storage module then outputs the stable voltage to the sensor. In this way, the voltage supplying the sensor is stable, thereby improving the accuracy of the pressure and deformation on the wing surface collected by the sensor.

[0045] In some embodiments, the power supply module is a solar panel, which is used to convert solar energy into electrical energy and power the sensor.

[0046] In this embodiment, in the prior art, when monitoring the wing surface, such as collecting the pressure and deformation of the wing surface, the sensor is powered by a battery, and the battery capacity is limited. After the battery is exhausted, a new battery needs to be replaced. The process of replacing the battery is complicated and cumbersome, so the sensor cannot be powered continuously and autonomously. In order to solve this technical problem, the above technical solution in this embodiment is proposed. Specifically, solar energy is converted into electrical energy by a solar panel installed on the wing surface, and the converted electrical energy is used to power the sensor. Since the solar panel can continuously convert solar energy into electrical energy, there is no need to frequently replace the battery as in the prior art, thereby reducing the workload caused by replacing the battery, and at the same time, the purpose of continuously and autonomously powering the sensor is achieved through the solar panel.

[0047] In some embodiments, the solar panel includes a flexible solar panel, and the flexible solar panel is attached to the wing. Specifically, the flexible solar panel has the characteristics of being lightweight and bendable, which can minimize the load-bearing problem of the wing caused by external loads and improve the fuel economy of the aircraft. The flexible solar panel uses a flexible film as a substrate and uses a copper indium gallium selenide thin film battery. It has the remarkable characteristics of low pollution, no decay, and good weak light performance. The photoelectric conversion efficiency ranks first among various thin film solar cells, close to crystalline silicon solar cells, and the production cost is low, only one-third of crystalline silicon solar cells, which is the preferred material for flexible thin film solar cells. When in use, first encapsulate a water-blocking film on the surface of the flexible solar panel to resist the adverse effects of rain and snow weather and ensure its normal operation; then use glue to stick the flexible solar panel to the surface of the wing so that it is in full contact with the wing and increases the contact area with sunlight; finally, connect it to the positive and negative poles of the flexible solar panel through a wire to output electrical energy.

[0048] In some embodiments, Figure 6 As shown, the flexible solar panel includes a plurality of solar cells, and the plurality of solar cells are connected in series in sequence. By connecting the plurality of solar cells in series, the amount of converted electrical energy can be increased, thereby further ensuring power supply for the sensor.

[0049] In some embodiments, multiple solar cells are welded by copper foil. Specifically, the solar cells can be welded and cut arbitrarily to meet different power requirements. For example, the voltage of a single solar cell is U, the current is I, and the power is P. Then, after n solar cells are connected in series, the voltage is nU, the current is I, and the power is nP. After welding is completed, the bare drain electrode at the bottom, as well as the welded and unused electrode welding points at the top, need to be taped with insulating tape to avoid short circuits during use or installation.

[0050] In some embodiments, the number of energy storage modules is multiple, and the energy storage module includes multiple rechargeable polymer batteries. Specifically, lithium batteries of different capacities can be selected according to sensors with different power consumption. In addition, the arrangement or number of lithium batteries can be changed according to the arrangement of the sensors. The arrangement is flexible and can be applied in different working conditions. The advantages of rechargeable polymer lithium batteries are strong power, durability, and can be charged and discharged more than 600 times. Imported protection board IC is used, with internal short circuit protection and overcurrent devices, which meet international safety standards. Jiaotai Electric is used as the battery core of lithium battery polymer to prevent the generation of a large amount of gas due to boiling of liquid, eliminating the possibility of violent explosion. Since the environment of the aircraft is relatively harsh during flight, the temperature difference is large, and the air pressure fluctuation is also large, the use of rechargeable polymer lithium batteries as the energy storage module of the vibration collection system can fully avoid the impact of the above-mentioned harsh environment. When in use, the rechargeable polymer lithium battery is attached to the surface of the wing, and it can charge and discharge automatically, providing the system with lasting energy and avoiding the trouble of frequent battery replacement.

[0051] See also Figure 7 Based on the above-mentioned wing surface monitoring system, this embodiment further provides a sensor arrangement method for the wing surface monitoring system, the method comprising:

[0052] S10: applying a fixed constraint at one end of the wing, and applying an upward uniform load at the bottom of the wing to simulate the lift force on the wing during flight; that is, one end of the wing is fixed, which is the fixed end, and the other end is not fixed, which is the free end;

[0053] S20: Performing static simulation on the wing to obtain a deformation diagram of the wing under a uniformly distributed load, wherein the deformation diagram includes a deformation gradient of the wing;

[0054] S30: Arrange a plurality of sensors based on the magnitude of the deformation gradient, wherein the simulated deformation amounts of the wing between two adjacent sensors are the same, and the sensor is a sensor in the above-mentioned wing surface monitoring system.

[0055] In this embodiment, Figure 2 As shown in the figure, a fixed constraint is applied to the left end of the wing, the right end is a free end, and an upward uniform load is applied to the bottom of the wing to simulate the lift of the wing during flight. Statics simulation is performed using abaqus to obtain the deformation diagram of the wing under uniform load, as shown in the figure below. Figure 3 For convenience of display, Figure 3It is 200 times the actual deformation. It can be seen that the deformation gradient of the wing along the axial direction (i.e., the x direction) is not uniform. The deformation gradient on the side close to the fixed end is smaller, and the deformation gradient on the side far from the fixed end is larger. Therefore, sensors can be arranged according to the size of the deformation gradient to ensure that the deformation between adjacent sensors is the same. Assuming that the maximum deformation of the free end of the wing is d, and the number of sensors to be arranged is n, the deformation between adjacent sensors is d / n. Figure 4 As shown, Figure 4 The following is a schematic diagram of the deformation curve of each point of the wing along the z direction under uniform load. The wing length is 1m, the maximum deformation of the free end of the wing is 2.129mm, and the number of sensors is 10. The deformation between adjacent sensors should be 0.2129mm. The arrangement on the wing surface is as follows: Figure 5 As shown, the number of sensors close to the fixed end is relatively small, while the number of sensors far from the fixed end is relatively large, thereby ensuring that the deformation amounts between adjacent sensors are the same.

[0056] Through the above experimental analysis, it can be known that when arranging the sensors on the wings, the present embodiment arranges the sensors according to the actual deformation of the wings during the flight of the aircraft, and requires that the deformation of the wings between two adjacent sensors are the same, that is, multiple sensors are arranged in a manner according to the equal deformation of the wings, rather than arranging the sensors at equal intervals before the wings are deformed, or only arranging one or two sensors. Therefore, the single arrangement method of sensors on the wing surface in the prior art is broken, so that the surface of the wing can be monitored more comprehensively and specifically.

[0057] In some embodiments, Figure 8 As shown, the wing includes a fixed end, and the deformation gradient close to the fixed end is smaller than the deformation gradient away from the fixed end; the step of arranging a plurality of sensors based on the magnitude of the deformation gradient includes:

[0058] S301: Arranging a plurality of the sensors at a position close to the fixed end according to a first spacing;

[0059] S302: Arrange a plurality of the sensors at a position away from the fixed end according to a second spacing, wherein the first spacing is smaller than the second spacing.

[0060] In this embodiment, through the introduction of the above embodiments, it can be known that the number of sensors installed close to the fixed end position will be less than the number of sensors installed far from the fixed end position, ensuring that the deformation of the wing between two adjacent sensors is the same, and ensuring that the number of sensors installed on the wing is appropriate. This will prevent the deformation of the wing surface from being unable to be fully measured due to fewer sensors arranged on the wing surface, and will not affect the balance of the wing due to too many sensors installed, and will not increase the redundant workload caused by arranging sensors.

[0061] What is disclosed above is only a partial embodiment of the present application, which certainly cannot be used to limit the scope of rights of the present application. A person skilled in the art can understand that the entire or partial process of implementing the above embodiment and the equivalent changes made according to the claims of the present application are still within the scope of the invention.

Claims

1. A wing surface monitoring system, characterized in that: The system comprises: A plurality of sensors are mounted on the wing surface, and the actual deformation of the wing between two adjacent sensors is the same, and the sensors are used to monitor the change parameters of the wing surface, and the actual deformation is the deformation of the wing during the flight of the aircraft; A power supply module is installed on the surface of the wing, and the power supply module is electrically connected to the multiple sensors, and the power supply module is used to supply power to the sensors.

2. The wing surface monitoring system according to claim 1, characterized in that: The system further comprises: A voltage stabilizing module, electrically connected to the power supply module, for converting the electric energy of the power supply module into a stable voltage and outputting the stable voltage; The energy storage module is electrically connected to the voltage stabilizing module and the sensor, and is used to store the stable voltage output by the voltage stabilizing module and to power the sensor through the stable voltage.

3. The wing surface monitoring system according to claim 2, characterized in that: There are multiple energy storage modules, and each energy storage module includes multiple polymer physical batteries.

4. The wing surface monitoring system according to claim 1, characterized in that: The power supply module includes a solar panel, which is used to convert solar energy into electrical energy and supply power to the sensor.

5. The wing surface monitoring system according to claim 4, characterized in that: The solar cell panel is a flexible solar cell panel, and the flexible solar cell panel is adhered to the wing.

6. The wing surface monitoring system according to claim 5, characterized in that: The flexible solar cell panel comprises a plurality of solar cells, and the plurality of solar cells are sequentially connected in series.

7. The wing surface monitoring system according to claim 1, characterized in that: The variable parameters include pressure and deformation on the wing surface.

8. The wing surface monitoring system according to claim 1, characterized in that: The wing includes a fixed end, and a deformation gradient close to the fixed end is smaller than a deformation gradient far from the fixed end.

9. A sensor arrangement method for a wing surface monitoring system, characterized in that: The method comprises: Applying a fixed constraint at one end of the wing and applying an upward uniform load at the bottom of the wing to simulate the lift force on the wing during flight; Performing static simulation on the wing to obtain a deformation diagram of the wing under a uniformly distributed load, wherein the deformation diagram includes a deformation gradient of the wing; A plurality of sensors are arranged based on the size of the deformation gradient; wherein the simulated deformation amounts of the wings between two adjacent sensors are the same.

10. The sensor arrangement method of the wing surface monitoring system according to claim 9, characterized in that: The wing includes a fixed end, and the deformation gradient close to the fixed end is smaller than the deformation gradient away from the fixed end; The step of arranging a plurality of sensors based on the magnitude of the deformation gradient comprises: Arrange a plurality of the sensors at a first spacing at a position close to the fixed end; A plurality of the sensors are arranged at a position away from the fixed end at a second interval, wherein the first interval is smaller than the second interval.

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