CN116625220A - Flexible sensor for monitoring state of aircraft panel and preparation method thereof - Google Patents

Flexible sensor for monitoring state of aircraft panel and preparation method thereof Download PDF

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Publication number
CN116625220A
CN116625220A CN202310613946.4A CN202310613946A CN116625220A CN 116625220 A CN116625220 A CN 116625220A CN 202310613946 A CN202310613946 A CN 202310613946A CN 116625220 A CN116625220 A CN 116625220A
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aluminum alloy
sensitive layer
laser
film
graphene
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CN202310613946.4A
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Inventor
孟庆实
池腾飞
王向明
刘建邦
韩森森
赵健凯
陆豪杰
王朔
王英波
姬书得
张业伟
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Shenyang Aerospace University
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Shenyang Aerospace University
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Priority to CN202310613946.4A priority Critical patent/CN116625220A/en
Publication of CN116625220A publication Critical patent/CN116625220A/en
Pending legal-status Critical Current

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B7/00—Measuring arrangements characterised by the use of electric or magnetic techniques
    • G01B7/16—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring the deformation in a solid, e.g. by resistance strain gauge
    • G01B7/18—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring the deformation in a solid, e.g. by resistance strain gauge using change in resistance
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M7/00—Vibration-testing of structures; Shock-testing of structures
    • G01M7/08—Shock-testing
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/02—Details
    • G01N3/06—Special adaptations of indicating or recording means
    • G01N3/066—Special adaptations of indicating or recording means with electrical indicating or recording means
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/30—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/0001—Type of application of the stress
    • G01N2203/001—Impulsive
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/0058—Kind of property studied
    • G01N2203/006—Crack, flaws, fracture or rupture
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/02—Details not specific for a particular testing method
    • G01N2203/06—Indicating or recording means; Sensing means
    • G01N2203/0617—Electrical or magnetic indicating, recording or sensing means

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

A method of manufacturing a flexible sensor for monitoring the condition of an aircraft panel, comprising the steps of: step 1: cutting the PI film and attaching the PI film on an aluminum alloy substrate; step 2: the PI film is induced by laser to obtain a graphene sensitive layer; step 3: packaging one side with the graphene sensitive layer by using a PI single-sided tape, and connecting wires at two ends; step 4: attaching the flexible sensor to the aluminum alloy structural member, and respectively performing impact damage, continuous loading stability and bending deformation real-time monitoring on the aluminum alloy structural member; and (3) performing rectangular array control on the carbon fiber aircraft wallboard by using a plurality of flexible sensors, and performing multichannel impact damage real-time monitoring on the carbon fiber wallboard. The flexible sensor comprises a graphene sensitive layer, electrodes are arranged at two ends of the graphene sensitive layer and are respectively connected with corresponding wires, and one side of the exposed graphene sensitive layer is packaged by a PI single-sided tape. The graphene sensitive layer is prepared by adopting the laser-induced PI film, and the preparation method is simple to operate and low in cost.

Description

Flexible sensor for monitoring state of aircraft panel and preparation method thereof
Technical Field
The invention belongs to the technical field of aircraft structure health monitoring, relates to a laser-induced graphene technology, and particularly relates to a flexible sensor for monitoring the state of an aircraft wallboard and a preparation method thereof.
Background
A flexible strain sensor is a flexible electronic component that can measure strain or deformation of an object surface. Such sensors are typically made of flexible materials, such as polymers or elastomers. When the object is deformed, the flexible sensor generates electrical signals which can be converted into digital signals and transmitted to a computer or other device for processing and analysis. The flexible strain sensor has the advantages of higher sensitivity and precision, and can measure very small strain or deformation. Furthermore, due to the nature of their flexible materials, they can adapt to object surfaces of different shapes and curvatures, and can take a wide range of strain measurements. Therefore, they are widely used in the fields of robotics, medical devices, intelligent transportation systems, smart homes, electronic games, etc. The methods of manufacturing flexible strain sensors are also very diverse, including printing, ink-jet, and textile techniques. These manufacturing methods allow for relatively low cost flexible strain sensors, while also allowing for their wide application in mass production.
The Laser Induced Graphene (LIG) technology is a novel method for preparing graphene, which generates charges on a surface by irradiating a carbon source material with laser light, thereby forming a graphene film on the surface. Compared with the traditional Chemical Vapor Deposition (CVD) method, the LIG method has the advantages of low cost, short preparation period, simple operation and the like, and therefore, has received extensive attention. Advantages of LIG technology include: the preparation process is simple, quick and low in cost; can be prepared on a variety of base materials including polymers, paper, fabrics, and the like; the graphene film is tightly combined with a base material, has good mechanical strength and flexibility, and can be used for preparing flexible electronic elements and the like.
At present, the flexible strain sensor is mainly applied to human body medical care, vital sign monitoring and the like of a human body, but is applied to health monitoring of aircraft wall plate structural members and has few reports. Aircraft structural health monitoring may help identify potential structural defects or faults, thereby preventing accidents. For example, if damage to the aircraft panel is detected, repairs may be performed in time to prevent the aircraft from failing while in flight. By monitoring the health condition of the aircraft structure, the health condition of the aircraft structure can be measured early, and timely maintenance and repair can be performed, so that the service life of the aircraft can be prolonged. The aircraft structure is healthy to find problems and maintain, so that more serious damage is avoided, the reliability of the aircraft is improved, and the maintenance cost is reduced. Monitoring by periodic supervision is one of the important means to ensure navigability. The flexible sensor can be integrated with an aircraft structural member, standardized preparation of the flexible sensor can be realized through laser-induced graphene, and the flexible sensor can be applied to the field of aircraft structural health monitoring.
The traditional graphene preparation method is complex in process and high in cost. The traditional strain gage and the fiber bragg grating have small coverage area. For an arc-shaped surface, a special-shaped surface and a vertical surface, the traditional strain gauge and the fiber bragg grating cannot be arranged. Therefore, the flexible sensor is very urgent to be applied to large structural parts such as aircraft panels and the like and standardized preparation is realized.
Disclosure of Invention
Aiming at the defects existing in the prior art, the invention provides a flexible sensor for monitoring the state of an aircraft panel and a preparation method thereof, and CO is adopted 2 The graphene sensitive layer is prepared by the PI film induced by laser of a laser machine, so that the operation is simple and the cost is low; the flexible strain sensor is adopted, so that the coverage area is large, and the monitoring range is wider; for an arc surface, a special-shaped surface and a vertical surface, the problem of optical fiber arrangement can be solved by adopting the flexible strain sensor.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
a method of manufacturing a flexible sensor for monitoring the condition of an aircraft panel, comprising the steps of:
step 1: cutting film
Cutting a PI film with a required size, attaching the PI film on an aluminum alloy substrate, and wiping impurities and dust on the aluminum alloy substrate by absolute ethyl alcohol in advance;
step 2: laser-induced graphene
Placing the aluminum alloy substrate with the PI film on a laser machine bee-hole workbench; adjusting laser processing parameters and the position of an aluminum alloy substrate, wherein the position of the aluminum alloy substrate, namely one side of the aluminum alloy substrate, is parallel to a laser head processing route; the PI film is induced by laser to obtain a graphene sensitive layer;
step 3: packaging
Taking the induced PI film with the graphene sensitive layer off the aluminum alloy substrate, packaging one side with the graphene sensitive layer by using a PI single-sided adhesive tape, connecting wires at two ends, and fixing the wires by using conductive silver paste;
step 4: testing
(1) Aluminum alloy aircraft panel: simulating an aluminum alloy wallboard of the aircraft by using an aluminum alloy structural member, attaching a flexible sensor to the aluminum alloy structural member, and respectively performing impact damage, continuous loading stability and bending deformation real-time monitoring on the aluminum alloy structural member;
(2) Carbon fiber aircraft panel: and (3) performing rectangular array control on the carbon fiber aircraft wallboard by using a plurality of flexible sensors, and performing multichannel impact damage real-time monitoring on the carbon fiber wallboard.
The laser machine in the step 2 is CO 2 A laser.
The laser processing parameters in the step 2 are laser power and scanning speed, wherein the laser power is 15-20W, and the scanning speed is 250-300 mm/s.
The flexible sensor for monitoring the state of the aircraft wallboard is prepared by the laser-induced preparation method, the flexible strain sensor comprises a graphene sensitive layer, electrodes protruding outwards are arranged at two ends of the graphene sensitive layer, PI single-sided tape packaging is arranged on one side of the exposed graphene sensitive layer, the electrodes at two ends of the graphene sensitive layer are respectively connected with corresponding wires, and the wires are fixed by conductive silver paste.
The invention has the technical effects that:
1. the flexible sensor prepared by inducing the graphene sensitive layer by using the laser processing PI film has the advantages of low cost, simple preparation process and higher sensitivity and stability. The flexible sensor can be perfectly attached to the aircraft panel structural member, and real-time online monitoring of the aircraft panel structural member can be realized. And (3) according to comprehensive analysis of the acquired data, judging the impact load and structural deformation of the aircraft panel structural member.
2. According to the real-time monitoring requirement of the aircraft wallboard structural member, a corresponding structural health monitoring scheme is designed:
(1) And a plurality of flexible sensors are manufactured by using the same laser processing parameters and the same PI film size, a plurality of groups of impact tests are carried out, impact loads applied by each impact test are the same, the impact tests lead to the resistance change of the flexible sensors, and the impact damage monitoring and the standardized preparation of the flexible sensors for the aircraft panel structural members are realized by calculating the resistance change rate of each flexible sensor to be approximately the same.
(2) And a plurality of flexible sensors are manufactured by using the same laser processing parameters and the same PI film size, a plurality of groups of continuous loading tests are carried out, the continuous loading applied by each continuous loading test is the same, the continuous loading test causes the resistance change of the flexible sensors, and the resistance change rate of each flexible sensor is calculated to be approximately the same, so that the continuous loading stability monitoring and the standardized preparation of the flexible sensors of the aircraft wallboard structural member are realized.
(3) And a plurality of flexible sensors are manufactured by using the same laser processing parameters and the same PI film size, a plurality of groups of bending tests are carried out, the bending test load and the bending angle are the same each time, the bending test causes the resistance change of the flexible sensors, and the bending deformation damage monitoring and the standardized preparation of the flexible sensors of the aircraft panel structural member are realized by calculating the resistance change rate of each flexible sensor to be approximately the same.
(4) The flexible sensors are attached to the carbon fiber wallboard in a rectangular array control mode, impact tests are sequentially carried out on the flexible sensors, and multichannel impact damage real-time monitoring on the carbon fiber wallboard is achieved.
Drawings
FIG. 1 is a pattern of a graphene sensitive layer of example 1 of the present invention applied to an aluminum alloy sample;
FIG. 2 is a schematic illustration of a flexible sensor of example 1 of the present invention applied to an aluminum alloy sample piece;
FIG. 3 is a graph showing the impact damage real-time monitoring results of an aluminum alloy sample according to example 1 of the present invention;
FIG. 4 is a graph showing the results of continuous loading real-time monitoring of an aluminum alloy sample according to example 1 of the present invention;
FIG. 5 is a graph showing the results of real-time monitoring of bending deformation of an aluminum alloy sample according to example 1 of the present invention;
FIG. 6 is a pattern of a graphene sensitive layer of example 2 of the present invention applied to a carbon fiber wallboard;
FIG. 7 is a flexible sensor of embodiment 2 of the present invention applied to a carbon fiber wallboard;
FIG. 8 is a real-time monitoring and controlling method for impact damage of a carbon fiber wallboard according to embodiment 2 of the present invention;
fig. 9 is a real-time impact damage monitoring result of the carbon fiber wall panel of example 2 of the present invention.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples.
Example 1
In example 1, an aircraft aluminum alloy panel was simulated using a rectangular aluminum alloy structural member having dimensions of 40mm by 120mm.
A preparation method of a stable and efficient flexible strain sensor for aviation comprises the following steps:
step 1: cutting film
The size of the rectangular aluminum alloy structural member is 40mm multiplied by 120mm, the size of the cut PI film is 30mm multiplied by 80mm, and in order to overcome deformation influence caused by thermal effect, the PI film is stuck on an aluminum alloy substrate with stronger heat conduction performance, so that the temperature of the film cannot be too high in the scanning process, and the surface of the aluminum alloy substrate is cleaned by absolute ethyl alcohol in advance;
step 2: laser-induced graphene
The aluminum alloy structural part is rectangular, so that the graphene sensitive layer is also rectangular, the size of the graphene sensitive layer is smaller than that of the PI film because of packaging treatment, namely the size of the graphene sensitive layer is 20mm multiplied by 50mm, two small rectangles are extended to serve as electrode connecting wires because of connecting wires at two ends, and finally, the whole is drawn by CAD drawing software, as shown in figure 1; introducing the drawn graphene sensitive layer pattern into RDworks software, and combining the RDworks software with CO 2 Laser machine connection, CO 2 The laser machine processes according to the pattern of the graphene sensitive layer in RDworks software; placing the aluminum alloy substrate with the PI film on CO 2 The laser machine bee-hole workbench is arranged, and one side of the aluminum alloy substrate is adjusted to be parallel to the laser head processing route; CO modulation 2 The laser processing parameters of the laser machine are that the laser power is 17W and the scanning speed is 300mm/s; start-up CO 2 The laser machine is used for inducing the PI film by laser to obtain a graphene sensitive layer;
step 3: packaging
Taking the induced PI film with the graphene sensitive layer off the aluminum alloy substrate, and then taking a piece of PI single-sided adhesive tape with the same size to encapsulate one side with the graphene sensitive layer, wherein two ends of the graphene sensitive layer are connected with wires which are fixed by conductive silver paste; packaging the flexible sensor based on the laser-induced graphene is completed, as shown in fig. 2; repeating the steps to manufacture 20 identical flexible sensors;
step 4: testing
Attaching the flexible sensor to a rectangular aluminum alloy structural member, and connecting wires at two ends with a DEWETRON data acquisition system for testing;
test 1: impact damage real-time monitoring
Continuous impact load of 5KPa is carried out on the flexible sensor, a DEWETRON data acquisition system is used for acquiring resistance value data, 100 data points are acquired every second, 20 groups of data are processed to find that each time of impact load of 5KPa is carried out, the change rate of each group of resistance is kept at-0.4+/-0.05, the data are shown in figure 3, and therefore, when the laser power is 17W and the scanning speed is 300mm/s, a stable graphene sensitive layer can be obtained;
test 2: continuous load stability real-time monitoring
Continuously loading the flexible sensor with 5KPa, acquiring resistance value data by using a DEWETRON data acquisition system, acquiring 100 data points per second, and finding that the continuous loading with 5KPa is realized after 20 groups of data processing, wherein the change rate of each group of resistance is kept at-0.4+/-0.05, and the data is shown in figure 4, so that a stable graphene sensitive layer can be obtained when the laser power is 17W and the scanning speed is 300mm/s;
test 3: real-time monitoring of bending deformation
The flexible sensor is subjected to 0-45-degree bending deformation, a DEWETRON data acquisition system is used for acquiring resistance value data, 100 data points are acquired every second, after 20 groups of data are processed, the bending deformation of 0-45 degrees is found, when a test piece reaches 45-degree bending, the change rate of each group of resistance is kept at-1.2+/-0.05, the data are shown in figure 5, and in addition, the graph shows that the larger the bending angle is, the smaller the absolute value of the slope of the change rate of the resistance is, the larger the bending angle is, the smaller the gaps of the graphene sensitive layer are, and the transmission paths are smaller.
The flexible sensor for monitoring the state of the aircraft wallboard is prepared by the laser-induced preparation method, the flexible strain sensor comprises a graphene sensitive layer, electrodes protruding outwards are arranged at two ends of the graphene sensitive layer, PI single-sided tape packaging is arranged on one side of the exposed graphene sensitive layer, the electrodes at two ends of the graphene sensitive layer are respectively connected with corresponding wires, and the wires are fixed by conductive silver paste.
Example 2
Real carbon fiber aircraft wall panels are adopted for impact damage real-time monitoring.
A preparation method of a stable and efficient flexible strain sensor for aviation comprises the following steps:
step 1: cutting film
The carbon fiber aircraft panel has dimensions of 500mm by 700mm, and the cut PI film has dimensions of 90mm by 90mm. In order to overcome deformation influence caused by thermal effect, a PI film is stuck to an aluminum alloy substrate with strong heat conduction performance, so that the temperature of the film is kept not to be too high in the scanning process, and the surface of the aluminum alloy substrate is cleaned by absolute ethyl alcohol in advance;
step 2:
because the carbon fiber aircraft wallboard is rectangular, the graphene sensitive layer is also designed into a rectangle, the size is 70mm multiplied by 70mm, two small rectangles are extended to serve as electrode connecting wires because the wires are connected at the two ends, finally, CAD is used for drawing the whole body, as shown in figure 6, the drawn graphene sensitive layer pattern is led into RDworks software, the software is connected with a CO2 laser, and the CO 2 The laser machine processes according to the pattern of the graphene sensitive layer in RDworks software; placing the aluminum alloy substrate with the PI film on CO 2 The method comprises the steps of adjusting one side of an aluminum alloy substrate to be parallel to a laser head processing route on a bee-hole workbench of a laser machine; CO modulation 2 The laser processing parameters of the laser machine are that the laser power is 17W and the scanning speed is 300mm/s; start-up CO 2 The laser machine is used for inducing the PI film by laser to obtain a graphene sensitive layer;
step 3:
taking the induced PI film with the graphene sensitive layer off the aluminum alloy substrate, and then taking a PI single-sided film with the same size to encapsulate one side with the graphene sensitive layer, wherein two ends of the graphene sensitive layer are connected with wires which are fixed by conductive silver paste; the flexible sensor based on the laser-induced graphene is packaged, and as shown in fig. 7, 4 identical flexible sensors are manufactured by repeating the steps;
step 4:
the method comprises the steps that 4 flexible sensors are respectively named as sensors 1, 2, 3 and 4, an array type cloth control is adopted to be attached to a carbon fiber aircraft wallboard, and wires at two ends are connected with a DEWETRON data acquisition system for testing;
test 1: impact damage real-time monitoring
The 4 flexible sensors were sequentially impacted, and as shown in fig. 8, a DEWETRON data acquisition system was used to acquire resistance value data, 100 data points per second. After 4 sets of data processing, taking the data of the knocking flexible sensor 1 as an example, as shown in fig. 9, when the knocking flexible sensor 1 is impacted, a channel one can be seen to have obvious stable signal response, a channel 2 and a channel 3 can be seen to have weaker signal response, and the channel 4 has almost no signal response. The results show that the specific impact position can be accurately judged by adopting array control on the flexible sensor.
The preparation process is simple, the preparation of the graphene sensitive layer is realized by using a CO2 laser machine, and the preparation is finally finished through simple encapsulation. The device can be perfectly attached to large structural members such as an aircraft wallboard, and real-time online monitoring of the aircraft wallboard can be realized. Under the same laser processing parameters and the same impact load conditions, the resistance change rate is kept to be changed in a fixed interval, so that the repeatability and the stability of the flexible sensor can be realized, and the standardization problem of the flexible sensor for aviation is further optimized.

Claims (4)

1. A method of manufacturing a flexible sensor for monitoring the condition of an aircraft panel, comprising the steps of:
step 1: cutting film
Cutting a PI film with a required size, attaching the PI film on an aluminum alloy substrate, and wiping impurities and dust on the aluminum alloy substrate by absolute ethyl alcohol in advance;
step 2: laser-induced graphene
Placing the aluminum alloy substrate with the PI film on a laser machine bee-hole workbench; adjusting laser processing parameters and the position of an aluminum alloy substrate, wherein the position of the aluminum alloy substrate, namely one side of the aluminum alloy substrate, is parallel to a laser head processing route; the PI film is induced by laser to obtain a graphene sensitive layer;
step 3: packaging
Taking the induced PI film with the graphene sensitive layer off the aluminum alloy substrate, packaging one side with the graphene sensitive layer by using a PI single-sided adhesive tape, connecting wires at two ends, and fixing the wires by using conductive silver paste;
step 4: testing
(1) Aluminum alloy aircraft panel: simulating an aluminum alloy wallboard of the aircraft by using an aluminum alloy structural member, attaching a flexible sensor to the aluminum alloy structural member, and respectively performing impact damage, continuous loading stability and bending deformation real-time monitoring on the aluminum alloy structural member;
(2) Carbon fiber aircraft panel: and (3) performing rectangular array control on the carbon fiber aircraft wallboard by using a plurality of flexible sensors, and performing multichannel impact damage real-time monitoring on the carbon fiber wallboard.
2. The method of manufacturing a flexible sensor for monitoring the condition of an aircraft panel according to claim 1, wherein: the laser machine in the step 2 is CO 2 A laser.
3. The method of manufacturing a flexible sensor for monitoring the condition of an aircraft panel according to claim 1, wherein: the laser processing parameters in the step 2 are laser power and scanning speed, wherein the laser power is 15-20W, and the scanning speed is 250-300 mm/s.
4. A flexible sensor for monitoring the condition of aircraft panels, produced by the method of any one of claims 1, 2 and 3, characterized in that: the flexible strain sensor comprises a graphene sensitive layer, electrodes protruding outwards are arranged at two ends of the graphene sensitive layer, PI single-sided tape packaging is arranged on one side of the exposed graphene sensitive layer, the electrodes at two ends of the graphene sensitive layer are respectively connected with corresponding wires, and the wires are fixed by conductive silver paste.
CN202310613946.4A 2023-05-29 2023-05-29 Flexible sensor for monitoring state of aircraft panel and preparation method thereof Pending CN116625220A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310613946.4A CN116625220A (en) 2023-05-29 2023-05-29 Flexible sensor for monitoring state of aircraft panel and preparation method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310613946.4A CN116625220A (en) 2023-05-29 2023-05-29 Flexible sensor for monitoring state of aircraft panel and preparation method thereof

Publications (1)

Publication Number Publication Date
CN116625220A true CN116625220A (en) 2023-08-22

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Application Number Title Priority Date Filing Date
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