CN113375544A - Micro-nano sensor for monitoring health state of connection structure of lug of airplane and manufacturing method thereof - Google Patents
Micro-nano sensor for monitoring health state of connection structure of lug of airplane and manufacturing method thereof Download PDFInfo
- Publication number
- CN113375544A CN113375544A CN202110683580.9A CN202110683580A CN113375544A CN 113375544 A CN113375544 A CN 113375544A CN 202110683580 A CN202110683580 A CN 202110683580A CN 113375544 A CN113375544 A CN 113375544A
- Authority
- CN
- China
- Prior art keywords
- monitoring
- connection structure
- sensor
- lug
- strain sensor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N27/00—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means
- G01N27/02—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating impedance
- G01N27/04—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating impedance by investigating resistance
- G01N27/20—Investigating the presence of flaws
Abstract
A micro-nano sensor for monitoring the health state of an airplane lug connection structure and a manufacturing method thereof belong to the field of airplane structure health monitoring. The micro-nano sensor for monitoring the health state of the lug connecting structure of the airplane comprises a strain sensor and a data acquisition device; the strain sensor comprises a conductive composite material film, conductive slurry and a lead, wherein the conductive composite material film is connected with the lead through the conductive slurry, and the lead of the strain sensor is connected with the data acquisition device; the strain sensor is arranged on the airplane lug connecting structure and used for acquiring resistance change information of the strain sensor when the airplane lug connecting structure is subjected to external force load and environmental change; and the data acquisition device is used for collecting and analyzing resistance change information of the strain sensor to judge the stress state and the environmental temperature of the connection structure of the tabs of the airplane. The sensor can realize real-time monitoring, can judge the damage information of the airplane lug connecting structure in time, and improves the safety of the airplane lug connecting structure.
Description
Technical Field
The invention belongs to the field of aircraft structure health monitoring, and relates to a micro-nano sensor for monitoring the health state of an aircraft lug connecting structure and a manufacturing method thereof.
Background
The aircraft lug connecting structure is a connecting structure commonly used on an aircraft, is usually matched with a pin bearing for use, can transmit higher concentrated load, is widely used in landing gear large joints, engine hangers, control surface hinges, rotating shaft joints for connecting a horizontal tail back beam and a rear fuselage, cabin door hinges and connecting parts needing to be disassembled, and is usually used as an important part or a key part on the aircraft. In the service process of the airplane, the connection structure of the lug of the airplane is very likely to be damaged due to factors such as fatigue load, abrasion, environmental corrosion and the like. As damage progresses, the load bearing capacity of the connection structure may continue to decline, which may result in failure and even eventual catastrophic failure of the connection joint, resulting in catastrophic accidents and significant economic losses. Therefore, the most important way to ensure the safe and reliable operation of the aircraft tab connection structure is to perform state health monitoring on the aircraft tab connection structure.
Currently, more mature structural damage monitoring sensor types include: the sensor comprises an optical fiber sensor, a piezoelectric material sensor, a relative vacuum sensor, an eddy current sensor, an acoustic emission sensor and the like, and when the sensor is used for monitoring cracks of an airplane metal structure, the following problems need to be solved: the integrated integration with the airplane metal structure is difficult to realize, the severe working environment of the airplane metal structure is difficult to bear, the fatigue damage state of the structure is difficult to effectively evaluate under the existing detection range and precision, and the large-range application is difficult to realize under the existing cost and equipment requirement level. Therefore, it is necessary to develop a crack monitoring technique for a simple and highly reliable connection structure.
Disclosure of Invention
The invention provides a micro-nano sensor for monitoring the health state of an airplane lug connecting structure and a manufacturing method thereof, and the micro-nano sensor for monitoring the health state of the airplane lug connecting structure is characterized in that a modified conductive carbon nano filler is blended with a polymer, a conductive composite material film is arranged at a key position of the airplane lug connecting structure by using a spin coating method or a pasting method, the conductive composite material film is connected with a lead by using conductive slurry to form a strain sensor, the strain sensor is further packaged by using a packaging film and is connected with a data acquisition device, and the acquired data is fused, processed and analyzed, so that real-time monitoring is realized, the damage information of the airplane lug connecting structure can be judged in time, and the safety of the airplane lug connecting structure is improved.
The invention discloses a micro-nano sensor for monitoring the health state of an aircraft lug connection structure, which comprises a strain sensor and a data acquisition device; the strain sensor comprises a conductive composite material film, conductive slurry and a lead, wherein the conductive composite material film is connected with the lead through the conductive slurry, and the lead of the strain sensor is connected with a data acquisition device;
the strain sensor is arranged on the aircraft lug connecting structure and used for acquiring resistance change information of the strain sensor when the aircraft lug connecting structure is subjected to external force load and environmental change;
and the data acquisition device is used for collecting and analyzing resistance change information of the strain sensor to judge the stress state and the environmental temperature of the connection structure of the tabs of the airplane.
The preparation method of the micro-nano sensor for monitoring the health state of the lug connection structure of the airplane comprises the following steps:
step 1: preparation of modified conductive carbon nanofiller
Mixing and grinding or ball-milling the prepared conductive carbon nano-filler and the modified surfactant to obtain a modified conductive carbon nano-filler;
or adding a modified surfactant to mix and grind or ball mill in the process of preparing the conductive carbon nano filler to obtain the modified conductive carbon nano filler;
wherein, the grinding or ball milling time is 3-10 h, and the conductive carbon nano filler comprises the following components in percentage by mass: modified surfactant 1: (2-7);
step 2: preparation of conductive composite film
Uniformly dispersing the modified conductive carbon nano filler and the polymer in a ball milling process to obtain a conductive composite material mixture; wherein, according to the mass ratio, the modified conductive carbon nano filler: a polymer (2-10): (90-98);
and step 3: preparation of strain sensor
The method is divided into different preparation processes according to different modes of arranging the connection structure on the lug plate of the airplane;
the mode of arranging on the connection structure of the aircraft lug is divided into a spin coating method or a pasting method:
spin coating method: after the conductive composite material mixture volatilizes the solvent, adding the curing agent, then coating the mixture on the connection structure of the airplane ear, fixing the conducting wire on the coating part by adopting conductive slurry, and then curing to obtain the strain sensor;
the application method comprises the following steps: adding a curing agent into the conductive composite material mixture, then volatilizing the solvent, curing to obtain a conductive composite material film, and connecting the conductive composite material film with a lead through conductive slurry to obtain a strain sensor; applying the strain sensor to the monitoring position of the connection structure of the lug of the airplane by adopting an interface agent;
and 4, step 4: and (3) packaging the strain sensor by using a packaging film, and connecting the strain sensor with a data acquisition device for monitoring.
In the step 1, the conductive carbon nanofiller is graphene nanosheets and/or carbon nanotubes; the modified surfactant is siloxane coupling agent or amino-terminated epoxy curing agent.
The graphene nanosheet is prepared by adopting a method of high-temperature expansion and low-temperature ultrasonic stripping or ball milling stripping.
In the step 1, a steel tank is selected in the ball milling process, one of zirconia balls, tungsten carbide balls and stainless steel balls is selected as the ball milling speed, the ball milling speed is 200-600 rpm, the ball milling program is selected for ball milling for 15-20 min, and the ball milling is suspended for 8-10 min.
In the step 2, a steel tank is selected in the ball milling process, one of zirconia balls, tungsten carbide balls and stainless steel balls is selected as the ball milling speed, the ball milling speed is 200-600 rpm, the ball milling program is ball milling for 15-20 min, and the ball milling is suspended for 8-10 min.
In the step 2, the polymer is one of epoxy resin and silicon rubber.
In the step 2, the modified conductive carbon nano-filler is stripped in a solvent by ultrasonic or ball milling, and a polymer is added into the mixed solution after ultrasonic or ball milling.
The solvent is one or more of toluene, glycol and ketone organic solvents.
The method for monitoring the micro-nano sensor for monitoring the health state of the lug connection structure of the airplane comprises the following steps:
stress state, fatigue life and ambient temperature in the aircraft lug connecting structure are monitored through the strain sensor, and then the stress state, the fatigue life and the ambient temperature of the aircraft lug connecting structure are judged by transmitting the stress state, the fatigue life and the ambient temperature to the data processing device and analyzing resistance change information monitored by the strain sensor.
The invention discloses a micro-nano sensor for monitoring the health state of an aircraft lug connection structure and a manufacturing method thereof, and has the beneficial effects that:
1. the micro-nano sensor prepared by blending the conductive carbon nano filler and the polymer has the advantages of low cost, simple preparation process and higher sensitivity and reliability. The micro-nano sensor prepared by using the polymer matrix can be perfectly attached to the material of the connection structure of the lug of the airplane, and the real-time online monitoring of the connection structure of the lug of the airplane can be realized. And comprehensively analyzing the acquired data so as to study and judge the safety state of the connecting structure.
2. Aiming at the real-time monitoring requirement of the safety state of the airplane lug connecting structure, a micro-nano film sensor perfectly integrated with a structural substrate is provided based on a resistance monitoring principle, and a corresponding structural health monitoring scheme (1) is designed to judge the strain state change of the airplane lug connecting structure through the resistance change information of the sensor so as to conjecture the normal working range of the airplane lug connecting structure; (2) judging the reliability of the connection structure of the lug of the airplane through the resistance change of the sensor, and further estimating the fatigue life of the connection structure of the lug of the airplane; (3) judging the environmental temperature of the connection structure of the lug of the airplane based on the temperature-sensitive effect of the sensor so as to ensure the normal work of the connection structure of the lug of the airplane; and carrying out a damage monitoring test on the aluminum alloy center hole test piece under a constant-amplitude load spectrum. The real-time health monitoring capability of the micro-nano sensor is verified by comparing the on-line monitoring result of the micro-nano film sensor array with the damage condition observed by using a microscope.
Drawings
FIG. 1: a schematic flow diagram of the preparation of the modified graphene nanosheet;
FIG. 2: the preparation process of the conductive composite film and the packaging and control flow schematic diagram of the sensor are shown;
FIG. 3: simulating and calculating a stress load spectrum of the connection structure of the lug of the airplane;
FIG. 4: monitoring a response curve of the tensile state of the connection structure of the lug of the airplane;
FIG. 5: a fatigue state monitoring response curve of the aircraft lug connection structure;
FIG. 6: temperature monitoring response curve of the aircraft tab connection structure.
Detailed Description
The present invention will be described in further detail with reference to examples.
In the following examples, the aircraft tab connection structure used was simulated with an aluminum alloy center hole specimen.
In the following embodiments, the data acquisition device adopts one of a FLUKE data acquisition device and a Devyware data acquisition system.
In the following examples, the modified surfactant is one or both of a siloxane coupling agent and an amino-terminated epoxy curing agent.
In the following examples, the organic solvent is one or more of toluene, ethylene glycol, and ketone organic solvents.
In the following examples, the modulus of the interfacial agent used to secure the sensor to the aircraft tab connection structure differed from the modulus of the aircraft tab connection structure material by ± 0.5 MPa.
Example 1
A method for preparing a micro-nano sensor for monitoring the health state of an aircraft lug connection structure comprises the following steps:
step 1:
subjecting natural intercalated graphite flakes to high-temperature expansion (700 ℃) to obtain high-temperature expanded graphite, adding a modified surfactant-siloxane coupling agent into a grinding body for grinding, washing with an organic solvent, and further carrying out ultrasonic stripping at low temperature (10 ℃) to obtain modified graphene nanosheets, wherein the schematic preparation flow diagram is shown in FIG. 1; wherein, according to the mass ratio, the high-temperature expanded graphite: modified surfactant 1: 2;
step 2:
taking a proper amount of the component A (epoxy resin) and the modified graphene nanosheets subjected to ultrasonic stripping, ball-milling and mixing in an organic solvent-acetone, selecting a steel tank in the ball-milling process, selecting stainless steel balls as the balls, ball-milling at the speed of 300rpm, selecting ball-milling procedures of ball-milling for 15min and suspending for 8min, and heating after ball-milling to completely volatilize the organic solvent; wherein, graphene nanoplatelets: 2:98 of epoxy resin; adding the component B (epoxy resin curing agent) in proportion, uniformly stirring, coating the mixture on a distribution control position of an aircraft lug connection structure, connecting a lead through conductive slurry, putting the mixture into an oven for curing to obtain a strain sensor, wherein the packaging and distribution control flow schematic diagram is shown in FIG. 2;
and step 3: and (3) packaging the strain sensor by using a packaging film, and connecting the strain sensor with a data acquisition device for monitoring.
Example 2
A method for preparing a micro-nano sensor for monitoring the health state of an aircraft lug connection structure comprises the following steps:
step 1:
subjecting natural intercalated graphite flakes to high-temperature expansion (800 ℃) to obtain high-temperature expanded graphite, adding a modified surfactant, namely an amino-terminated epoxy curing agent into a grinding body for grinding, washing with an organic solvent, and further carrying out ultrasonic stripping at low temperature (10 ℃) to obtain modified graphene nanosheets, wherein the schematic preparation flow diagram is shown in FIG. 1; wherein, according to the mass ratio, the thermal expansion graphite: 1:6 of modified surfactant;
step 2:
taking a proper amount of the component A (epoxy resin) and a certain proportion of the component B (epoxy resin curing agent) to be ball-milled and mixed with the modified graphene nanosheets subjected to ultrasonic stripping; wherein, according to the mass ratio, the conductive carbon nano filler: polymer 5: 95; selecting a steel tank in the ball milling process, selecting zirconia balls as the balls, ball milling at the speed of 200rpm, selecting ball milling for 16min and suspending for 8min in the ball milling program, transferring the ball-milled liquid mixture into a polypropylene plastic box, standing at room temperature until the organic solvent is completely volatilized naturally, and then placing into an oven for further curing. The cured conductive composite material film is cut into a proper shape, the film is attached to the connection structure of the lugs of the airplane by using an interface agent, and the connection structure is connected with a lead by conductive slurry to obtain the strain sensor, and the schematic diagram of the packaging and control flow of the strain sensor is shown in figure 2.
And step 3: and (3) packaging the strain sensor by using a packaging film, and connecting the strain sensor with a data acquisition device for monitoring.
Example 3
A method for preparing a micro-nano sensor for monitoring the health state of an aircraft lug connection structure comprises the following steps:
step 1:
subjecting natural intercalated graphite flakes to high-temperature expansion (900 ℃) to obtain high-temperature expanded graphite, adding a modified surfactant-siloxane coupling agent into a grinding body for grinding, washing with an organic solvent, and further carrying out ultrasonic stripping at low temperature (15 ℃) to obtain modified graphene nanosheets, wherein the schematic preparation flow diagram is shown in FIG. 1; wherein, according to the mass ratio, the high-temperature expanded graphite: 1:6 of modified surfactant;
step 2:
taking a proper amount of a component A (silicon rubber) and the modified graphene nanosheet subjected to ultrasonic stripping, and ball-milling and mixing the component A and the modified graphene nanosheet in an organic solvent-toluene, wherein the weight ratio of the graphene nanosheet: 8:92 parts of silicon rubber; selecting a steel tank in the ball milling process, selecting zirconia balls as the balls, ball milling at the speed of 400rpm, selecting ball milling for 20min and pausing for 10min in the ball milling program, adding a component B (silicon rubber curing agent) in proportion after ball milling, uniformly stirring, heating to completely volatilize an organic solvent, curing to obtain a composite material film at the edge, pasting the composite material film at a distribution control position of an airplane lug connection structure by adopting an interface agent, and connecting a lead by conductive slurry to obtain a strain sensor;
and step 3: and (3) packaging the strain sensor by using a packaging film, and connecting the strain sensor with a data acquisition device for monitoring.
Example 4
A method for preparing a micro-nano sensor for monitoring the health state of an aircraft lug connection structure comprises the following steps:
step 1:
subjecting natural intercalated graphite flakes to high-temperature expansion (1500 ℃) to obtain high-temperature expanded graphite, adding a modified surfactant-siloxane coupling agent into a grinding body for grinding, washing with an organic solvent, carrying out ball-milling stripping at low temperature (0 ℃), selecting a steel tank in the ball-milling process, selecting zirconium carbide balls as the balls, carrying out ball-milling at the speed of 400rpm, selecting ball-milling for 20min and pausing for 10min in the ball-milling procedure to obtain modified graphene nanosheets, wherein the schematic diagram of the preparation process is shown in FIG. 1; wherein, according to the mass ratio, the high-temperature expanded graphite: 1:5 of modified surfactant;
step 2:
taking a proper amount of a component A (epoxy resin) and modified graphene nanosheets subjected to ultrasonic stripping, ball-milling and mixing in an organic solvent-acetone, selecting a steel tank in the ball-milling process, selecting zirconia balls as the balls, ball-milling at a speed of 400rpm, selecting ball-milling procedures of ball-milling for 15min and suspending for 10min, and heating after ball-milling to completely volatilize the organic solvent; wherein, graphene nanoplatelets: 8:92 parts of epoxy resin; adding the component B (epoxy resin curing agent) in proportion, uniformly stirring, coating the mixture on a distribution control position of an aircraft lug connecting structure, connecting a lead through conductive slurry, and putting the mixture into an oven for curing to obtain a strain sensor;
and step 3: and (3) packaging the strain sensor by using a packaging film, and connecting the strain sensor with a data acquisition device for monitoring.
Example 5
A method for preparing a micro-nano sensor for monitoring the health state of an aircraft lug connection structure comprises the following steps:
step 1:
subjecting the natural intercalated graphite flakes to high-temperature expansion (1200 ℃) to obtain high-temperature expanded graphite, adding a modified surfactant-siloxane coupling agent into a ball-milling steel tank for ball milling, wherein the ball milling time is 6 hours, the ball is selected from zirconia balls, the ball milling speed is 400rpm, and the ball milling program is selected from ball milling for 20min and pause for 10 min. After ball milling, ball material separation, washing the material by using an organic solvent, and further carrying out ultrasonic stripping at low temperature (10 ℃) to obtain a modified graphene nanosheet, wherein the schematic diagram of the preparation process is shown in FIG. 1; wherein, according to the mass ratio, the high-temperature expanded graphite: 1:3 of modified surfactant;
step 2:
taking a proper amount of the component A (silicon rubber) and the modified graphene nanosheets subjected to ultrasonic stripping, ball-milling and mixing in an organic solvent-ethylene glycol, selecting a steel tank in the ball-milling process, selecting stainless steel balls as the balls, ball-milling at the speed of 200rpm, selecting ball-milling procedures for 15min and suspending for 8min, and heating after ball-milling to completely volatilize the organic solvent; wherein, graphene nanoplatelets: silicone rubber 4: 96; adding the component B (silicon rubber curing agent) in proportion, uniformly stirring, coating the mixture on a distribution control position of an airplane lug connecting structure, connecting a lead through conductive slurry, and putting the mixture into an oven for curing to obtain a strain sensor;
and step 3: and (3) packaging the strain sensor by using a packaging film, and connecting the strain sensor with a data acquisition device for monitoring.
Example 6
A method for preparing a micro-nano sensor for monitoring the health state of an aircraft lug connection structure comprises the following steps:
step 1:
after natural intercalated graphite flakes are subjected to high-temperature expansion (1200 ℃), adding an organic solvent for further ultrasonic stripping at a low temperature (10 ℃) to obtain graphene nanosheets; adding the graphene nanosheets into a ball-milling steel tank, adding a modified surfactant-siloxane coupling agent, and carrying out ball milling for 6 hours at a ball-milling speed of 400rpm for zirconium oxide balls, wherein the ball-milling program is ball-milling for 20min and suspending for 10 min. After ball milling, separating ball materials, and washing with an organic solvent to obtain a modified graphene nanosheet, wherein the schematic preparation flow diagram is shown in fig. 1; wherein, according to the mass ratio, the graphene nano sheet: modified surfactant 1: 7;
step 2:
taking a proper amount of the component A (silicon rubber) and the modified graphene nanosheets subjected to ultrasonic stripping, ball-milling and mixing in an organic solvent-ethylene glycol, selecting a steel tank in the ball-milling process, selecting stainless steel balls as the balls, ball-milling at the speed of 20rpm, selecting ball-milling procedures of ball-milling for 15min and suspending for 8min, and heating after ball-milling to completely volatilize the organic solvent; wherein, graphene nanoplatelets: silicone rubber 10: 90; adding the component B (silicon rubber curing agent) in proportion, uniformly stirring, coating the mixture on a distribution control position of an airplane lug connecting structure, connecting a lead through conductive slurry, and putting the mixture into an oven for curing to obtain a strain sensor;
and step 3: and (3) packaging the strain sensor by using a packaging film, and connecting the strain sensor with a data acquisition device for monitoring.
Example 7
A method for preparing a micro-nano sensor for monitoring the health state of an aircraft lug connection structure comprises the following steps:
step 1:
adding the carbon nano tube into a ball milling steel tank, adding a modified surfactant-siloxane coupling agent, and carrying out ball milling for 8 hours, wherein the ball milling speed is 300rpm, and the ball milling program is ball milling for 15min and pause for 9 min. After ball milling, ball material is separated, and an organic solvent is used for washing to obtain the modified carbon nano tube, wherein the preparation flow schematic diagram of the modified carbon nano tube is shown in figure 1; wherein, according to the mass ratio, the carbon nano tube: modified surfactant 1: 2;
step 2:
taking a proper amount of the component A (silicon rubber) and the modified carbon nano tube which is stripped by ultrasonic, performing ball milling and mixing in an organic solvent-ethylene glycol, selecting a steel tank in the ball milling process, selecting stainless steel balls as the balls, performing ball milling at the speed of 20rpm, selecting ball milling procedures for 15min and pausing for 8min, and heating after ball milling to completely volatilize the organic solvent; wherein, graphene nanoplatelets: silicone rubber 4: 96; adding the component B (silicon rubber curing agent) in proportion, uniformly stirring, coating the mixture on a distribution control position of an airplane lug connecting structure, connecting a lead through conductive slurry, and putting the mixture into an oven for curing to obtain a strain sensor;
and step 3: and (3) packaging the strain sensor by using a packaging film, and connecting the strain sensor with a data acquisition device for monitoring.
Comparative example
A method for manufacturing a micro-nano sensor for monitoring the health state of an aircraft lug connection structure is the same as that in embodiment 1, and is different from the following steps: according to the strain sensor prepared by the method, the graphene nanosheets are insufficiently stripped, cannot be relatively uniformly dispersed in the epoxy resin, cannot form a strong interface with the epoxy resin, easily form stress concentration points, cannot effectively enhance the mechanical and conductive properties of the epoxy resin and the like, and finally influence the sensing performance of the micro-nano sensor.
Application example
Before monitoring the micro-nano sensor for monitoring the health state of the lug connecting structure of the airplane, calibrating the micro-nano sensor: the adopted connection structure of the lug of the airplane is a standard part.
According to the mechanical simulation calculation of the airplane lug connecting structure, obtaining the position (shown in figure 3) of the airplane lug connecting structure, which is easy to damage and lose efficacy;
the micro-nano sensor for monitoring the health state of the aircraft lug connecting structure prepared in the embodiment is packaged at the position of the aircraft lug connecting structure, which is easy to damage and lose efficacy; and observing the damage failure condition of the part by using a microscope.
Monitoring the aircraft lug connecting structure through the strain sensor to obtain a tensile state monitoring response curve (see fig. 4) of the aircraft lug connecting structure, fitting the tensile state monitoring response curve into a curve, and obtaining the relationship between the resistance change of the sensor and the strain change of the aircraft lug connecting structure as follows:
the resistance of the strain sensor is increased along with the increase of the strain of the connection structure of the lug of the airplane, and when the change rate of the resistance exceeds 5%, the irreversible damage failure of the connection structure of the lug of the airplane is shown;
and correspondingly obtaining the damage condition of the part, and observing through a microscope, judging that the part is damaged when a crack appears, and indicating that the connection structure of the airplane ear is damaged and should be replaced when the resistance change rate exceeds 5%.
Monitoring the aircraft lug connecting structure through the strain sensor to obtain a fatigue state monitoring response curve (see fig. 5) of the aircraft lug connecting structure, fitting the fatigue state monitoring response curve into a curve, and obtaining the relationship between the resistance change of the sensor and the fatigue life of the aircraft lug connecting structure as follows:
the resistance change of the strain sensor tends to be in a stable range along with the increase of the fatigue cycle times of the aircraft lug connecting structure, after the fatigue cycle times exceed 35000 times, the resistance change rate is increased rapidly, the fluctuation range of the resistance change rate is increased by 0.2-0.4%, and the irreversible fatigue damage failure of the aircraft lug connecting structure is shown;
and correspondingly obtaining the damage condition of the part, observing through a microscope, judging as damage when cracks appear, and indicating that the service life of the connection structure of the aircraft ear is basically finished and the connection structure of the aircraft ear is required to be replaced when the fatigue cycle number exceeds 35000.
Monitoring the aircraft lug connecting structure through the strain sensor to obtain response curves (see fig. 6) of the aircraft lug connecting structure at different temperatures, fitting the response curves into a curve, and obtaining the relationship between the resistance change of the sensor and the temperature change of the aircraft lug connecting structure as follows:
the resistance of the strain sensor is increased along with the increase of the temperature of the service environment of the aircraft lug connecting structure, and when the resistance change rate exceeds 5%, the irreversible damage failure of the aircraft lug connecting structure is shown.
Claims (10)
1. A micro-nano sensor for monitoring the health state of an aircraft lug connecting structure is characterized by comprising a strain sensor and a data acquisition device; the strain sensor comprises a conductive composite material film, conductive slurry and a lead, wherein the conductive composite material film is connected with the lead through the conductive slurry, and the lead of the strain sensor is connected with a data acquisition device;
the strain sensor is arranged on the aircraft lug connecting structure and used for acquiring resistance change information of the strain sensor when the aircraft lug connecting structure is subjected to external force load and environmental change;
and the data acquisition device is used for collecting and analyzing resistance change information of the strain sensor to judge the stress state and the environmental temperature of the connection structure of the tabs of the airplane.
2. A method for preparing a micro-nano sensor for monitoring the health state of an aircraft lug connection structure is characterized by comprising the following steps:
step 1: preparation of modified conductive carbon nanofiller
Mixing and grinding or ball-milling the prepared conductive carbon nano-filler and the modified surfactant to obtain a modified conductive carbon nano-filler;
or adding a modified surfactant to mix and grind or ball mill in the process of preparing the conductive carbon nano filler to obtain the modified conductive carbon nano filler;
wherein, the grinding or ball milling time is 3-10 h, and the conductive carbon nano filler comprises the following components in percentage by mass: modified surfactant 1: (2-7);
step 2: preparation of conductive composite film
Uniformly dispersing the modified conductive carbon nano filler and the polymer in a ball milling process to obtain a conductive composite material mixture; wherein, according to the mass ratio, the modified conductive carbon nano filler: a polymer (2-10): (90-98);
and step 3: preparation of strain sensor
The method is divided into different preparation processes according to different modes of arranging the connection structure on the lug plate of the airplane;
the mode of arranging on the connection structure of the aircraft lug is divided into a spin coating method or a pasting method:
spin coating method: after the conductive composite material mixture volatilizes the solvent, adding the curing agent, then coating the mixture on the connection structure of the airplane ear, fixing the conducting wire on the coating part by adopting conductive slurry, and then curing to obtain the strain sensor;
the application method comprises the following steps: adding a curing agent into the conductive composite material mixture, then volatilizing the solvent, curing to obtain a conductive composite material film, and connecting the conductive composite material film with a lead through conductive slurry to obtain a strain sensor; applying the strain sensor to the monitoring position of the connection structure of the lug of the airplane by adopting an interface agent;
and 4, step 4: and (3) packaging the strain sensor by using a packaging film, and connecting the strain sensor with a data acquisition device for monitoring.
3. The method for preparing the micro-nano sensor for monitoring the health state of the lug connection structure of the airplane according to claim 1, wherein the conductive carbon nano filler is a graphene nano sheet and/or a carbon nano tube; the modified surfactant is siloxane coupling agent or amino-terminated epoxy curing agent.
4. The method for preparing a micro-nano sensor for monitoring the health state of an aircraft lug connection structure according to claim 3, wherein the graphene nanosheets are prepared by a method of high-temperature expansion and low-temperature ultrasonic stripping or ball milling stripping.
5. The method for preparing the micro-nano sensor for monitoring the health state of the connection structure of the tabs of the airplane according to claim 1, wherein a steel tank is selected in a ball milling process, one of zirconia balls, tungsten carbide balls and stainless steel balls is selected as the ball milling speed, the ball milling speed is 200-600 rpm, and the ball milling program is selected for ball milling for 15-20 min and is suspended for 8-10 min.
6. The method for preparing the micro-nano sensor for monitoring the health state of the connection structure of the tabs of the airplane according to claim 1, wherein in the step 1, the polymer is one of epoxy resin and silicon rubber.
7. The method for preparing a micro-nano sensor for monitoring the health state of an aircraft ear connection structure according to claim 1, wherein in the step 2, the modified conductive carbon nano filler is stripped in a solvent by ultrasonic or ball milling, and a polymer is added into a mixed solution after ultrasonic or ball milling; the solvent is one or more of toluene, glycol and ketone organic solvents.
8. A method for monitoring a micro-nano sensor for monitoring the health state of an aircraft lug connection structure is characterized by comprising the following steps:
stress state, fatigue life and ambient temperature in the aircraft lug connecting structure are monitored through the strain sensor, and then the stress state, the fatigue life and the ambient temperature of the aircraft lug connecting structure are judged by transmitting the stress state, the fatigue life and the ambient temperature to the data processing device and analyzing resistance change information monitored by the strain sensor.
9. The method for monitoring the micro-nano sensor for monitoring the health state of the connection structure of the aircraft tabs according to claim 8, wherein when the strain sensor monitors that the resistance change rate is greater than 5%, the connection structure of the aircraft tabs is irreversibly damaged, namely stressed damage or temperature damage of a service environment.
10. The method for monitoring the micro-nano sensor for monitoring the health state of the aircraft tab connection structure according to claim 8, wherein the resistance change rate continuously fluctuates within a stable range, and the fluctuation range of the sudden resistance change rate is increased by 0.2-0.4%, which indicates that the aircraft tab connection structure has irreversible fatigue damage failure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110683580.9A CN113375544B (en) | 2021-06-21 | 2021-06-21 | Micro-nano sensor for monitoring health state of connection structure of lug of airplane and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110683580.9A CN113375544B (en) | 2021-06-21 | 2021-06-21 | Micro-nano sensor for monitoring health state of connection structure of lug of airplane and manufacturing method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113375544A true CN113375544A (en) | 2021-09-10 |
| CN113375544B CN113375544B (en) | 2022-11-29 |
Family
ID=77577888
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110683580.9A Active CN113375544B (en) | 2021-06-21 | 2021-06-21 | Micro-nano sensor for monitoring health state of connection structure of lug of airplane and manufacturing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113375544B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102107845A (en) * | 2009-12-25 | 2011-06-29 | 中国科学院金属研究所 | Micron sensing element, and preparation method and application thereof |
| US20130312535A1 (en) * | 2010-09-20 | 2013-11-28 | Bae Systems Plc | Structural health monitoring using sprayable paint formulations |
| CN103808247A (en) * | 2012-11-06 | 2014-05-21 | 沈阳航空航天大学 | Preparation method for strain sensor based on carbon nano tube three-dimensional network film |
| CN107573557A (en) * | 2017-10-12 | 2018-01-12 | 沈阳航空航天大学 | The method that solution blended process prepares graphene/elastomer nanocomposites |
| CN108859300A (en) * | 2018-06-14 | 2018-11-23 | 沈阳航空航天大学 | A kind of high sensitivity graphene flexibility strain transducer and preparation method thereof |
| CN108896617A (en) * | 2018-06-20 | 2018-11-27 | 北京航数车辆数据研究所有限公司 | A kind of structural healthy monitoring system based on electroconductive polymer coating array |
| CN109341512A (en) * | 2018-10-30 | 2019-02-15 | 中国运载火箭技术研究院 | A kind of strain transducer, structure monitoring system and manufacturing method |
| CN112345592A (en) * | 2020-10-07 | 2021-02-09 | 大连理工大学 | Real-time monitoring method for optimized layout strain of loop-type measuring point of aircraft composite material key structure |
-
2021
- 2021-06-21 CN CN202110683580.9A patent/CN113375544B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102107845A (en) * | 2009-12-25 | 2011-06-29 | 中国科学院金属研究所 | Micron sensing element, and preparation method and application thereof |
| US20130312535A1 (en) * | 2010-09-20 | 2013-11-28 | Bae Systems Plc | Structural health monitoring using sprayable paint formulations |
| CN103808247A (en) * | 2012-11-06 | 2014-05-21 | 沈阳航空航天大学 | Preparation method for strain sensor based on carbon nano tube three-dimensional network film |
| CN107573557A (en) * | 2017-10-12 | 2018-01-12 | 沈阳航空航天大学 | The method that solution blended process prepares graphene/elastomer nanocomposites |
| CN108859300A (en) * | 2018-06-14 | 2018-11-23 | 沈阳航空航天大学 | A kind of high sensitivity graphene flexibility strain transducer and preparation method thereof |
| CN108896617A (en) * | 2018-06-20 | 2018-11-27 | 北京航数车辆数据研究所有限公司 | A kind of structural healthy monitoring system based on electroconductive polymer coating array |
| CN109341512A (en) * | 2018-10-30 | 2019-02-15 | 中国运载火箭技术研究院 | A kind of strain transducer, structure monitoring system and manufacturing method |
| CN112345592A (en) * | 2020-10-07 | 2021-02-09 | 大连理工大学 | Real-time monitoring method for optimized layout strain of loop-type measuring point of aircraft composite material key structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113375544B (en) | 2022-11-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Zhang et al. | Impact behaviour of GLAREs with MWCNT modified epoxy resins | |
| Sam-Daliri et al. | Structural health monitoring of defective single lap adhesive joints using graphene nanoplatelets | |
| CN113375544B (en) | Micro-nano sensor for monitoring health state of connection structure of lug of airplane and manufacturing method thereof | |
| Dong et al. | Experimental study on the ice freezing adhesive characteristics of metal surfaces | |
| Okabe et al. | Prediction of tensile strength of unidirectional CFRP composites | |
| Robert et al. | Improving through‐thickness conductivity of carbon fiber reinforced polymer using carbon nanotube/polyethylenimine at the interlaminar region | |
| Cardoso et al. | Effect of external loads on damage detection of rubber‐toughened nanocomposites using carbon nanotubes sensory network | |
| KR101680090B1 (en) | Method for testing contact fatigue test of composit structure | |
| Al-Bahrani et al. | Damage sensing and mechanical properties of a laminate composite material containing MWCNTs during low-velocity impact | |
| CN109486204A (en) | A kind of heat conductive insulating composite material and preparation method | |
| Rubio-González et al. | Damage progression monitoring using self-sensing capability and acoustic emission on glass fiber/epoxy composites and damage classification through principal component analysis | |
| Marguerès et al. | Preliminary experimental study on the electrical impedance analysis for in-situ monitoring of the curing of carbon/epoxy composite material for aeronautical and aerospace structures | |
| CN113376224A (en) | Nano paper sensor for monitoring crack damage evolution of connection structure of lug of airplane and manufacturing method thereof | |
| CN112630045B (en) | Creep life prediction method of nickel-based single crystal alloy based on real blade sample | |
| Wang et al. | Biaxial fatigue of fiber-reinforced composites at cryogenic temperatures. Part I: fatigue fracture life and mechanisms | |
| CN112782073A (en) | Method for testing bonding strength of high-temperature-resistant low-emissivity coating | |
| Huo et al. | Self-sensing properties of bending deformation of buckypaper composites | |
| CN113956619A (en) | Skin material for electric heating ice prevention and removal of airplane and preparation method thereof | |
| CN103697942A (en) | Method for verifying cage rotor induction brazing technique | |
| Shu et al. | Three-point bending damage detection of GFRP composites doped with graphene oxide by acoustic emission technology | |
| Minty et al. | The role of the epoxy resin: curing agent ratio in composite interfacial strength by single fibre microbond test | |
| Arun et al. | Improving the De-Icing Properties of Wing Structure by Adding Graphene Filler into the Composite Structure | |
| Tsai et al. | Geometric nonlinear effect on biaxial bending strength of thin silicon die in the PoEF test | |
| Wang et al. | A novel carbon nanotubes (CNTs) film displacement sensor for countersink depth control | |
| Jebaraj et al. | Finite Element Predictions for the Thermoelastic Properties and Interphase Fracture of Titanium Nitride/AA3003 Alloy Particle-Reinforced Composites |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |