CN103640713A - Monitoring system of aircraft structure fatigue part - Google Patents
Monitoring system of aircraft structure fatigue part Download PDFInfo
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- CN103640713A CN103640713A CN201310693825.1A CN201310693825A CN103640713A CN 103640713 A CN103640713 A CN 103640713A CN 201310693825 A CN201310693825 A CN 201310693825A CN 103640713 A CN103640713 A CN 103640713A
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- strain gage
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Abstract
The invention provides a monitoring system of an aircraft structure fatigue part. The system comprises intelligent coating sensors and strain meters bonded on the surface of the fatigue part, as well as a measuring device, wherein the number of the intelligent coating sensors and the number of the strain meters are set according to monitoring requirements of the fatigue part; the intelligent coating sensors and the strain meters are sequentially connected in series; the measuring device is connected with the intelligent coating sensors and the strain meters, provides power supply and constant current for the intelligent coating sensors and the strain meters and is used for collecting respective voltage values of the intelligent coating sensors and the strain meters after the system is powered on; and the intelligent coating sensors and the strain meters are recognized according to collected voltage values, and a monitoring result of the fatigue part is generated according to recorded voltage values. According to the monitoring system of the aircraft structure fatigue part, strain course recording and crack damage monitoring can be performed simultaneously under the limitation of space and weight.
Description
Technical field
The present invention relates to crack monitoring field, in particular to the monitoring system of the tired parts of aircaft configuration.
Background technology
Due to problems such as environment for use, tenure of use, may there is Crack Damage and affect flight safety in the phase to each structure member of aircraft under arms.These damages all must be captured and repair before appearance, and the damage of significant points afterwards also must its state of development of monitoring in repairing.Usually, correlation technique is installed strain gage at aircaft configuration key position, use conventional strain recording device records aircaft configuration key position strain history in use, on the basis of fatigue damage theory, can judge according to the strain history of record the service condition of aircaft configuration key position.For the structural key position of particular importance, except recording the strain history in use procedure, also need to use smart coat sensor and corresponding recording device directly to monitor Crack Damage, early stage of development of Crack Damage can and alarm.
For example, owing to using different sensors (: strain gage and smart coat sensor), when the tired key position of current aircaft configuration is carried out to strain history record and damage monitoring, need to use two kinds of different equipment and two covers to measure cable.In some special significant points, due to space and heavily quantitative limitation, do not allow to install two complete equipments, be therefore difficult to carry out the monitoring of strain history record and Crack Damage simultaneously.
Summary of the invention
The object of the present invention is to provide the monitoring system of the tired parts of a kind of aircaft configuration, to solve the above problems.
The monitoring system of the tired parts of a kind of aircaft configuration is provided in an embodiment of the present invention, comprise: be mounted on smart coat sensor and the strain gage of tired parts surface, the number of smart coat sensor and the number of strain gage are set according to the monitoring requirements of tired parts; Each smart coat sensor and each strain gage are connected successively; The measurement mechanism being all connected with strain gage with smart coat sensor; Measurement mechanism provides power supply and constant current for smart coat sensor and strain gage, and for gathering smart coat sensor and strain gage magnitude of voltage separately after powering in system, according to the magnitude of voltage identification intelligent coating sensor and the strain gage that gather, according to recognition result, record the magnitude of voltage of each smart coat sensor and strain gage, and according to the magnitude of voltage of record, generate the monitoring result of tired parts.
The said system of the embodiment of the present invention forms current return by smart coat sensor and strain gage series connection, and by measurement mechanism, gather the magnitude of voltage of each smart coat sensor and strain gage, can to the strain of tired parts and Crack Damage signal, monitor simultaneously, which does not need for smart coat sensor and the independent measurement mechanism of each self-configuring of strain gage, therefore can realize under space and weight limits, carry out the monitoring of strain history record and Crack Damage simultaneously, strengthen the reliability of tired parts monitoring, and then promoted the safety of aircraft.
Accompanying drawing explanation
Fig. 1 shows the structured flowchart of the monitoring system of the tired parts of aircaft configuration that the embodiment of the present invention provides;
Fig. 2 shows the circuit diagram of the monitoring system of the tired parts of aircaft configuration that the embodiment of the present invention provides;
Fig. 3 shows the schematic diagram of the adaptive measuring circuit that the embodiment of the present invention provides;
Fig. 4 shows the physical circuit schematic diagram of the pressure reduction amplification module that the embodiment of the present invention provides;
Fig. 5 shows the connection diagram of sensor in the monitoring system of the tired parts of aircaft configuration that the embodiment of the present invention provides.
The specific embodiment
Below by specific embodiment, also by reference to the accompanying drawings the present invention is described in further detail.
The embodiment of the present invention provides the monitoring system of the tired parts of aircaft configuration, in order to realize, the strain of structure and Crack Damage signal are carried out to adaptive measuring simultaneously, the survey record that especially the tired key position of military aircraft structure is carried out to strain history record and Crack Damage monitoring simultaneously.Below by embodiment, be described.
The structured flowchart of the monitoring system of the tired parts of aircaft configuration shown in Figure 1, comprising:
Be mounted on smart coat sensor and the strain gage of tired parts surface, wherein, the number of smart coat sensor and the number of strain gage are set according to the monitoring requirements of tired parts; Each smart coat sensor and each strain gage are connected successively, in Fig. 1, take two smart coat sensors (being smart coat sensor 12a and smart coat sensor 12b) and two strain gages (being strain gage 14a and strain gage 14b) describes as example, two smart coat sensors and two strain gages are as long as connect, and mutual order is restriction not;
The measurement mechanism 20 being all connected with strain gage with smart coat sensor; Measurement mechanism 20 provides power supply and constant current for smart coat sensor and strain gage, and for gathering smart coat sensor and strain gage magnitude of voltage separately after powering in system, according to the magnitude of voltage identification intelligent coating sensor and the strain gage that gather, according to recognition result, record the magnitude of voltage of each smart coat sensor and strain gage, and according to the magnitude of voltage of record, generate the monitoring result of tired parts.
The system of the present embodiment forms current return by smart coat sensor and strain gage series connection, and by measurement mechanism, gather the magnitude of voltage of each smart coat sensor and strain gage, can to the strain of tired parts and Crack Damage signal, monitor simultaneously, which does not need for smart coat sensor and the independent measurement mechanism of each self-configuring of strain gage, therefore can realize under space and weight limits, carry out the monitoring of strain history record and Crack Damage simultaneously, strengthen the reliability of tired parts monitoring, and then promoted the safety of aircraft.
When specific implementation, above-mentioned measurement mechanism 20 can comprise with lower module:
(1) provide module with constant current source module and the power supply of smart coat sensor and strain gage formation current return;
(2) the pressure reduction amplification module that goes between and be connected with the measurement at each smart coat sensor and strain gage two ends, for amplifying the pressure reduction of measuring between lead-in wire according to the magnification factor arranging;
(3) each pressure reduction amplification module is connected with a data acquisition module, for gather the data of pressure reduction amplification module output according to the frequency acquisition arranging; Wherein, the initial magnification factor of this pressure reduction amplification module is 1;
(4) data recordin module, the data that gather for record data acquisition module;
(5) device recognition module, after powering in system, according to smart coat sensor and the strain gage magnitude of voltage separately of data recordin module record, identifies each smart coat sensor and strain gage;
(6) pressure reduction amplifies control module, for the magnification factor of pressure reduction amplification module and the frequency acquisition of data acquisition module are set according to the recognition result of device recognition module.
Wherein, above-mentioned pressure reduction amplification module can be two-stage instrumentation amplifier, and its internal resistance is greater than resistance threshold, adopts the instrumentation amplifier that internal resistance is larger as far as possible, to ignore the resistance of measuring lead-in wire.
In addition, whether constant in order to measure the electric current of the current return that smart coat sensor and strain gage form, above-mentioned smart coat sensor and strain gage are also in series with a reference resistance, the two ends of this reference resistance are connected with measurement mechanism, so that measurement mechanism impact on survey precision by the electric current minor fluctuations that gathers the voltage at reference resistance two ends and automatically eliminate constant current source module.
Based on above-mentioned implementation, the circuit diagram of the monitoring system of the tired parts of aircaft configuration as shown in Figure 2, wherein, the embodiment of the present invention utilizes strain gage and smart coat sensor from being all characteristics of resistance in essence, in Fig. 2, with resistance, represents strain gage and smart coat sensor.In Fig. 2, strain gage and smart coat sensor are together in series, and measurement mechanism formation current return, the two ends of each sensor have the lead-in wire of measurement to be connected with measurement mechanism (i.e. pressure reduction amplification module and data acquisition module in figure).In Fig. 2, dotted portion is pressure reduction amplification module, and solid line boxes is data acquisition module.R
grepresent the initial resistance of strain gage resistance, Δ R
grepresent the change in resistance value of strain gage resistance.R
irepresent the initial resistance of smart coat sensor, Δ R
irepresent the change in resistance value of smart coat sensor.Some two kinds of sensors (being strain gage and smart coat sensor) are cascaded by a current return, on loop, by constant current source, keep current constant, by the pressure drop of measuring on each sensor, obtain sensor electrical resistance and variable quantity thereof.Pressure reduction amplification module selects the instrumentation amplifier that input resistance is higher to form, under high input impedance, can think that the electric current passing through on measure traverse line can ignore, be the variation of measure traverse line resistance on result of a measurement without impact, and due to the effect of constant current source, connect the wire resistance of each sensor also on measuring without impact.For the electric current on Real-time Collection current source, in current return, seal in a reference resistance R
ref.Can find out, after each sensor is cascaded by a current return, each sensor is introduced test macro by two measure traverse lines simultaneously, compares with adopting the wheatstone bridge of trilinear method, and each sensor is used a wire less.
Set reference resistance resistance just in time identical with strain gage resistance, (smart coat sensor model number is more, and ununified resistance value, therefore inapplicable the method), obtains thus:
V
g-V
ref=IΔR
g （1）
In formula (1), V
gfor pressure drop on strain gage, and V
reffor pressure drop on reference resistance.I is current value on measuring circuit, for:
I=V
ref/R
ref （2）
In formula (2), R
reffor known, V
refcan record.So formula (1) can turn to:
In formula (4), K is resistance strain gauge sensitivity coefficient, and ε is strain.
Same, can obtain the observed reading of smart coat sensor:
In formula (5), R
ithe initial resistance of smart coat sensor, Δ R
iit is the change in resistance value of smart coat sensor.From formula (4) and (5), current-series metering circuit can be connected on two kinds of sensors in same current return and measure.
The resistance that is generally used for the strain gage of structural strain course monitoring is 350 Ω, and the resistance of smart coat sensor is generally 0.3 Ω left and right, strain gage and smart coat sensor senses device that the constant current producing when constant current source is flowed through in series loop by measuring series loop, voltage in strain gage and the generation of smart coat sensor two ends is the difference of the order of magnitude, according to this feature, the present embodiment also provides the adaptive measuring circuit of a kind of strain gage and smart coat sensor, the schematic diagram of adaptive measuring circuit as shown in Figure 3, wherein, this circuit is by power module (be equivalent to above-mentioned power supply module is provided), constant current source module and pressure reduction amplification module form, constant current source is mainly sensor (being equivalent to above-mentioned strain gage and smart coat sensor) and reference resistance provides stable constant current, power module provides required constant pressure source for circuit each several part, pressure reduction amplification module adopts two-stage instrument amplifier to realize the extraction to sensor signal, adaptive measuring circuit is according to the pressure drop size automatic decision sensor type at sensor two ends, according to the type of each sensor, adjust again the signal amplification factor of pressure reduction amplification module.
Wherein, as shown in Figure 4, it is secondary instrument discharge circuit to the physical circuit schematic diagram of above-mentioned pressure reduction amplification module, identical with Fig. 2 of the physical significance of each resistance, and the PORT in Fig. 4 is interface board, in order to connect each lead-in wire.
The measurement mechanism 20 of the present embodiment can be take ARM embedded platform as core builds, and adopts the adaptive measuring circuit of the strain gage shown in above-mentioned Fig. 3 and smart coat sensor.LAN(Local Area Network, local area network) data transmission between Interface realization equipment and ground maintenance computing machine.When aircraft aloft flies, measurement mechanism can be connected with 28 volts of direct current (DC) (VDC) source on aircraft, adopts the 28 volts of direct current (DC) (VDC) on aircraft to power; Aircraft is when ground, and measurement mechanism can be connected with ground 28 volts of direct supplys, adopts 28 volts of direct current (DC) on ground to power.
In order to report to the police in time, above-mentioned measurement mechanism 20 also comprises: device change in resistance computing module, for calculate the change in resistance value of corresponding smart coat sensor or strain gage according to the magnitude of voltage of record; Alarm module, while being greater than corresponding threshold value for the change in resistance value of the smart coat sensor that calculates when device change in resistance computing module or strain gage, reports to the police.
The connection diagram of sensor in the monitoring system of the tired parts of aircaft configuration shown in Figure 5.This figure need to install 4 smart coat sensors and 2 strains with the structural health monitoring of a certain seat of fatigue of aircraft and count example and describe.Wherein, heavy line represents current return, and fine line represents to measure lead-in wire, and little rectangular box represents strain gage, ellipse representation smart coat sensor, and dashed region is damage field.These 6 sensors are mounted on after body structure surface according to technological requirement, by the mode of series connection, are connected with measurement mechanism.The order of 6 sensors series connection does not affect result of a measurement, measurement mechanism after start by automatic distinguishing strain gage and smart coat sensor.For strain gage, measurement mechanism is by according to the frequency collection of 320Hz record data; For smart coat sensor, measurement mechanism is by according to the frequency collection of 1Hz record data.If smart coat sensor detects Crack Damage, measurement mechanism will be reported to the police.
The system that above embodiment provides can be used a kind of device (being measurement mechanism) and a set of measurement cable to monitor strain signal and the Crack Damage signal of the tired key position of aircaft configuration simultaneously.In the more concentrated structure control region of sensor, can reduce the quantity of measuring lead-in wire, and in relevant strain monitoring system or smart coat monitoring system, sensor of every increase needs three lead-in wires, sensor of the every increase of system of above-described embodiment only need to increase by one to two lead-in wire.
Said system, except the strain history record and Crack Damage monitoring of the tired key position of outfield aircaft configuration, is also applicable to strain history record and the Crack Damage monitoring of aircaft configuration in test cell environment.
Obviously, those skilled in the art should be understood that, above-mentioned each module of the present invention or each step can realize with general computer device, they can concentrate on single computer device, or be distributed on the network that a plurality of computer devices form, alternatively, they can be realized with the executable program code of computer device, thereby, they can be stored in memory storage and be carried out by computer device, or they are made into respectively to each integrated circuit modules, or a plurality of modules in them or step are made into single integrated circuit module to be realized.Like this, the present invention is not restricted to any specific hardware and software combination.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (6)
1. a monitoring system for the tired parts of aircaft configuration, is characterized in that, comprising:
Be mounted on smart coat sensor and the strain gage of tired parts surface, the number of described smart coat sensor and the number of described strain gage are set according to the monitoring requirements of described tired parts; Described in each, smart coat sensor is connected successively with strain gage described in each;
The measurement mechanism being all connected with described strain gage with described smart coat sensor; Described measurement mechanism provides power supply and constant current for described smart coat sensor and described strain gage, and for gathering described smart coat sensor and described strain gage magnitude of voltage separately after powering in described system, according to the described magnitude of voltage gathering, identify described smart coat sensor and described strain gage, according to recognition result, record the magnitude of voltage of smart coat sensor and described strain gage described in each, and according to the described magnitude of voltage of record, generate the monitoring result of described tired parts.
2. system according to claim 1, is characterized in that, described measurement mechanism comprises:
The constant current source module and the power supply that form current return with described smart coat sensor and described strain gage provide module;
The pressure reduction amplification module that goes between and be connected with the measurement at smart coat sensor described in each and described strain gage two ends, for amplifying the pressure reduction between described measurement lead-in wire according to the magnification factor arranging;
Described in each, pressure reduction amplification module is connected with a data acquisition module, for gather the data of described pressure reduction amplification module output according to the frequency acquisition arranging; Wherein, the initial magnification factor of described pressure reduction amplification module is 1;
Data recordin module, for recording the data of described data collecting module collected;
Device recognition module, after powering in described system, according to described smart coat sensor and the described strain gage magnitude of voltage separately of described data recordin module record, identifies smart coat sensor and described strain gage described in each;
Pressure reduction amplifies control module, for the magnification factor of described pressure reduction amplification module and the frequency acquisition of described data acquisition module are set according to the recognition result of described device recognition module.
3. system according to claim 2, is characterized in that, described pressure reduction amplification module is two-stage instrumentation amplifier, and its internal resistance is greater than resistance threshold.
4. system according to claim 2, it is characterized in that, described smart coat sensor and described strain gage are also in series with a reference resistance, the two ends of described reference resistance are connected with described measurement mechanism, and described measurement mechanism is the impact on survey precision by the surge of current that gathers the voltage at described reference resistance two ends and automatically eliminate described constant current source module.
5. system according to claim 1, is characterized in that, described measurement mechanism also comprises:
Device change in resistance computing module, calculates corresponding described smart coat sensor or the change in resistance value of described strain gage for the described magnitude of voltage according to record;
Alarm module, while being greater than corresponding threshold value for the change in resistance value of the described smart coat sensor that calculates when described device change in resistance computing module or described strain gage, reports to the police.
6. system according to claim 1, is characterized in that, when aircraft aloft flies, described measurement mechanism is connected with 28 volts of direct supplys on described aircraft; Aircraft is when ground, and described measurement mechanism is connected with 28 volts of direct supplys on ground.
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Cited By (9)
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| CN105300587A (en) * | 2015-10-21 | 2016-02-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Convenient pressure gauge of airplane |
| CN107014668A (en) * | 2016-04-22 | 2017-08-04 | 北京航空航天大学 | A kind of fatigue crack integrated monitoring based on piezoelectricity and smart coat sensor |
| CN107328561A (en) * | 2017-07-20 | 2017-11-07 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft engine hanging joint Fatigue Test Design method |
| CN107478170A (en) * | 2017-08-29 | 2017-12-15 | 北京航空航天大学 | A kind of implementation method of fibre strain flower and smart coat integrated sensor |
| CN108263639A (en) * | 2018-01-28 | 2018-07-10 | 北京工业大学 | Aircaft configuration key position fatigue life on-line monitoring method based on indirect measuring strain under spectrum carries |
| CN108317947A (en) * | 2017-11-30 | 2018-07-24 | 陕西电器研究所 | Unmanned plane monitoring structural health conditions intelligent assembly |
| CN108318261A (en) * | 2018-01-08 | 2018-07-24 | 中车青岛四方机车车辆股份有限公司 | The monitoring method and device of vehicle structure |
| CN109911245A (en) * | 2019-03-08 | 2019-06-21 | 郑州市傅立叶电子科技有限公司 | A kind of the fatigue part monitoring system and its monitoring method of Flight Vehicle Structure |
| CN112158359A (en) * | 2020-10-12 | 2021-01-01 | 中国地质大学（北京） | Method for detecting fatigue fracture of wing |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105300587A (en) * | 2015-10-21 | 2016-02-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Convenient pressure gauge of airplane |
| CN105300587B (en) * | 2015-10-21 | 2018-03-27 | 沈阳旋飞航空技术有限公司 | The convenient pressure tester of aircraft |
| CN107014668A (en) * | 2016-04-22 | 2017-08-04 | 北京航空航天大学 | A kind of fatigue crack integrated monitoring based on piezoelectricity and smart coat sensor |
| CN107328561A (en) * | 2017-07-20 | 2017-11-07 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft engine hanging joint Fatigue Test Design method |
| CN107478170A (en) * | 2017-08-29 | 2017-12-15 | 北京航空航天大学 | A kind of implementation method of fibre strain flower and smart coat integrated sensor |
| CN107478170B (en) * | 2017-08-29 | 2019-06-28 | 北京航空航天大学 | A kind of colored implementation method with smart coat integrated sensor of fibre strain |
| CN108317947A (en) * | 2017-11-30 | 2018-07-24 | 陕西电器研究所 | Unmanned plane monitoring structural health conditions intelligent assembly |
| CN108318261A (en) * | 2018-01-08 | 2018-07-24 | 中车青岛四方机车车辆股份有限公司 | The monitoring method and device of vehicle structure |
| CN108263639B (en) * | 2018-01-28 | 2018-11-13 | 北京工业大学 | Aircaft configuration key position fatigue life on-line monitoring method based on indirect measuring strain under spectrum carries |
| CN108263639A (en) * | 2018-01-28 | 2018-07-10 | 北京工业大学 | Aircaft configuration key position fatigue life on-line monitoring method based on indirect measuring strain under spectrum carries |
| CN109911245A (en) * | 2019-03-08 | 2019-06-21 | 郑州市傅立叶电子科技有限公司 | A kind of the fatigue part monitoring system and its monitoring method of Flight Vehicle Structure |
| CN112158359A (en) * | 2020-10-12 | 2021-01-01 | 中国地质大学（北京） | Method for detecting fatigue fracture of wing |
| CN112158359B (en) * | 2020-10-12 | 2022-01-04 | 中国地质大学（北京） | Method for detecting fatigue fracture of wing |
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