CN103640713B - The monitoring system of aircraft structure fatigue part - Google Patents

The monitoring system of aircraft structure fatigue part Download PDF

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Publication number
CN103640713B
CN103640713B CN201310693825.1A CN201310693825A CN103640713B CN 103640713 B CN103640713 B CN 103640713B CN 201310693825 A CN201310693825 A CN 201310693825A CN 103640713 B CN103640713 B CN 103640713B
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China
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strain gage
smart coat
module
sensor
coat sensor
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CN201310693825.1A
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Chinese (zh)
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CN103640713A (en
Inventor
张移山
王智
蔡佳昆
王磊
薛军
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中国人民解放军空军装备研究院航空装备研究所
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Priority to CN201310693825.1A priority Critical patent/CN103640713B/en
Publication of CN103640713A publication Critical patent/CN103640713A/en
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Abstract

The invention provides a kind of monitoring system of aircraft structure fatigue part.This system comprises: the smart coat sensor and the strain gage that are mounted on fatigue part surface, and the number of smart coat sensor and the number of strain gage set according to the monitoring requirements of fatigue part; Each smart coat sensor and each strain gage are connected successively; The measurement mechanism be all connected with smart coat sensor and strain gage; 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 upon power-up of the system, according to the magnitude of voltage identification intelligent coating sensor gathered and strain gage, according to the magnitude of voltage of each smart coat sensor of recognition result record and strain gage, and generate the monitoring result of fatigue part according to the magnitude of voltage of record.The present invention can realize, under space and weight limits, carrying out the monitoring of strain history record and Crack Damage simultaneously.

Description

The monitoring system of aircraft structure fatigue part

Technical field

The present invention relates to crack monitoring field, in particular to the monitoring system of aircraft structure fatigue part.

Background technology

Due to the problem 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 also must monitor its state of development after a repair.Usually, correlation technique installs 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, the service condition of aircaft configuration key position can be judged according to the strain history of record.For the structural key position of particular importance, except the strain history in record use procedure, also need to use smart coat sensor and corresponding recording device directly to monitor Crack Damage, Crack Damage the early stage of development can and alarm.

Owing to using different sensors (such as: strain gage and smart coat sensor), when carrying out strain history record and damage monitoring to current aircraft structure fatigue key position, cable measured by the equipment needing use two kinds different and two covers.In some special significant points, due to space and heavily quantitative limitation, do not allow installation two complete equipment, be therefore difficult to the monitoring simultaneously carrying out strain history record and Crack Damage.

Summary of the invention

The object of the present invention is to provide a kind of monitoring system of aircraft structure fatigue part, to solve the above problems.

Provide a kind of monitoring system of aircraft structure fatigue part in an embodiment of the present invention, comprise: the smart coat sensor and the strain gage that are mounted on fatigue part surface, the number of smart coat sensor and the number of strain gage set according to the monitoring requirements of fatigue part; Each smart coat sensor and each strain gage are connected successively; The measurement mechanism be all connected with smart coat sensor and strain gage; 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 upon power-up of the system, according to the magnitude of voltage identification intelligent coating sensor gathered and strain gage, according to the magnitude of voltage of each smart coat sensor of recognition result record and strain gage, and generate the monitoring result of fatigue part according to the magnitude of voltage of record.

Smart coat sensor and strain gage series connection are formed current return by the said system of the embodiment of the present invention, and the magnitude of voltage of each smart coat sensor and strain gage is gathered by measurement mechanism, can monitor the strain of fatigue part and Crack Damage signal simultaneously, which does not need for smart coat sensor and the independent measurement mechanism of each self-configuring of strain gage, therefore, it is possible to realize under space and weight limits, carry out the monitoring of strain history record and Crack Damage simultaneously, enhance the reliability of fatigue part monitoring, and then improve the safety of aircraft.

Accompanying drawing explanation

Fig. 1 shows the structured flowchart of the monitoring system of the aircraft structure fatigue part that the embodiment of the present invention provides;

Fig. 2 shows the circuit diagram of the monitoring system of the aircraft structure fatigue part 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 aircraft structure fatigue part that the embodiment of the present invention provides.

Detailed description of the invention

Also by reference to the accompanying drawings the present invention is described in further detail below by specific embodiment.

Embodiments provide the monitoring system of aircraft structure fatigue part, in order to realization, adaptive measuring is carried out to the strain of structure and Crack Damage signal simultaneously, especially the tired key position of military aircraft structure is carried out to the survey record of strain history record and Crack Damage monitoring simultaneously.Be described below by embodiment.

The structured flowchart of the monitoring system of aircraft structure fatigue part shown in Figure 1, comprising:

Be mounted on smart coat sensor and the strain gage on fatigue part surface, wherein, the number of smart coat sensor and the number of strain gage set according to the monitoring requirements of fatigue part; Each smart coat sensor and each strain gage are connected successively, be described for two smart coat sensors (i.e. smart coat sensor 12a and smart coat sensor 12b) and two strain gages (i.e. strain gage 14a and strain gage 14b) in Fig. 1, as long as two smart coat sensors and two strain gages are connected, mutual order does not limit;

The measurement mechanism 20 be all connected with smart coat sensor and strain gage; 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 upon power-up of the system, according to the magnitude of voltage identification intelligent coating sensor gathered and strain gage, according to the magnitude of voltage of each smart coat sensor of recognition result record and strain gage, and generate the monitoring result of fatigue part according to the magnitude of voltage of record.

Smart coat sensor and strain gage series connection are formed current return by the system of the present embodiment, and the magnitude of voltage of each smart coat sensor and strain gage is gathered by measurement mechanism, can monitor the strain of fatigue part and Crack Damage signal simultaneously, which does not need for smart coat sensor and the independent measurement mechanism of each self-configuring of strain gage, therefore, it is possible to realize under space and weight limits, carry out the monitoring of strain history record and Crack Damage simultaneously, enhance the reliability of fatigue part monitoring, and then improve the safety of aircraft.

When specific implementation, above-mentioned measurement mechanism 20 can comprise with lower module:

(1) the constant current source module and the power supply that form current return with smart coat sensor and strain gage provide module;

(2) go between with each smart coat sensor and the measurement at strain gage two ends the pressure reduction amplification module be connected, for amplifying the pressure reduction measured between lead-in wire according to the magnification factor arranged;

(3) each pressure reduction amplification module is connected with a data acquisition module, for gathering the data that pressure reduction amplification module exports according to the frequency acquisition arranged; Wherein, the initial magnification factor of this pressure reduction amplification module is 1;

(4) data recordin module, for recording the data of data collecting module collected;

(5) device recognition module, for upon power-up of the 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 arranging the magnification factor of pressure reduction amplification module and the frequency acquisition of data acquisition module 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, namely adopts the instrumentation amplifier that internal resistance is larger as far as possible, to ignore the resistance measuring lead-in wire.

In addition, in order to whether the electric current of the current return measuring smart coat sensor and strain gage formation is constant, 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, automatically eliminate the electric current minor fluctuations of constant current source module to the impact of survey precision to make measurement mechanism by the voltage gathering reference resistance two ends.

Based on above-mentioned implementation, the circuit diagram of the monitoring system of aircraft structure fatigue part as shown in Figure 2, wherein, the embodiment of the present invention utilizes strain gage and smart coat sensor to be all inherently characteristics of resistance, represents strain gage and smart coat sensor in Fig. 2 with resistance.Strain gage and smart coat sensor series are got up in Fig. 2, and measurement mechanism forms current return, the two ends of each sensor have measurement lead-in wire to be connected with measurement mechanism (the pressure reduction amplification module namely in figure and data acquisition module).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 (i.e. strain gage and smart coat sensor) are cascaded by a current return, loop keep current constant by constant current source, obtains sensor resistance and variable quantity thereof by the pressure drop of measuring on each sensor.The instrumentation amplifier that pressure reduction amplification module selects input resistance higher is formed, under high input impedance, can think that the electric current that measure traverse line passes through can be ignored, namely the change of measure traverse line resistance on result of a measurement without impact, and due to the effect of constant current source, the wire resistance connecting each sensor also on measurement 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 being cascaded by a current return by each sensor, each sensor introduces test macro by two measure traverse lines simultaneously, and compared with adopting the wheatstone bridge of trilinear method, each sensor uses a wire less.

Setting reference resistance resistance is just in time identical with strain gage resistance, (smart coat sensor model number is more, and does not have uniform resistance value, therefore inapplicable the method), obtain 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:

ΔR g R g = ( V g - V ref ) R ref V ref R g = Kϵ Kϵ = ΔR g R g = V g - V ref V ref - - - ( 4 )

In formula (4), K is resistance strain gauge sensitivity coefficient, and ε is strain.

Same, the observed reading of smart coat sensor can be obtained:

ΔR i + R i = R ref V i V ref - - - ( 5 )

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), two kinds of sensor series can be measured by current-series metering circuit in same current return.

The resistance being generally used for the strain gage of structural strain course monitoring is 350 Ω, and the resistance of smart coat sensor is generally about 0.3 Ω, the constant current produced when constant current source flows through strain gage in series loop and smart coat sensor by measurement series loop, the voltage produced at strain gage and smart coat sensor two ends is the difference of the order of magnitude, according to this feature, the present embodiment additionally 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 and provide module), constant current source module and pressure reduction amplification module composition, 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 portions, pressure reduction amplification module adopts the extraction of two-stage instrument amplifier realization to sensor signal, adaptive measuring circuit is according to the pressure drop size automatic decision sensor type at sensor two ends, again according to the signal amplification factor of the type adjustment pressure reduction amplification module of each sensor.

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, the physical significance of each resistance and identical in Fig. 2, 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 build for core with ARM embedded platform, adopts the adaptive measuring circuit of the strain gage shown in above-mentioned Fig. 3 and smart coat sensor.LAN(LocalAreaNetwork, 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 on aircraft volt direct current (DC) (VDC) source, adopts 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 calculating corresponding smart coat sensor or the change in resistance value of strain gage according to the magnitude of voltage of record; Alarm module, during for being greater than corresponding threshold value when the change in resistance value of the smart coat sensor that device change in resistance computing module calculates or strain gage, reports to the police.

The connection diagram of sensor in the monitoring system of aircraft structure fatigue part shown in Figure 5.This figure needs installation 4 smart coat sensors and 2 strains to count example with the structural health monitoring of a certain seat of fatigue of aircraft to be described.Wherein, heavy line represents current return, and fine line represents measures lead-in wire, and little rectangular box represents strain gage, ellipse representation smart coat sensor, and dashed region is damage field.After these 6 sensors are mounted on body structure surface according to technological requirement, be connected with measurement mechanism by the mode of series connection.The order of 6 sensor series does not affect result of a measurement, and measurement mechanism is after powering by automatic distinguishing strain gage and smart coat sensor.For strain gage, measurement mechanism by according to 320Hz frequency collection and record data; For smart coat sensor, measurement mechanism by according to 1Hz frequency collection and record data.If smart coat sensor detects Crack Damage, measurement mechanism will be reported to the police.

The system that above embodiment provides, can use a kind of device (i.e. measurement mechanism) and a set of measurement cable to monitor the strain signal of aircraft structure fatigue key position and Crack Damage signal simultaneously.In the structure control region that sensor is relatively concentrated, the quantity measuring lead-in wire can be reduced, and be correlated with in strain monitoring system or smart coat monitoring system, often increasing a sensor needs three lead-in wires, and the system of above-described embodiment often increases a sensor only needs increase by two lead-in wire.

Said system, except the strain history record of outfield aircraft structure fatigue key position and Crack Damage monitoring, 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 of the present invention each module or each step can realize with general computer device, they can concentrate on single computer device, or be distributed on network that multiple computer device forms, alternatively, they can realize with the executable program code of computer device, thus, they can be stored and be performed by computer device in the storage device, or they are made into each integrated circuit modules respectively, or the multiple module in them or step are made into single integrated circuit module to realize.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 amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.

Claims (6)

1. a monitoring system for aircraft structure fatigue part, is characterized in that, comprising:
Be mounted on smart coat sensor and the strain gage on fatigue part surface, the number of described smart coat sensor and the number of described strain gage set according to the monitoring requirements of described fatigue part; Smart coat sensor described in each and strain gage described in each are connected successively;
The measurement mechanism be 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 gather described smart coat sensor and described strain gage magnitude of voltage separately for electricity is rear on the system, smart coat sensor and described strain gage according to the described magnitude of voltage identification gathered, according to the magnitude of voltage of recognition result record smart coat sensor described in each and described strain gage, and generate the monitoring result of described fatigue part according to the described magnitude of voltage of record;
Described measurement mechanism comprises:
The constant current source module of current return is formed and power supply provides module with described smart coat sensor and described strain gage;
To go between the pressure reduction amplification module be connected with each described smart coat sensor and the measurement at described strain gage two ends, for amplifying the described pressure reduction measured between lead-in wire according to the magnification factor arranged;
Each described pressure reduction amplification module is connected with a data acquisition module, for gathering the data that described pressure reduction amplification module exports according to the frequency acquisition arranged; Wherein, the initial magnification factor of described pressure reduction amplification module is 1.
2. system according to claim 1, is characterized in that, described measurement mechanism also comprises:
Data recordin module, for recording the data of described data collecting module collected;
Device recognition module, for after electricity on the 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 described in each and described strain gage;
Pressure reduction amplifies control module, for arranging the magnification factor of described pressure reduction amplification module and the frequency acquisition of described data acquisition module 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 eliminates the surge of current of described constant current source module to the impact of survey precision automatically by the voltage gathering described reference resistance two ends.
5. system according to claim 1, is characterized in that, described measurement mechanism also comprises:
Device change in resistance computing module, for calculating corresponding described smart coat sensor or the change in resistance value of described strain gage according to the described magnitude of voltage of record;
Alarm module, during for being greater than corresponding threshold value when the change in resistance value of the described smart coat sensor that described device change in resistance computing module calculates 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 volt direct supply of 28 on described aircraft; Aircraft is when ground, and described measurement mechanism is connected with 28 volts of direct supplys on ground.
CN201310693825.1A 2013-12-17 2013-12-17 The monitoring system of aircraft structure fatigue part CN103640713B (en)

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