CN109911245A - A kind of the fatigue part monitoring system and its monitoring method of Flight Vehicle Structure - Google Patents
A kind of the fatigue part monitoring system and its monitoring method of Flight Vehicle Structure Download PDFInfo
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- CN109911245A CN109911245A CN201910174884.5A CN201910174884A CN109911245A CN 109911245 A CN109911245 A CN 109911245A CN 201910174884 A CN201910174884 A CN 201910174884A CN 109911245 A CN109911245 A CN 109911245A
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Abstract
It include power supply module, multiple strain gauges, multiple strain measuring devices and a data processing equipment the invention discloses a kind of fatigue part of Flight Vehicle Structure monitoring system and its monitoring method, the system；The power supply module provides power supply by two power supply lines for the strain measuring device and data processing unit；The strain measuring device is electrically connected multiple strain gauges, and the strain value of monitored fatigue part is acquired using strain gauge；The data processing equipment, for passing through wire communication or/and communication, the data that strain measuring device is sent described in aggregation process form the diagnostic result to strain gauge real value by pretreatment.Extensive strain measuring device communication network can be constituted, comprehensive monitoring is carried out to the structure member Crack Damage situation of aircraft in real time by the way that multiple strain gauges are attached and are communicated using the present invention.
Description
Technical field
The present invention relates to material crack detection technique more particularly to a kind of fatigue part of Flight Vehicle Structure monitoring system and
Its monitoring method.
Background technique
The structure member of aircraft, service phase after a period of use, Crack Damage phenomenon can be gradually appeared and influenced
Flight safety.
The Crack Damage situation of aircraft structural component is monitored at present, the measure generally used is in structural portion
Near part, strain gauge is pasted and installed according to certain way cloth, using strain measuring device interrecord structure component in use of being on active service
In strain history, corresponding data result is then obtained by LOAD FOR, finally using data result to aircaft configuration portion
The fatigue conditions of part carry out quantitative analysis.
But in above-mentioned monitoring method, each strain measuring device is required to two power supply lines, two communication
Signal wire connection.For Large Scale Space Vehicle, since its structure member is very more, the strain measuring device number that needs to use
Measure it is also very more, it is therefore desirable to power supply line, signal wire quantity in multiple growth.But aircraft by space and weight with
And the limitation of safety requirements, do not allow in many cases using more power supply lines and signal wire.Therefore, it is difficult to simultaneously using multiple
Strain measuring device is in real time monitored the structure member Crack Damage situation of aircraft.
Summary of the invention
In view of this, the main purpose of the present invention is to provide a kind of fatigue part of Flight Vehicle Structure monitoring system and its
Monitoring method, it is intended to by the way that multiple strain gauges are attached and are communicated, the extensive strain measuring device communication network of composition,
So as to carry out comprehensive monitoring to the structure member Crack Damage situation of aircraft in real time.
Another object of the present invention is to provide a kind of lotuses of fatigue part monitoring system using the Flight Vehicle Structure
Calculating control system is carried, the ess-strain situation of strain gauge is obtained by strain measuring device, according to ess-strain numerical value meter
The fatigue part institute for calculating structure is loaded.
In order to achieve the above objectives, the technical scheme of the present invention is realized as follows:
A kind of fatigue part monitoring system of Flight Vehicle Structure, including power supply module, further include multiple strain gauges, multiple strain gauges
Measuring device and a data processing equipment；
The power supply module provides power supply by two power supply lines for the strain measuring device and data processing unit；
The strain measuring device is electrically connected multiple strain gauges, and the strain of monitored fatigue part is acquired using strain gauge
Numerical value；
The data processing equipment, for passing through wire communication or/and communication, the measurement of strain gauge described in aggregation process
The data that device is sent form the diagnostic result to strain gauge real value by pretreatment.
Wherein, the data processing equipment has with multiple strain measuring devices by the signal wire realization of 2 CAN bus
Line communication.
The data processing equipment and multiple strain measuring devices are realized wireless by wireless radio frequency discrimination RFID technology
Communication.
The multiple strain gauge is at least 2.The multiple strain measuring device is at least 2.
The strain measuring device, including the first power module, the first CAN interface, the first RFID interface, first
Memory module, the first CPU, the first data processing module and modulus A/D conversion module；Wherein,
First power module, is electrically connected with power supply module, is the modules of the strain measuring device by voltage transformation
And coupled strain gauge power supply；
A/D conversion module, for connecting the strain gauge, the analog signal that strain gauge is monitored is converted to digital signal；
First data processing module will pass through the real time value of the strain gauge after A/D conversion module under the instruction of the first CPU
Data summarization after conversion gets up, rejecting abnormalities data value, then by the strain gauge real time value of each channel reception, according to certain
Format composition data packet, data processing equipment is sent to by the first CAN interface or the first RFID interface；
First memory module, for storing the collected real time value of strain gauge.
The data processing equipment, including second power supply module, device interface module, the second CAN interface, second
RFID interface, the second memory module, the 2nd CPU and the second data processing module；
Second power supply module is electrically connected with power supply module, is supplied by the modules that voltage transformation is the data processing module
Electricity；
Second CAN interface, for carrying out data exchange with the first CAN interface of strain measuring device；
Second RFID interface, for carrying out data exchange with the first RFID interface of strain measuring device；
Second data processing module, under the instruction of the 2nd CPU, the data of each strain measuring device of aggregation process are passed through
Certain process flow forms the diagnostic result to strain gauge real time value, and diagnostic result is stored in described second in real time
In memory module.
Device interface module calculates control for connecting load specially with the memory interface of external equipment or communication interface
Device processed.
A kind of load calculating control system of the fatigue part monitoring system using the Flight Vehicle Structure, including be equipped with
Load calculates program module, is configured to the real time value of strain gauge, calculates strain field, according to the variation of strain field,
Calculate load suffered by structure.
A kind of fatigue part monitoring method of Flight Vehicle Structure, includes the following steps:
A, power supply is provided for data processing equipment and strain measuring device by two power supply lines using power supply module；
B, multiple strain gauges are electrically connected by straining measuring device, acquire answering for monitored fatigue part using strain gauge
Variable value；
C, wire communication or/and communication, the measurement dress of strain gauge described in aggregation process are utilized by data processing equipment
The data sent are set, by pretreatment, form the diagnostic result to strain gauge real value.
Wherein, wire communication or/and communication are utilized by data processing equipment described in step C, it is described wired
Communication mode are as follows: realized using data processing equipment and multiple strain measuring devices by the signal wire of 2 CAN bus；Institute
State communication are as follows: pass through wireless radio frequency discrimination RFID technology using data processing equipment and multiple strain measuring devices
It realizes.
The fatigue part monitoring system and its monitoring method of Flight Vehicle Structure of the invention, have the following beneficial effects:
Using the present invention, the quantity of power supply line in the monitoring system, signal wire can be greatly simplified, thus to utilize strain
Meter carries out large-scale network-estabilishing and has established technical foundation using its situation of change for monitoring the fatigue part of Flight Vehicle Structure.Especially
The signal wire of communication is eliminated by using RFID technique using wireless networking mode, Wireline can be further reduced
Usage quantity and reduce actual use in wiring condition limitation so that using its carry out Large Scale Space Vehicle structure tired portion
Part monitors be possibly realized simultaneously.
Detailed description of the invention
Fig. 1 is that the fatigue part of one of embodiment of the present invention Flight Vehicle Structure monitors the extensive strain gauge networking knot of system
Structure block diagram；
Fig. 2 is that the fatigue part of two Flight Vehicle Structures of the embodiment of the present invention monitors the extensive Strain Meter Set web frame frame of system
Figure；
Fig. 3 is the functional schematic that the embodiment of the present invention strains measuring device；
Fig. 4 is the functional schematic of data processing equipment of the embodiment of the present invention；
Fig. 5 is to calculate fatigue part load according to ess-strain situation using fatigue part of the present invention monitoring system
System schematic.
Specific embodiment
With reference to the accompanying drawing and the embodiment of the present invention to the fatigue part of Flight Vehicle Structure of the present invention monitor system and its
Monitoring method is described in further detail.
Fig. 1 is that the fatigue part of one of embodiment of the present invention Flight Vehicle Structure monitors the extensive strain gauge networking knot of system
Structure block diagram.
As shown in Figure 1, in the embodiment one, using wired communication mode to strain gauge, strain measuring device sum number
Networking is carried out according to processing unit.Specific networking mode is as follows:
Using 2 power supply lines to strain measuring device 1, strain measuring device 2 ..., strain measuring device n and number
It is powered according to processing unit.Wherein one is power supply line, and another is ground wire.Using power supply module, pass through 2 power supplys
Line is data processing module and all strain measuring device power supplies.Each strain measuring device, is electrically connected several
Strain gauge, i.e. strain gauge 1, strain gauge 2 ..., strain gauge n.
In example 1, each strain measuring device (referring to Fig. 3) and data processing equipment (with reference to Fig. 4) it
Between, data exchange is carried out by the communication mode of CAN bus.
The CAN bus of data processing equipment can be communicated with multiple strain measuring devices simultaneously.Data processing dress
Two CAN bus of the CAN interface institute band set are connected with the CAN interface of all strain measuring devices.
The CAN interface of data processing equipment is answered by CAN bus with each as main control unit, according to preset sequence
The CAN interface for becoming meter detection device carries out data exchange.The data processing equipment is attached thereto by CAN interface reading
Strain measuring device in stored, the strain value of structure member that is measured by strain gauge, each answered to realize
Become the data exchange of measuring device and data processing equipment.
Fig. 2 is that the fatigue part of two Flight Vehicle Structures of the embodiment of the present invention monitors the extensive strain gauge networking knot of system
Structure block diagram.
As shown in Fig. 2, in the embodiment two, using communication to strain gauge, strain measuring device sum number
Networking is carried out according to processing unit.Specific networking mode is as follows:
Still use 2 power supply lines to strain measuring device 1, strain measuring device 2 ..., strain measuring device n with
And data processing equipment is powered.Wherein one is power supply line, and another is ground wire.Using power supply module, pass through described 2
Power supply line is data processing module and all strain measuring device power supplies.Each strain measuring device, is electrically connected
Several strain gauges, i.e. strain gauge 1, strain gauge 2 ..., strain gauge n.
In the embodiment two, each strain measuring device (referring to Fig. 3) and data processing equipment (with reference to Fig. 4) it
Between, mode carries out data exchange by wireless communication.For example, radio frequency identification (Radio Frequency can be used
Identification, RFID) technology carries out data exchange between all strain measuring devices and data processing unit.
Each strain measuring device is equipped with a RFID interface (referring to Fig. 3), connects RFID label tag, each RFID
Label has unique electronic code.
By the RFID interface (referring to Fig. 4) of the data processing equipment, RFID reader is connected.RFID reader is set
It is carried out wireless communication according to preset sequence with RFID label tag described in each for main control unit, reads the strain being attached thereto
The strain value of structure member being stored in measuring device, by strain measurement, to realize each strain gauge measurement
The data exchange of device and data processing equipment.
One, embodiment two through the foregoing embodiment can greatly simplify power supply line, signal wire among the monitoring system
Quantity, thus for using strain gauge carry out large-scale network-estabilishing using its monitor Flight Vehicle Structure fatigue part situation of change
Technical foundation is established.It eliminates communication by using RFID technique in particular by the wireless networking mode of embodiment two and uses
Signal wire, can be further reduced Wireline usage quantity and reduce actual use in wiring condition limitation so that
It monitors and is possibly realized simultaneously using its fatigue part for carrying out Large Scale Space Vehicle structure.
In above-described embodiment one, embodiment two, using the wired communication mode of CAN bus and using the wireless of RFID mode
Communication mode, data exchange ways can be identical.For example, data processing equipment can be set to master control, successively poll is each answered
Become measuring device, when be polled to some strain measuring device when, data processing equipment just with the strain measuring device into
Row data exchange.
The data frame format of its data exchange specifically includes that packet header+strain gauge number+data content.The packet header can be with
Sets itself, such as 0xFA.
The number of strain measuring device must unify setting in advance, and each strain measuring device is made to have unique volume
Number.The real-time strain data (numerical value) that data content, mainly strain gauge measurement obtain.
Fig. 3 is the functional schematic that the embodiment of the present invention strains measuring device.The strain measuring device, it is main to use
Real time data is sent to data processing equipment by certain processing in the real time data (numerical value) for acquiring each strain gauge.
Each strain measuring device, can connect multiple strain gauges.
As shown in figure 3, the strain measuring device further includes including the first power module being connected with power supply module
One CAN interface, the first RFID interface, the first memory module, the first CPU, the first data processing module and modulus (A/D)
Conversion module.
First power module, is connected with power supply module, is each of the strain measuring device by voltage transformation
A module and the power supply of coupled strain gauge.
Modulus (A/D) conversion module, for connecting the strain gauge, the analog signal that strain gauge is monitored is converted
For digital signal.Measuring device is strained by the changing value of real-time acquisition strain gauge, illegal value is filtered out first, then will own
Strain gauge numerical value, a data packet is broken into, by first CAN interface or the first RFID interface real-time Transmission to number
According to processing unit.
First data processing module will pass through the strain gauge after A/D conversion module under the instruction of the first CPU
Data summarization after real time value conversion gets up, rejecting abnormalities data value, then by the strain gauge real time value of each channel reception,
According to certain format composition data packet, data processing dress is sent to by the first CAN interface or the first RFID interface
It sets.
First memory module, for storing the collected real time value of strain gauge.
Here, first CAN interface is counted for the second CAN interface with data processing equipment
According to exchange.First RFID interface, for carrying out data exchange with the second RFID interface of data processing equipment.It was actually using
Any one of Cheng Zhong, this wire communication can be used, wirelessly communicate both modes, it can also make simultaneously in two ways
With.First CPU, the main control module as strain measuring device, in embodiments of the present invention, using STM32
Chip is realized.
Fig. 4 is the functional schematic of data processing equipment of the embodiment of the present invention.The data processing equipment is mainly used for leading to
Cross the second CAN interface or the second RFID interface, the data that each strain measuring device of aggregation process is sent, by pre-
If process flow, formed to the diagnostic result of strain gauge real value, real-time storage diagnostic result.When real value is greater than given threshold
When value, real-time alerting information is provided.
As shown in figure 4, the data processing equipment, including second power supply module, device interface module, the second CAN bus connect
Mouth, the second RFID interface, the second memory module, the 2nd CPU and the second data processing module.
The second power supply module, is connected with power supply module, is each of the data processing module by voltage transformation
Module for power supply.
Second CAN interface, for carrying out data friendship with the first CAN interface of strain measuring device
It changes；Second RFID interface, for carrying out data exchange with the first RFID interface of strain measuring device.In the process used
In, can be used this wired or wireless communication mode both any one of, can also use simultaneously in two ways.
2nd CPU, the main control module as the data processing equipment, in embodiments of the present invention, using ARM core
Piece.
Second data processing module, under the instruction of the 2nd CPU, the number of each strain measuring device of aggregation process
According to forming the diagnostic result to strain gauge real time value, and diagnostic result is stored in institute in real time by certain process flow
It states in the second memory module.
The device interface module can be used for connecting load specially with the memory interface of external equipment or communication interface
Calculation control device.For example, the load calculation control device, can be one and is equipped with relevant software programs module, set
It sets for the real-value by strain gauge, calculates strain field, according to the variation of strain field, calculate load suffered by structure.
Fig. 5 monitors system for application fatigue part of the present invention and calculates fatigue part institute load-bearing according to ess-strain situation
The system schematic of load.
The load calculating control system, including strain measuring device, several strains being connected with strain measuring device
Meter, data processing equipment and load calculation control device.
As shown in figure 5, to pass through a certain number of strains of laying on aluminium alloy (aircraft) spar using the system
Meter is obtained the ess-strain situation of strain gauge by strain measuring device, the fatigue of structure is calculated according to ess-strain numerical value
Component embodiment loaded.
According to the analysis of the spar to aircraft wing, the mainly effect by three kinds of load of the spar of aircraft wing, difference
It is moment of flexure, shearing and torque.In the case where aircraft flight, the spar of wing will be simultaneously by moment of flexure, shearing and three kinds of torque
The collective effect of load.In the upper surface of aluminum alloy spar, multiple strain gauges are laid in respectively apart from aluminum alloy spar center
(Fig. 5 is referred to) at the different location of axis, as different measurement points.Can also be at the side surface of aluminum alloy spar, it will be multiple
Strain gauge is laid in respectively at the central axes of aluminum alloy spar, this position is from the short transverse of aluminum alloy spar by aluminum alloy spar
Two parts are bisected into, equally as different measurement points (figure omits).
The fiber grating right angle that we are attached to aluminum alloy spar upper surface to cloth, which should change, to be analyzed:
When loading pure torsional load on aluminum alloy spar, the strain gauge in only 45 ° directions has good linear relationship.
When loading curved scissors load, through analyzing it is found that the strain gauge in only 0 ° direction has in the presence of only pure shear
The strain gauge of good linear relationship, 45 ° of directions has weak line sexual intercourse.
When loading pure bending load, there is the strain gauge in 0 ° and 90 ° direction that there is good linear relationship.Thus, it can be known that
In loaded load on aluminum alloy spar, there is mutually independent relationship between the strain gauge and bending and twisting load of different directions,
The common load of bending and twisting load be can use to establish strain and load relation matrix.
The strain and load relation matrix established according to test data are as follows:
In above formula, parameter M represents moment of flexure, and square is cut in Q representative, and T represents torque.
Above-mentioned strain and load relation matrix, suitable under aluminum alloy spar size designed by test of the embodiment of the present invention
The structure static load in structural elasticity deformation range monitoring, and in the normal flight of aircraft, the deformation of wing is all tieed up
It holds in the range of flexible deformation.On the engineer application of aircraft wing spar, for the spar of different structure size, need by
According to the experimental method of the embodiment of the present invention, load is outer on practical spar is loaded into row rating test, determines form of the same race, but coefficient
Different loading matrixs.
The foregoing is only a preferred embodiment of the present invention, is not intended to limit the scope of the present invention.
Claims (10)
1. a kind of fatigue part of Flight Vehicle Structure monitors system, including power supply module, which is characterized in that further include multiple strains
Meter, multiple strain measuring devices and a data processing equipment；
The power supply module provides power supply by two power supply lines for the strain measuring device and data processing unit；
The strain measuring device is electrically connected multiple strain gauges, and the strain of monitored fatigue part is acquired using strain gauge
Numerical value；
The data processing equipment, for passing through wire communication or/and communication, the measurement of strain gauge described in aggregation process
The data that device is sent form the diagnostic result to strain gauge real value by pretreatment.
2. the fatigue part of Flight Vehicle Structure monitors system according to claim 1, which is characterized in that the data processing dress
It sets and wire communication is realized by the signal wire of 2 CAN bus with multiple strain measuring devices.
3. the fatigue part of Flight Vehicle Structure monitors system according to claim 1, which is characterized in that the data processing dress
It sets and wireless communication is realized by wireless radio frequency discrimination RFID technology with multiple strain measuring devices.
4. the fatigue part of Flight Vehicle Structure monitors system according to claim 1, which is characterized in that the multiple strain gauge
At least 2.
5. the fatigue part of any Flight Vehicle Structure monitors system according to claim 1~3, which is characterized in that described more
A strain measuring device is at least 2.
6. the fatigue part of Flight Vehicle Structure monitors system according to claim 1, which is characterized in that the strain gauge measurement
Device, including the first power module, the first CAN interface, the first RFID interface, the first memory module, the first CPU, first
Data processing module and modulus A/D conversion module；Wherein,
First power module, is electrically connected with power supply module, is the modules of the strain measuring device by voltage transformation
And coupled strain gauge power supply；
A/D conversion module, for connecting the strain gauge, the analog signal that strain gauge is monitored is converted to digital signal；
First data processing module will pass through the real time value of the strain gauge after A/D conversion module under the instruction of the first CPU
Data summarization after conversion gets up, rejecting abnormalities data value, then by the strain gauge real time value of each channel reception, according to certain
Format composition data packet, data processing equipment is sent to by the first CAN interface or the first RFID interface；
First memory module, for storing the collected real time value of strain gauge.
7. the fatigue part of Flight Vehicle Structure monitors system according to claim 1, which is characterized in that the data processing dress
It sets, including second power supply module, device interface module, the second CAN interface, the second RFID interface, the second memory module,
Two CPU and the second data processing module；
Second power supply module is electrically connected with power supply module, is supplied by the modules that voltage transformation is the data processing module
Electricity；
Second CAN interface, for carrying out data exchange with the first CAN interface of strain measuring device；
Second RFID interface, for carrying out data exchange with the first RFID interface of strain measuring device；
Second data processing module, under the instruction of the 2nd CPU, the data of each strain measuring device of aggregation process are passed through
Certain process flow forms the diagnostic result to strain gauge real time value, and diagnostic result is stored in described second in real time
In memory module；
Device interface module calculates control dress for connecting load specially with the memory interface of external equipment or communication interface
It sets.
8. a kind of load of the fatigue part monitoring system including any Flight Vehicle Structure of claim 1~7 calculates control
System, which is characterized in that further include that load is installed to calculate program module, is configured to the real time value of strain gauge,
Strain field is calculated, according to the variation of strain field, calculates load suffered by structure.
9. a kind of fatigue part monitoring method of Flight Vehicle Structure, which comprises the steps of:
A, power supply is provided for data processing equipment and strain measuring device by two power supply lines using power supply module；
B, multiple strain gauges are electrically connected by straining measuring device, acquire answering for monitored fatigue part using strain gauge
Variable value；
C, wire communication or/and communication, the measurement dress of strain gauge described in aggregation process are utilized by data processing equipment
The data sent are set, by pretreatment, form the diagnostic result to strain gauge real value.
10. the fatigue part monitoring method of Flight Vehicle Structure according to claim 9, which is characterized in that pass through described in step C
Data processing equipment utilizes wire communication or/and communication, the wired communication mode are as follows: utilizes data processing equipment
It is realized with multiple strain measuring devices by the signal wire of 2 CAN bus；The communication are as follows: using at data
Reason device is realized with multiple strain measuring devices by wireless radio frequency discrimination RFID technology.
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| CN112254769A (en) * | 2020-10-22 | 2021-01-22 | 北京卫星环境工程研究所 | Multifunctional health monitoring system and method for spacecraft structure |
| CN112345217A (en) * | 2020-10-07 | 2021-02-09 | 大连理工大学 | Intelligent health monitoring system for residual fatigue life of key part of airplane |
| CN112660417A (en) * | 2020-12-25 | 2021-04-16 | 湖南航天机电设备与特种材料研究所 | Structural damage diagnosis method and system for aircraft structural component |
| CN112763345A (en) * | 2020-12-24 | 2021-05-07 | 中国飞行试验研究院 | Loading test method for airplane airfoil surface load calibration area |
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Application publication date: 20190621 |