CN103760226A - Non-destructive detection method of spacecraft - Google Patents
Non-destructive detection method of spacecraft Download PDFInfo
- Publication number
- CN103760226A CN103760226A CN201310714258.3A CN201310714258A CN103760226A CN 103760226 A CN103760226 A CN 103760226A CN 201310714258 A CN201310714258 A CN 201310714258A CN 103760226 A CN103760226 A CN 103760226A
- Authority
- CN
- China
- Prior art keywords
- spacecraft
- signal
- detected
- destructive testing
- testing 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.)
- Pending
Links
Images
Landscapes
- Investigating Or Analyzing Materials By The Use Of Magnetic Means (AREA)
Abstract
The invention provides a non-destructive detection method of a spacecraft. The non-destructive detection method comprises the following steps of putting a non-destructive detecting sensor to a part to be detected of the spacecraft, and providing square-wave pulse electric current for an excitation mechanism in the non-destructive detecting sensor to generate a vortex magnetic field at the part to be detected of the spacecraft; detecting the variation condition of the vortex magnetic field of the part to be detected through a tunnel magnetoresistor in the non-destructive detecting sensor, and outputting a detection signal; and carrying out corresponding treatment on the detection signal, and analyzing the damage condition of the part to be detected according to a processing analysis result. According to the invention, the highly sensitive tunnel magnetoresistor as a detecting element, and the vortex magnetic field is generated at the part to be detected by using the square-wave pulse current excitation mechanism, and can permeate in the material, so that the non-destructive detection method of the spacecraft provided by the invention can achieve large detection depth and high detection sensitivity.
Description
Technical field
The present invention relates to spationautics field, relate in particular to a kind of spacecraft lossless detection method.
Background technology
For the long-life, the development trend of highly reliable spacecraft and demand, current vortex Dynamic Non-Destruction Measurement is the effective means that is applicable to spacecraft Non-Destructive Testing, current vortex non-destructive control probe is to using coil as detecting element, according to the deep zone defect of the detected material internal of variation identification of the magnetic flux through coil, while only having the excitation frequency of coil lower, the deep zone defect of detected material internal just can be detected, according to the law of electromagnetic induction, coil-induced electromotive force is relevant with rate of change of magnetic, in order to improve the sensitivity of probe, only has the size that increases coil, this just causes the spatial resolution of coil to reduce and a certain degree of depth minimum detectable flaw size increases, therefore conventional current vortex non-destructive control probe cannot be taken into account and detect the degree of depth and detection sensitivity.
Summary of the invention
Provide hereinafter about brief overview of the present invention, to the basic comprehension about some aspect of the present invention is provided.Should be appreciated that this general introduction is not about exhaustive general introduction of the present invention.It is not that intention is determined key of the present invention or pith, and nor is it intended to limit the scope of the present invention.Its object is only that the form of simplifying provides some concept, usings this as the preorder in greater detail of discussing after a while.
The invention provides a kind of spacecraft lossless detection method, comprising:
Non-Destructive Testing sensor is placed on to spacecraft position to be detected;
For providing square wave pulsed current, the excitation mechanism in Non-Destructive Testing sensor produces eddy current magnetism with the position to be detected at spacecraft;
By the tunnel magnetoresistance in Non-Destructive Testing sensor, detect the situation of change of the eddy current magnetism at described position to be detected, and output detection signal;
Described detection signal is carried out to respective handling, according to result, analyze the degree of impairment at described position to be detected.
Spacecraft lossless detection method provided by the invention, adopt highly sensitive tunnel magnetoresistance as detecting element, utilize square wave pulsed current excitation mechanism to produce eddy current magnetism at position to be detected, this eddy current magnetism is permeable to material internal, and therefore spacecraft lossless detection method provided by the invention can be taken into account and detect the degree of depth and detection sensitivity.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present invention or technical scheme of the prior art, to the accompanying drawing of required use in embodiment or description of the Prior Art be briefly described below, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skills, do not paying under the prerequisite of creative work, can also obtain according to these accompanying drawings other accompanying drawing.
Fig. 1 is the structural representation of a kind of embodiment of spacecraft Non-Destructive Testing sensor provided by the invention.
Fig. 2 is the structural representation of a kind of embodiment of spacecraft nondestructive detection system provided by the invention.
Fig. 3 is the process flow diagram of a kind of embodiment of spacecraft lossless detection method provided by the invention.
Fig. 4 is the schematic diagram in spacecraft lossless detection method provided by the invention, reference block being detected.
Fig. 5 detects to reference block the signal curve schematic diagram obtaining in spacecraft lossless detection method provided by the invention.
Fig. 6 is the curve synoptic diagram in spacecraft lossless detection method provided by the invention, multilayer board being detected.
Embodiment
For making object, technical scheme and the advantage of the embodiment of the present invention clearer, below in conjunction with the accompanying drawing in the embodiment of the present invention, technical scheme in the embodiment of the present invention is clearly and completely described, obviously, described embodiment is the present invention's part embodiment, rather than whole embodiment.The element of describing in an accompanying drawing of the present invention or a kind of embodiment and feature can combine with element and feature shown in one or more other accompanying drawing or embodiment.It should be noted that for purposes of clarity, in accompanying drawing and explanation, omitted expression and the description of unrelated to the invention, parts known to persons of ordinary skill in the art and processing.Embodiment based in the present invention, the every other embodiment that those of ordinary skills obtain under the prerequisite of not paying creative work, belongs to the scope of protection of the invention.
Embodiment mono-
With reference to figure 1, the present embodiment provides a kind of spacecraft Non-Destructive Testing sensor, comprising:
The position to be detected of spacecraft adopts metal material to make, excitation mechanism 101 produces eddy current magnetism at the position to be detected at spacecraft under the effect of square wave pulsed current, because square-wave pulse has comprised abundant frequency content, can produce at position to be detected the eddy current magnetism of different frequency, the eddy current magnetism of different frequency is different to the length of penetration of detected material, when there is damage in the inside at detected position, when its eddy current of inducting is blocked by the defect of material internal at the circulation path of inside, detected position, the distribution of eddy current magnetism also changes, by tunnel magnetoresistance 102, detect this situation of change, can realize the damage check to this position, adopt square wave pulsed current to provide exciting current for excitation mechanism, can realize the detection of the different depth of inside, position to be detected, tunnel magnetoresistance has higher sensitivity simultaneously, therefore can improve the degree of depth of sensitivity and the detection of detection simultaneously.
The spacecraft Non-Destructive Testing sensor that the present embodiment provides is applicable to the Non-Destructive Testing of spacecraft when ground.
Particularly, excitation mechanism 101 comprises field coil 103 and the magnet that adopts high permeability materials to make, magnet comprises barrel-shaped magnetic conduction portion 104 and the magnetic cylinder 105 that is fixed on barrel-shaped magnetic conduction portion 104 inner bottom surface geometric center places, barrel-shaped magnetic conduction portion 104 is the cylindrical structure of an end opening, other end sealing, field coil 103 is wound on magnetic cylinder 105, and magnetic cylinder 105 is positioned at the end face of barrel-shaped magnetic conduction portion 104 openend directions and the end face of barrel-shaped magnetic conduction portion 104 openends in same plane.
The longitdinal cross-section diagram of the spacecraft Non-Destructive Testing sensor that Fig. 1 provides for the present embodiment, the longitdinal cross-section diagram of magnet is mountain font.
For field coil 103 provides square wave pulsed current, can produce at position to be detected the magnetic field of different frequency.
Particularly, magnetic cylinder 105 is hollow structure, and one end of tunnel magnetoresistance 102 is arranged in magnetic cylinder 105, and the end face of the other end and barrel-shaped magnetic conduction portion openend is in same plane.
By the surface laminating at the openend of barrel-shaped magnetic conduction portion 104 and position to be detected, tunnel magnetoresistance 102 can detect with the Surface Contact at position to be detected.
As a kind of optional embodiment, the Non-Destructive Testing sensor that the present embodiment provides also comprises the shield shell 106 suitable with barrel-shaped magnetic conduction portion 104, shield shell 106 is barrel shaped structure, be that shield shell 106 is the cylindrical structure of an end opening, other end sealing, described shield shell is arranged at the outside of barrel-shaped magnetic conduction portion 104, for excitation mechanism 101 being fixed and magnetic interference to external world shields, the end face of the openend of the end face of shield shell 106 openends and barrel-shaped magnetic conduction portion 104 is in same plane.
As a kind of optional embodiment, between shield shell 106 and barrel-shaped magnetic conduction portion 104, be also provided with insulation course 107, insulation course 107 is positioned at the end face of barrel-shaped magnetic conduction portion 104 openend directions and the end face of barrel-shaped magnetic conduction portion 104 openends in same plane.
As optional embodiment, shield shell 106 is provided with lead terminal 108, lead terminal 108 is arranged at the geometric center place of shield shell 106 bottom surfaces, for detection signal being exported to outside or extraneous square wave pulsed current being inputed to excitation mechanism 101.
Further, tunnel magnetoresistance 102 is connected with lead terminal 108 by the first lead-in wire 109, for exporting detection signal to outside; Excitation mechanism 101 is connected with lead terminal 108 by the second lead-in wire 110, for extraneous square wave pulsed current is inputed to excitation mechanism 101.
Particularly, on barrel-shaped magnetic conduction portion 104, insulation course 107, be correspondingly provided with and the corresponding through hole of this lead terminal 108, one end of the first lead-in wire 109 is connected with lead terminal 108, the other end is connected with tunnel magnetoresistance 102 through the through hole on barrel-shaped magnetic conduction portion 104, insulation course 107, one end of the second lead-in wire 110 is connected with the field coil 103 in excitation mechanism 101, the other end is connected with lead terminal 108, and lead terminal 108 is the input information/output terminal of Non-Destructive Testing sensor.
The beneficial effect of the spacecraft Non-Destructive Testing sensor that the present embodiment provides is:
1, overcome the shortcoming that Ultrasonic Nondestructive technology cannot for example, detect the conductor material of inner Presence of an interface (Multilayer Structure of spacecraft), and in use procedure, do not needed couplant;
2, with respect to magnetic Dynamic Non-Destruction Measurement, can only be applicable to ferrimagnet and detect, the kind of test material is more extensive, is applicable to any conductive material;
3,, with respect to infiltration Dynamic Non-Destruction Measurement, can carry out in situ detection to detected material;
4, with respect to ray Dynamic Non-Destruction Measurement, need the transmitting terminal of ray and the both sides that receiving end lays respectively at position to be detected, to installation site no requirement (NR), can carry out in situ detection;
5, relatively adopt coil as the traditional electrical nondestructive detecting technology of vortex of detecting element, adopt the square-wave pulse of certain dutycycle to encourage, power consumption is lower, can realize the detection to different depth defect, has avoided the mode of scanning;
6, adopt tunnel magnetoresistance as detecting element, magnetic field sensitivity and spatial resolution are higher, and sensitivity has nothing to do with changes of magnetic field, have realized the high resolution detection of deep zone defect, and power consumption is little.
Embodiment bis-
With reference to figure 2, the present embodiment provides a kind of spacecraft nondestructive detection system, comprising:
Non-Destructive Testing sensor 201;
The structure of Non-Destructive Testing sensor 201 and principle of work please refer to embodiment mono-, do not repeat them here.
Particularly, impulse source 202 is connected with the field coil in excitation mechanism, for field coil provides the square wave pulsed current of certain dutycycle, certain frequency and certain strength of current.
As a kind of optional embodiment, the detection system that the present embodiment provides also comprises the gear train 204 being connected with Non-Destructive Testing sensor 201, for controlling described Non-Destructive Testing sensor 201, on the surface at position to be detected, moves.
By gear train 204, control Non-Destructive Testing sensor 201 and move on the surface at position to be detected, can realize large-area automatic detection.
As a kind of optional embodiment, detection system also comprises the wave filter 205 being connected between tunnel magnetoresistance and data acquisition equipment 203, for described detection signal is carried out to filtering processing.
Process after filtering, can remove the burr signal in detection signal.
In addition, also comprise the amplifier being arranged between wave filter 205 and data acquisition equipment 203, for the detection signal after filtering is processed, amplify processing.
The spacecraft nondestructive detection system that the present embodiment provides, simple in structure, adopt highly sensitive tunnel magnetoresistance as detecting element, utilize square wave pulsed current excitation mechanism to produce eddy current magnetism at position to be detected, this eddy current magnetism is permeable to material internal, and therefore spacecraft Non-Destructive Testing sensor provided by the invention can be taken into account and detect the degree of depth and detect Ling Dumin.
Embodiment tri-
With reference to figure 3, the present embodiment provides a kind of spacecraft lossless detection method, comprising:
Step S301, is placed on spacecraft position to be detected by Non-Destructive Testing sensor;
Step S302, produces eddy current magnetism for the excitation mechanism in Non-Destructive Testing sensor provides square wave pulsed current with the position to be detected at spacecraft;
Step S303, the tunnel magnetoresistance by Non-Destructive Testing sensor detects the situation of change of the eddy current magnetism at described position to be detected, and output detection signal;
Step S304, carries out respective handling to described detection signal, analyzes the degree of impairment at described position to be detected according to result.
The spacecraft lossless detection method that the present embodiment provides is applicable to the detection of spacecraft when ground, during detection, Non-Destructive Testing sensor is placed on to the position to be detected of spacecraft, can to spacecraft, carry out the detection at a plurality of positions by manual mobile Non-Destructive Testing sensor, also can automatically on spacecraft, move and detect by transmission mechanism control Non-Destructive Testing sensor.
Degree of impairment comprises equivalent size and/or the depth of defect of position to be detected defect.
As a kind of optional embodiment, by the tunnel magnetoresistance in Non-Destructive Testing sensor, detect the situation of change of the eddy current magnetism at described position to be detected, and after output detection signal, also comprise:
Detection signal is carried out to filtering processing.
By filtering, process the burr elimination in detection signal.
As a kind of optional embodiment, detection signal is carried out also comprising after filtering processing:
Detection signal after filtering is processed amplifies processing.
Particularly, adopt impulse source to provide the square wave pulsed current of certain dutycycle, certain frequency and some strength for the field coil in excitation mechanism, tunnel magnetoresistance is connected with data acquisition equipment by lead-in wire, Non-Destructive Testing sensor is covered on to surface, position to be detected, tunnel magnetoresistance detects the situation of change of eddy current magnetism, and exporting detection signal to data acquisition equipment, data acquisition equipment carries out respective handling to detection signal and demarcation signal.
Detection signal is carried out to respective handling, according to result, analyzes the degree of impairment at described position to be detected, comprising:
Detection signal is compared from the demarcation signal of corresponding different degree of impairments in database, select the demarcation signal corresponding with described detection signal, according to the degree of impairment of setting up in advance and the mapping relations between demarcation signal, obtain the degree of impairment corresponding with described demarcation signal.
With reference to figure 4, the method that obtains demarcation signal comprises:
Reference signal and damage signal are carried out to difference processing, obtain the corresponding equivalent size of described known damage position and the demarcation signal of depth of defect.
Consider the individual difference of Non-Destructive Testing sensor, therefore before detecting, carry out calibrate, turn-on data collecting device, with reference to figure 4, Non-Destructive Testing sensor is positioned over to the not damaged position 306 of reference block 305, detect the eddy current magnetism of this position, the signal obtaining is as reference signal, and draw reference data and lack curve, Non-Destructive Testing sensor is being moved to the known damage position 307 of reference block 305, depth of defect and the equivalent size of this position are known, detect the eddy current magnetism of this position, the signal obtaining is as damage signal, and draw defective data curve, reference signal and damage signal are carried out to difference processing, the differential data obtaining is should the equivalent size of defective locations and the demarcation signal of depth of defect, draw this differential data curve, with reference to figure 5, the equivalent size of the corresponding known damage position 307 of amplitude Vp of differential data curve, the time T p that Vp is corresponding is the depth of defect of known damage position 307 in reference block, utilize the reference block of known different depth of defects and equivalent size to demarcate Non-Destructive Testing sensor, obtain the demarcation signal that different depth of defects and equivalent size are corresponding, demarcation signal to degree of impairment is stored, set up corresponding database.
The lossless detection method that the present embodiment provides, utilize constant current square-wave pulse to provide exciting current for excitation mechanism, square-wave pulse comprises abundant frequency content, the magnetic field that field coil is produced comprises abundant frequency spectrum, the length of penetration of different frequency magnetic field in detected position is different, its die-away time is also not identical, when the eddy current in different frequency magnetic field is blocked by the defect of inside, position to be detected at the circulation path of inside, position to be detected, the distribution of eddy current magnetism also changes, by tunnel magnetoresistance, detect the variation of eddy current magnetism, can obtain the degree of impairment of inside, position to be detected, and utilize Vp in testing result and Tp to treat the degree of impairment detecting in position and carry out qualitative description.
During Non-Destructive Testing sensor that the present embodiment provides, logical one rect.p. electric current periodically in field coil, the magnetic field that field coil produces generates eddy current in position to be detected, and the magnetic field that eddy current produces is received by tunnel magnetoresistance.If there is defect in position to be checked, the eddy current in position to be detected is blocked at the circulation path of inside, position to be detected, its magnetic field of inducting can change thereupon, so this magnetic field has comprised the abundant information about position to be detected internal injury, by tunnel magnetoresistance being detected to the analysis of data, can obtain the relevant information of conductor internal injury.
Induct in inside, the position to be detected skin depth (the theoretic degree of depth that detects) of eddy current of the eddy current magnetism of the generation of field coil is defined as:
In formula, δ represents skin depth, and unit is m; F indicating impulse frequency, unit is Hz; μ represents the conductor material magnetic permeability at position to be detected, and unit is H/m; σ represents conductor material conductivity, and unit is S/m.
According to the physical attribute of the conductive material at position to be detected (as conductivity and magnetic permeability) and testing requirement, (detect the degree of depth, minimum detectable flaw sizes etc.) (frequency is lower to determine the frequency of pulse, skin depth is darker), (dutycycle is less for dutycycle, pulse medium-high frequency composition is more, more be beneficial to the detection of surface imperfection, otherwise be beneficial to the detection of deep zone defect, but dutycycle is larger, power consumption also can rise thereupon, so this is the result of a compromise) and the strength of current (intensity of strength of current decision eddy current magnetism, electric current is larger, eddy current magnetism is stronger, but electric current is excessive, to circuit, detected conductor material may have a negative impact, so consider various influence factors).
Multilayer aluminum plate structure is the primary structure form of spacecraft, is also one of main application direction of current current vortex Non-Destructive Testing.Adopt the thick aluminium sheet simulated aircraft of multilayer 1mm stressed-skin construction, the identical break-through crackle of processing length different in width on an aluminium sheet therein, by adjust on it aluminium sheet number simulation different depth covering crack defect (as, on the defective aluminium sheet of processing, covering one deck aluminium sheet, is also that defect is positioned under the 1mm degree of depth).As shown in Figure 6, to utilize Non-Destructive Testing sensor that the present embodiment the provides testing result to 6mm long crack under 1-6mm, as can be seen from the figure along with the crack defect place degree of depth is darker, Vp is less for testing result amplitude, the corresponding time T p of Vp is larger, so can realize the qualitative description to crackle by Vp and the Tp value reading in testing result.
Be subject to Multilayer Structure effect of the interface, Ultrasonic Nondestructive technology cannot be carried out Non-Destructive Testing to Multilayer Structure, magnetic Dynamic Non-Destruction Measurement can only be for the Non-Destructive Testing of ferrimagnet (as iron, cobalt and alloy thereof), infiltration Dynamic Non-Destruction Measurement need to be by liquid media, and can only, for surface defects detection, cannot be used in the in situ detection of sandwich construction, ray Dynamic Non-Destruction Measurement can not be for the in situ detection of spacecraft Multilayer Structure, and has radiation, need to effectively protect, and can use, traditional electrical nondestructive detecting technology of vortex, adopt coil as detecting element, utilization is by the variation defect recognition of coil flux amount, it detects data curve plotting is butterfly diagram, interpreting blueprints needs the accumulation of very dark professional standing and experience, simultaneously, detect deep zone defect, need lower excitation frequency (obtaining large skin depth), according to Faraday's electromagnetic induction law, frequency is lower, the rate of change of the magnetic flux by coil is less, improve coil sensitivity, only has increase coil dimension, cause the flaw size of a certain degree of depth minimum detectable to increase, so traditional electrical nondestructive detecting technology of vortex, cannot take into account and detect the degree of depth and detection sensitivity.
To sum up, the lossless detection method that the present embodiment provides has following beneficial effect:
1) testing result is directly perceived, and data judging does not need the experience accumulation of professional knowledge collection, is conducive to applying of technology;
2) can detect darker defect, data reliability is good, Non-Destructive Testing problem that can fine solution Multilayer Structure, and this is the blind area of ultrasound examination;
3) adopt square-wave pulse to encourage, can realize the detection to different depth defect simultaneously, more easily realize the online imaging processing of Non-destructive Testing Data result, realize mechanization and the intellectuality of operation;
4) utilize tunnel magnetoresistance as detecting element, this sensor has ultra-small volume, and only to magnetic field magnitude, with changes of magnetic field frequency-independent, has overcome the shortcoming that traditional Dynamic Non-Destruction Measurement detection degree of depth and sensitivity cannot take into account;
5) detecting element tunnel magnetoresistance has ultra-small volume and power consumption, is easy to realize array design, realizes quick high accuracy and detects.
In the various embodiments described above of the present invention, the sequence number of embodiment is only convenient to describe, and does not represent the quality of embodiment.Description to each embodiment all emphasizes particularly on different fields, and there is no the part of detailed description in certain embodiment, can be referring to the associated description of other embodiment.
One of ordinary skill in the art will appreciate that: all or part of step that realizes said method embodiment can complete by the relevant hardware of programmed instruction, aforesaid program can be stored in a computer read/write memory medium, this program, when carrying out, is carried out the step that comprises said method embodiment; And aforesaid storage medium comprises: various media that can be program code stored such as ROM (read-only memory) (Read-Only Memory is called for short ROM), random access memory (Random Access Memory is called for short RAM), magnetic disc or CDs.
In the embodiment such as apparatus and method of the present invention, obviously, each parts or each step reconfigure after can decomposing, combine and/or decomposing.These decomposition and/or reconfigure and should be considered as equivalents of the present invention.Simultaneously, in the above in the description of the specific embodiment of the invention, the feature of describing and/or illustrating for a kind of embodiment can be used in same or similar mode in one or more other embodiment, combined with the feature in other embodiment, or substitute the feature in other embodiment.
Should emphasize, term " comprises/comprises " existence that refers to feature, key element, step or assembly while using herein, but does not get rid of the existence of one or more further feature, key element, step or assembly or add.
Finally it should be noted that: although described above the present invention and advantage thereof in detail, be to be understood that in the situation that do not exceed the spirit and scope of the present invention that limited by appended claim and can carry out various changes, alternative and conversion.And scope of the present invention is not limited only to the specific embodiment of the described process of instructions, equipment, means, method and step.One of ordinary skilled in the art will readily appreciate that from disclosure of the present invention, can use carry out with the essentially identical function of corresponding embodiment described herein or obtain process, equipment, means, method or step result essentially identical with it, that existing and will be developed future according to the present invention.Therefore, appended claim is intended to comprise such process, equipment, means, method or step in their scope.
Claims (7)
1. a spacecraft lossless detection method, is characterized in that, comprising:
Non-Destructive Testing sensor is placed on to spacecraft position to be detected;
For providing square wave pulsed current, the excitation mechanism in Non-Destructive Testing sensor produces eddy current magnetism with the position to be detected at spacecraft;
By the tunnel magnetoresistance in Non-Destructive Testing sensor, detect the situation of change of the eddy current magnetism at described position to be detected, and output detection signal;
Described detection signal is carried out to respective handling, according to result, analyze the degree of impairment at described position to be detected.
2. spacecraft lossless detection method according to claim 1, is characterized in that, described detection signal is carried out to respective handling, analyzes the degree of impairment at described position to be detected according to result, comprising:
Detection signal is compared from the demarcation signal of corresponding different degree of impairments in database, select the demarcation signal corresponding with described detection signal, according to the degree of impairment of setting up in advance and the mapping relations between demarcation signal, obtain the degree of impairment corresponding with described demarcation signal;
Described degree of impairment comprises equivalent size and/or depth of defect.
3. spacecraft lossless detection method according to claim 2, is characterized in that, the method that obtains described demarcation signal comprises:
Non-Destructive Testing sensor is positioned over to the not damaged position of reference block, and obtains reference signal by the tunnel magnetoresistance in Non-Destructive Testing sensor;
Non-Destructive Testing sensor is moved to the known damage position of reference block; And obtain damage signal by the tunnel magnetoresistance in Non-Destructive Testing sensor;
Reference signal and damage signal are carried out to difference processing, obtain the corresponding equivalent size of described known damage position and the demarcation signal of depth of defect.
4. spacecraft lossless detection method according to claim 3, is characterized in that, described reference signal and damage signal is carried out to difference processing, after obtaining the corresponding equivalent size of described known damage position and the demarcation signal of depth of defect, also comprises:
Reference block to different known damages detects, and sets up the database of the demarcation signal of corresponding different degree of impairments.
5. spacecraft lossless detection method according to claim 1, is characterized in that, the described situation of change that detects the eddy current magnetism at described position to be detected by the tunnel magnetoresistance in Non-Destructive Testing sensor, and after output detection signal, also comprise:
Described detection signal is carried out to filtering processing.
6. spacecraft lossless detection method according to claim 5, is characterized in that, after described detection signal is carried out to filtering processing, also comprises:
Detection signal after filtering is processed amplifies processing.
7. spacecraft lossless detection method according to claim 1, is characterized in that, described method also comprises:
Described tunnel magnetoresistance is arranged to the geometric center place of excitation mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310714258.3A CN103760226A (en) | 2013-12-20 | 2013-12-20 | Non-destructive detection method of spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310714258.3A CN103760226A (en) | 2013-12-20 | 2013-12-20 | Non-destructive detection method of spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103760226A true CN103760226A (en) | 2014-04-30 |
Family
ID=50527499
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310714258.3A Pending CN103760226A (en) | 2013-12-20 | 2013-12-20 | Non-destructive detection method of spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103760226A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106198722A (en) * | 2016-06-28 | 2016-12-07 | 天津因科新创科技有限公司 | The method and apparatus of Pulsed eddy current testing weld seam |
| CN109625317A (en) * | 2018-11-29 | 2019-04-16 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of detecting instrument having aircraft and engine component eddy current inspection function concurrently |
| CN116068044A (en) * | 2023-03-21 | 2023-05-05 | 辽宁锂想科技有限公司 | Multichannel multi-frequency weld joint flaw detection device |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6504363B1 (en) * | 2000-03-07 | 2003-01-07 | Teodor Dogaru | Sensor for eddy current testing and method of use thereof |
| US20040051525A1 (en) * | 2002-09-17 | 2004-03-18 | Siemens Westinghouse Power Corporation | Eddy current inspection probe |
| JP2009079984A (en) * | 2007-09-26 | 2009-04-16 | Hitachi Ltd | Eddy current inspection apparatus and method |
| CN201527411U (en) * | 2009-07-06 | 2010-07-14 | 李长青 | Two-dimensional low frequency pulse eddy current probe |
| CN102230914A (en) * | 2011-03-31 | 2011-11-02 | 厦门安锐捷电子科技有限公司 | Electromagnetic resonance-based nondestructive testing method for metal material |
| CN102549375A (en) * | 2009-09-21 | 2012-07-04 | 通用电气公司 | Eddy current inspection of case hardening depth |
| CN103163216A (en) * | 2013-03-14 | 2013-06-19 | 天津大学 | Defect identification and evaluation method of metallic conductor based on giant magnetoresistance sensor |
-
2013
- 2013-12-20 CN CN201310714258.3A patent/CN103760226A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6504363B1 (en) * | 2000-03-07 | 2003-01-07 | Teodor Dogaru | Sensor for eddy current testing and method of use thereof |
| US20040051525A1 (en) * | 2002-09-17 | 2004-03-18 | Siemens Westinghouse Power Corporation | Eddy current inspection probe |
| JP2009079984A (en) * | 2007-09-26 | 2009-04-16 | Hitachi Ltd | Eddy current inspection apparatus and method |
| CN201527411U (en) * | 2009-07-06 | 2010-07-14 | 李长青 | Two-dimensional low frequency pulse eddy current probe |
| CN102549375A (en) * | 2009-09-21 | 2012-07-04 | 通用电气公司 | Eddy current inspection of case hardening depth |
| CN102230914A (en) * | 2011-03-31 | 2011-11-02 | 厦门安锐捷电子科技有限公司 | Electromagnetic resonance-based nondestructive testing method for metal material |
| CN103163216A (en) * | 2013-03-14 | 2013-06-19 | 天津大学 | Defect identification and evaluation method of metallic conductor based on giant magnetoresistance sensor |
Non-Patent Citations (3)
| Title |
|---|
| 赖圣 等: "脉冲涡流阵列成像检测", 《无损检测》, vol. 33, no. 10, 31 December 2011 (2011-12-31), pages 13 - 15 * |
| 赖圣: "飞机多层金属结构脉冲涡流检测技术研究", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑（月刊）》, no. 01, 15 January 2013 (2013-01-15) * |
| 郑阔海 等: "微型磁电阻效应传感器的空间应用前景", 《真空与低温》, vol. 18, no. 2, 30 June 2012 (2012-06-30), pages 83 - 87 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106198722A (en) * | 2016-06-28 | 2016-12-07 | 天津因科新创科技有限公司 | The method and apparatus of Pulsed eddy current testing weld seam |
| CN106198722B (en) * | 2016-06-28 | 2021-11-19 | 天津因科新创科技有限公司 | Method and device for detecting welding seam by pulse eddy current |
| CN109625317A (en) * | 2018-11-29 | 2019-04-16 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of detecting instrument having aircraft and engine component eddy current inspection function concurrently |
| CN109625317B (en) * | 2018-11-29 | 2022-06-03 | 中国航发沈阳黎明航空发动机有限责任公司 | Detection instrument with eddy current inspection function of airplane and engine parts |
| CN116068044A (en) * | 2023-03-21 | 2023-05-05 | 辽宁锂想科技有限公司 | Multichannel multi-frequency weld joint flaw detection device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103760224A (en) | Spacecraft nondestructive detection sensor and nondestructive detection system | |
| CN111398413B (en) | Double-layer symmetrical differential plane eddy current detection sensor | |
| CN102590328B (en) | Permanent magnetic and alternating current direct current composite magnetic flux leakage detecting method | |
| US11493479B2 (en) | Low-frequency electromagnetic detection method for large-scale damage of ferromagnetic materials based on broadband excitation | |
| CN205861255U (en) | Ferromagnetic material stress based on barkhausen detection device | |
| Huang et al. | New technologies in electromagnetic non-destructive testing | |
| CN103412038B (en) | The portable ACFM detector of a kind of Based PC/104 embedded system | |
| CN106442711B (en) | Nondestructive testing method based on eddy current reflection and transmission | |
| CN103257181B (en) | Sheet metal defect detecting device and method under a kind of high-speed motion state | |
| CN104155361A (en) | Pulse eddy electromagnetism nondestructive detection method based on probe with iron core coil | |
| CN103822967B (en) | Double-excitation-coil conductor defect automatic flaw detection device and flaw detection method | |
| CN105067701B (en) | Pulsed eddy current testing hardware separation method based on rectangular probe | |
| CN104977352A (en) | Defect and stress non-destructive testing system and non-destructive testing method based on pulsed eddy current and Barkhausen | |
| CN103954684A (en) | Method for nondestructive testing by use of change rate of magnetic flux leakage | |
| CN105717191A (en) | Detection method and device for magnetic Barkhausen noise signal and magnetic parameters | |
| CN105548349B (en) | Realize the rectangular probe pulse eddy current detection method of Root cause analysis technology | |
| CN103760226A (en) | Non-destructive detection method of spacecraft | |
| CN109060939A (en) | Steel rail defect checking method for width based on leakage magnetic detection device | |
| CN204255904U (en) | Based on the Pulsed Eddy Current Testing System of rectangle difference detector | |
| CN103728368A (en) | Crack detector used for rail parts | |
| CN112415088B (en) | Internal penetrating type transverse pulse eddy current detection probe and application method thereof | |
| CN205879865U (en) | Nondestructive detection system based on vortex reflection and transmission | |
| CN109212019A (en) | A kind of far-field eddy and magnetic striction wave guide hybrid sensor and its detection method | |
| WO2019047396A1 (en) | Dynamic magnet detection system and detection method, and electromagnetic array control method | |
| CN107356664A (en) | A kind of ferrimagnet defect detecting device based on low frequency leakage field |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20140430 |