CN103760224A - Spacecraft nondestructive detection sensor and nondestructive detection system - Google Patents

Spacecraft nondestructive detection sensor and nondestructive detection system Download PDF

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Publication number
CN103760224A
CN103760224A CN201310711809.0A CN201310711809A CN103760224A CN 103760224 A CN103760224 A CN 103760224A CN 201310711809 A CN201310711809 A CN 201310711809A CN 103760224 A CN103760224 A CN 103760224A
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described
spacecraft
destructive testing
non
barrel
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CN201310711809.0A
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Chinese (zh)
Inventor
郑阔海
杨生胜
李存惠
苗育君
王鷁
孔风连
全小平
顾征
王彤
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兰州空间技术物理研究所
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Priority to CN201310711809.0A priority Critical patent/CN103760224A/en
Publication of CN103760224A publication Critical patent/CN103760224A/en

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Abstract

The invention provides a spacecraft nondestructive detection sensor and a nondestructive detection system. The spacecraft nondestructive detection sensor comprises an excitation mechanism and a tunnel magnetoresistor, wherein the excitation mechanism is used for providing a vortex magnetic field for a part to be detected of a spacecraft under the action of a square-wave pulse electric current; the tunnel magnetoresistor is connected with the excitation mechanism in a matching way, is used for detecting the change condition of the vortex magnetic field of the part to be detected, and generates the corresponding detection signal for output; the tunnel magnetoresistor with the high sensitivity is adopted as a detecting element, the square-wave pulse electric current is utilized to stimulate the excitation mechanism to generate the vortex magnetic field for the part to be detected, the vortex magnetic field can permeate in a material, and thus the spacecraft nondestructive detection sensor provided by the invention is capable of detecting both depth and sensitivity.

Description

Spacecraft Non-Destructive Testing sensor and nondestructive detection system

Technical field

The present invention relates to spationautics field, relate in particular to a kind of spacecraft Non-Destructive Testing sensor and nondestructive detection system.

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 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, using this as the preorder in greater detail of discussing after a while.

The invention provides a kind of spacecraft Non-Destructive Testing sensor, comprising:

Excitation mechanism, provides eddy current magnetism for the position to be detected for spacecraft under the effect of square wave pulsed current;

Tunnel magnetoresistance, is connected with described excitation mechanism, changes, and generate corresponding detection signal and export for detection of the eddy current magnetism at described position to be detected.

The present invention also provides a kind of spacecraft nondestructive detection system, comprises above-mentioned spacecraft Non-Destructive Testing sensor, also comprises:

Impulse source, is connected with described excitation mechanism, is used to described excitation mechanism that square wave pulsed current is provided;

Data acquisition equipment, is connected with described tunnel magnetoresistance, for analyze the degree of impairment at described position to be detected according to detection signal.

Spacecraft Non-Destructive Testing sensor provided by the invention and nondestructive detection system, 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 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.Based on the embodiment 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:

Excitation mechanism 101, provides eddy current magnetism for the position to be detected for spacecraft under the effect of square wave pulsed current;

Tunnel magnetoresistance 102, is connected with excitation mechanism 101, changes, and generate corresponding detection signal and export for detection of the eddy current magnetism at position to be detected.

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 length of penetration difference of the eddy current magnetism of different frequency to 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 is fixed on the magnetic cylinder 105 at 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 the optional embodiment of one, 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.

Shield shell 106 shields extraneous magnetic interference on the one hand, and it is more accurate to make to detect, and the convenience of using improves in fixed excitation mechanism 101 on the other hand.

As the optional embodiment of one, 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.

Insulation course 107 is for to isolating between excitation mechanism 101 and shield shell 106.

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, input information/output terminal that lead terminal 108 is 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 receiving end to lay respectively at the both sides at position to be detected, to installation site no requirement (NR), can carry out in situ detection;

5, relatively adopt the traditional electrical nondestructive detecting technology of vortex of coil as 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 and changes of magnetic field have nothing to do, and 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;

Impulse source 202, is connected with the excitation mechanism in Non-Destructive Testing sensor 201, is used to excitation mechanism that square wave pulsed current is provided;

Data acquisition equipment 203, is connected with the tunnel magnetoresistance in Non-Destructive Testing sensor 201, for analyze the degree of impairment at described position to be detected according to detection signal.

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.

Data acquisition equipment 203 carries out difference processing with demarcation signal after obtaining detection signal, can obtain the degree of impairment at position to be detected according to structure after treatment.

As the optional embodiment of one, the detection system that the present embodiment provides also comprises the gear train 204 being connected with Non-Destructive Testing sensor 201 companies of institute, 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 the optional embodiment of one, 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 206 being arranged between wave filter 205 and data acquisition equipment 203, for filtering detection signal after treatment is amplified to 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 multiple positions by manual mobile Non-Destructive Testing sensor, also can be by transmission mechanism control Non-Destructive Testing sensor mobile detection on spacecraft automatically.

Degree of impairment comprises equivalent size and the depth of defect of position to be detected defect.

As the optional embodiment of one, 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 the optional embodiment of one, detection signal is carried out also comprising after filtering processing:

Filtering detection signal after treatment is amplified to 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 mapping relations between degree of impairment and the demarcation signal set up in advance, obtain the degree of impairment corresponding with described demarcation signal.

With reference to figure 4, the method that obtains demarcation signal comprises:

Non-Destructive Testing sensor 304 is positioned over to the not damaged position 306 of reference block 305, and obtains reference signal by the tunnel magnetoresistance in Non-Destructive Testing sensor 304;

Non-Destructive Testing sensor 304 is moved to the known damage position 307 of reference block 305; And obtain damage signal by the tunnel magnetoresistance in Non-Destructive Testing sensor 304;

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 lack curve, at the known damage position 307 that Non-Destructive Testing sensor is moved to 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 difference of different frequency magnetic field in detected position, 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:

δ = 1 πfμσ

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 size 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 the Vp and the Tp value that read 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 used 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 be used for surface defects detection, cannot be used in the in situ detection of sandwich construction, ray Dynamic Non-Destruction Measurement can not be used 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, for a kind of embodiment, describe and/or the feature that illustrates 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 case of not exceeding 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 (10)

1. a spacecraft Non-Destructive Testing sensor, is characterized in that, comprising:
Excitation mechanism, provides eddy current magnetism for the position to be detected for spacecraft under the effect of square wave pulsed current;
Tunnel magnetoresistance, is connected with described excitation mechanism, for detection of the eddy current magnetism situation of change at described position to be detected, and generates corresponding detection signal and exports.
2. spacecraft Non-Destructive Testing sensor according to claim 1, it is characterized in that, described excitation mechanism comprises field coil and the magnet that adopts high permeability materials to make, described magnet comprises barrel-shaped magnetic conduction portion and is fixed on the magnetic cylinder at described barrel-shaped magnetic conduction portion's inner bottom surface geometric center place, described field coil is wound on described magnetic cylinder, and described magnetic cylinder is positioned at the end face of described barrel-shaped magnetic conduction portion openend direction and the end face of described barrel-shaped magnetic conduction portion openend in same plane.
3. spacecraft Non-Destructive Testing sensor according to claim 2, is characterized in that, described magnetic cylinder is hollow structure, and one end of described tunnel magnetoresistance is arranged in magnetic cylinder, and the end face of the other end and described barrel-shaped magnetic conduction portion openend is in same plane.
4. spacecraft Non-Destructive Testing sensor according to claim 2, it is characterized in that, described sensor also comprises the shield shell suitable with described barrel-shaped magnetic conduction portion, described shield shell is barrel shaped structure, described shield shell is arranged at the outside of described barrel-shaped magnetic conduction portion, for described excitation mechanism being fixed and magnetic interference to external world shields, the end face of the openend of the end face of described shield shell openend and described barrel-shaped magnetic conduction portion is in same plane.
5. spacecraft Non-Destructive Testing sensor according to claim 4, it is characterized in that, between described shield shell and described barrel-shaped magnetic conduction portion, be also provided with insulation course, described insulation course is positioned at the end face of described barrel-shaped magnetic conduction portion openend direction and the end face of described barrel-shaped magnetic conduction portion openend in same plane.
6. spacecraft Non-Destructive Testing sensor according to claim 4, it is characterized in that, described shield shell is provided with lead terminal, described lead terminal is arranged at the geometric center place of described shield shell bottom surface, for described detection signal being exported to outside or extraneous square wave pulsed current being inputed to described excitation mechanism.
7. spacecraft Non-Destructive Testing sensor according to claim 6, is characterized in that, described tunnel magnetoresistance is connected with described lead terminal by the first lead-in wire, for exporting described detection signal to outside; Described excitation mechanism is connected with described lead terminal by the second lead-in wire, for extraneous square wave pulsed current is inputed to described excitation mechanism.
8. a spacecraft nondestructive detection system, is characterized in that, comprises the spacecraft Non-Destructive Testing sensor as described in as arbitrary in claim 1-7, also comprises:
Impulse source, is connected with described excitation mechanism, is used to described excitation mechanism that square wave pulsed current is provided;
Data acquisition equipment, is connected with described tunnel magnetoresistance, for analyze the degree of impairment at described position to be detected according to detection signal.
9. spacecraft nondestructive detection system according to claim 8, it is characterized in that, described detection system also comprises the gear train being connected with described Non-Destructive Testing sensor, for controlling described Non-Destructive Testing sensor, on the surface at described position to be detected, moves.
10. spacecraft nondestructive detection system according to claim 8, is characterized in that, described detection system also comprises the wave filter being connected between described tunnel magnetoresistance and described data acquisition equipment, for described detection signal is carried out to filtering processing;
Also comprise the amplifier being arranged between described wave filter and described data acquisition equipment, for filtering detection signal after treatment is amplified to processing.
CN201310711809.0A 2013-12-20 2013-12-20 Spacecraft nondestructive detection sensor and nondestructive detection system CN103760224A (en)

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CN104865311A (en) * 2015-05-04 2015-08-26 华中科技大学 Pulsed eddy current probe, testing device and testing method of testing device
CN105181786A (en) * 2015-07-16 2015-12-23 宁波市鄞州磁泰电子科技有限公司 Weld defect magnetic detection method
CN106596712A (en) * 2016-11-22 2017-04-26 西安交通大学 Frequency band selection type pulsed eddy current nondestructive testing method based on defect depth
CN107064291A (en) * 2017-04-26 2017-08-18 电子科技大学 A kind of magnetic assembles impulse eddy current Coil Detector sensor

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