CN104020497A - Z component receiving device for airborne Z-axis tipper electromagnetic survey system - Google Patents
Z component receiving device for airborne Z-axis tipper electromagnetic survey system Download PDFInfo
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Abstract
The invention relates to a Z component receiving device for an airborne Z-axis tipper electromagnetic survey system. The device is formed in the following ways: a collection system is fixed on a collection platform, the collection platform is hung on the lower part of a helicopter by three groups of steel wires which are more than 80m, a Z component receiving coil is hung on the lower part of the collection platform by virtue of a hanging rope, a preposed amplification circuit is fixed on the Z component receiving coil and connected with the output end of the Z component receiving coil, output of the preposed amplification circuit is connected with the collection system through a signal wire. A feedback coil generates a negative feedback magnetic field opposite to the direction of a detected magnetic field, so that the receiving coil forms a closed-loop flux negative feedback loop, the dynamic range of the output sensitivity of the receiving coil is reduced, and collection of output signals by the data collection system is favored; the receiving coil adopts a grading shielding structure, so that the shielding layer impedance can be reduced; a two-layer shielding structure is adopted, the first shielding layer floats, and the second shielding layer is grounded, so that high and low frequency electromagnetic interference of the environment outside the receiving coil can be effectively shielded, and the detection accuracy of the receiving coil can be improved.
Description
Technical field:
The present invention relates to a kind of airborne geophysical prospecting receiving trap, especially the aviation Z axis electromagnetic prospecting system Z component receiving trap that inclines.
Background technology:
Incline sub-EMP method of aviation Z axis adopts helicopter as flight carrier, utilizes natively magnetic field or artificial magnetic field as field source, receives underground medium because of the secondary field of eddy effect generation, thereby subsurface resistivity is made explanations by receiving trap.The aviation Z axis electromagnetic prospecting system Z component receiving trap that inclines is aviation Z axis one of the core of sub-electromagnetic prospecting system of inclining, and comprises inductive coil, tickler, screen layer, homophase pre-amplification circuit.
Canada Geotech company proposed the aviation Z axis electromagnetic exploration method that inclines as far back as 2006, but introduce aviation Z axis except part, incline and can find in the application case of sub-electromagnetic exploration method receiving trap surface structure, do not see concrete aviation Z axis the disclosing of sub-electromagnetic prospecting system Z component receiving trap structure of inclining.
Incline sub-electromagnetic prospecting system Z component receiving trap of Geotech company aviation Z axis adopts fiberglass skeleton, and weight is heavier, requires aircraft to have very high load.Simultaneously because fiberglass belongs to rigid material, non-deformable, for diameter, compared with for large receiving coil, transport also extremely inconvenient.
Domestic at present except the article of some research aviation TDEM, aviation frequency domain electromagnetic methods or device are published, not yet find to relate to aviation Z axis the incline paper of sub-electromagnetic exploration method or publishing of patent.
Summary of the invention:
The object of the present invention is to provide a kind of incline Z component receiving trap of sub-electromagnetic prospecting system of aviation Z axis that is applicable to.
The object of the invention is to realize in the following manner:
Airborne electromagnetic survey system Z component receiving trap, to be fixed on acquisition platform 2 by acquisition system 1, acquisition platform 2 is hung in helicopter 4 bottoms by three groups of wire rope 3 that are greater than 80m, Z component receiving coil 5 is hung in acquisition platform 2 bottoms by hanging rope 6, be fixed on pre-amplification circuit 7 on Z component receiving coil 5 and be connected with the output terminal of Z component receiving coil 5, the output of pre-amplification circuit 7 connects and composes through signal wire 8 and acquisition system 1.
Z component receiving coil 5 is to be on the elasticity carbon skeleton 10 of 3.8m-10m circle or regular polygon, to be equipped with to be no less than eight groups of detachable firm banking 9 fixed inductors 11 and tickler 16 forms by diameter.
Inductive coil 11 is by 12 circle 10 core shielding line coilings, any heart yearn one end of take in ten core shielding lines is starting point, by clockwise or counter clockwise direction, ten heart yearns are connected into a wire, coiling initiating terminal is output signal end, tail end is earth terminal, and every circle 10 core shielding lines are outer by the first screen layer 12 shieldings.
The first screen layer 12 is provided with shielding copper mesh breakpoint I 13 and shielding copper mesh breakpoint II 14 with any two points of center of circle symmetry, shielding copper mesh breakpoint I 13 is connected with adjacent shields copper mesh breakpoint I 13, and shielding copper mesh breakpoint II 14 is connected with adjacent shields copper mesh breakpoint II 14.
Secondary shielding layer 15 is enclosed at the inductive coil 11 even spiral windings one in outside by wide 2cm copper strips, and head and the tail do not join.
Tickler 16 is parallel to inductive coil 11 coilings by wire in secondary shielding layer 15 outside, and the number of turn is 3 circles, and coiling direction is identical with inductive coil, and coiling initiating terminal is feedback signal incoming end, and tail end is earth terminal.
The earth terminal of secondary shielding layer 15, inductive coil 11 and tickler 16 all accesses the earth terminal of homophase pre-amplification circuit 7.
Beneficial effect: the aviation Z axis electromagnetic prospecting system Z component receiving trap that inclines, as receiving coil skeleton, has reduced the weight of coil with elasticity carbon skeleton; Adopt detachable mounting structure simultaneously, thereby make to transport convenient.Tickler produces the negative feedback magnetic field contrary with tested magnetic direction, thereby makes receiving coil form closed loop magnetic flux negative feedback loop, has reduced the dynamic range of receiving coil output sensitivity, and more favourable data acquisition system (DAS) gathers output signal.Receiving coil adopts double-layer shielding structure, the floating ground of the first screen layer, and secondary shielding layer ground connection, thus can effectively shield receiving coil external environment condition low-and high-frequency electromagnetic interference (EMI), improved the detection accuracy of receiving coil.
Accompanying drawing explanation:
Fig. 1 is the aviation Z axis electromagnetic prospecting system Z component receiving trap structural drawing that inclines
Fig. 2 is Fig. 1 receiving coil mounting structure figure
Fig. 3 screen layer sectional view
Fig. 4 the first screen layer 12 any two points shielding copper mesh breakpoint graphs
1 data acquisition system (DAS), 2 aerial data acquisition platforms, 3 wire rope, 4 helicopters, 5 Z component receiving coils, 6 nylon suspension lanyard ropes, 7 homophase pre-amplification circuits, 8 homophase pre-amplification circuits are to the signal wire of data acquisition system (DAS), 9 firm bankings, 10 elasticity carbon skeletons, 11 inductive coils, 12 first screen layers, 13 shielding copper mesh breakpoint I, 14 shielding copper mesh breakpoint II, 15 secondary shielding layers, 16 ticklers.
Embodiment:
Below in conjunction with drawings and Examples, be described in further detail:
Airborne electromagnetic survey system Z component receiving trap, to be fixed on acquisition platform 2 by acquisition system 1, acquisition platform 2 is hung in helicopter 4 bottoms by three groups of wire rope 3 that are greater than 80m, Z component receiving coil 5 is hung in acquisition platform 2 bottoms by hanging rope 6, be fixed on pre-amplification circuit 7 on Z component receiving coil 5 and be connected with the output terminal of Z component receiving coil 5, the output of pre-amplification circuit 7 connects and composes through signal wire 8 and acquisition system 1.
Z component receiving coil 5 is to be on the elasticity carbon skeleton 10 of 3.8m-10m circle or regular polygon, to be equipped with to be no less than eight groups of detachable firm banking 9 fixed inductors 11 and tickler 13 forms by diameter.
Inductive coil 11 is by 12 circle 10 core shielding line coilings, any heart yearn one end of take in ten core shielding lines is starting point, by clockwise or counter clockwise direction, ten heart yearns are connected into a wire, coiling initiating terminal is output signal end, tail end is earth terminal, and every circle 10 core shielding lines are outer by the first screen layer 12 shieldings.
The first screen layer 12 is provided with shielding copper mesh breakpoint I 13 and shielding copper mesh breakpoint II 14 with any two points of center of circle symmetry, shielding copper mesh breakpoint I 13 is connected with adjacent shields copper mesh breakpoint I 13, and shielding copper mesh breakpoint II 14 is connected with adjacent shields copper mesh breakpoint II 14.
Secondary shielding layer 15 is enclosed at the inductive coil 11 even spiral windings one in outside by wide 2cm copper strips, and head and the tail do not join.
Tickler 16 is parallel to inductive coil 11 coilings by wire in secondary shielding layer 15 outside, and the number of turn is 3 circles, and coiling direction is identical with inductive coil, and coiling initiating terminal is feedback signal incoming end, and tail end is earth terminal.
The earth terminal of secondary shielding layer 15, inductive coil 11 and tickler 16 all accesses the earth terminal of homophase pre-amplification circuit 7.
Embodiment 1
Data acquisition system (DAS) 1 is fixed on aerial data acquisition platform 2 upper surfaces, hangs in helicopter 4 bottoms, thereby reduce the electromagnetic interference (EMI) of helicopter to receiving trap by three groups of steel wires 3 that are greater than 80m.Z component receiving coil 5 is shaped as circle, by being no less than eight groups of nylon suspension lanyard ropes 6 that are greater than 8m, hangs platform bottom aloft.Homophase pre-amplification circuit 7 is fixed on Z component receiving coil upside by firm banking, and be connected with receiving coil output terminal, the output of homophase pre-amplification circuit is delivered in data acquisition system (DAS) to the signal wire 8 of data acquisition system (DAS) via homophase pre-amplification circuit, by data acquisition system (DAS), carries out data acquisition and pre-service.
Z component receiving trap receiving coil is fixed on elasticity carbon skeleton 10 by being no less than the detachable firm banking 9 of eight groups, comprises inductive coil 11, tickler 12.Inductive coil is by 12 circle 10 core shielding line coilings, and any heart yearn one end of take in ten core shielding lines is starting point, in the direction of the clock ten heart yearns is connected into a wire, and coil diameter is 3.8m, and coiling initiating terminal is output signal end, and tail end is earth terminal.The first screen layer 12 is provided with shielding copper mesh breakpoint I 13 and shielding copper mesh breakpoint II 14 with any two points of center of circle symmetry, shielding copper mesh breakpoint I 13 is connected with adjacent shields copper mesh breakpoint I 13, and shielding copper mesh breakpoint II 14 is connected with adjacent shields copper mesh breakpoint II 14.
By wide 2cm copper strips, in inductive coil outside, even spiral winding one encloses secondary shielding layer 15, and head and the tail do not join.Tickler 16 is parallel to inductive coil 11 coilings by wire in secondary shielding layer outside, and the number of turn is 3 circles, and coiling direction is identical with inductive coil, and coiling initiating terminal is feedback signal incoming end, and tail end is earth terminal.The earth terminal of secondary shielding layer 15, inductive coil 11 and tickler 16 all accesses the earth terminal of homophase pre-amplification circuit 7.
At the helicopter take-off venue assembling aviation Z axis electromagnetic prospecting system Z component receiving trap that inclines, fastening firm banking in assembling process, and receiving coil one side is installed and launched to be placed in to nylon suspension lanyard rope, aerial data acquisition platform and steel wire in order.Before helicopter takes off, data acquisition system (DAS) is opened and started to gather, after taking off, ground experiment personnel record gets off the plane and starts and finish along the moment of survey line flight.The secondary field signal of data acquisition system (DAS) Real-time Collection storing received coil output in flight course, and the geographic location signal sent of the GPS module of receiving system inside.According to the aircraft of recording, start and finish, along the moment of survey line flight, from the data of data acquisition system stores, to intercept effectively along survey line secondary field signal, and then according to secondary field information, subsurface resistivity is made explanations.
Receiving coil is suspended on helicopter bottom, parallel with surface level.Underground medium is because the Z component secondary field (representing with B) that eddy effect produces acts on receiving coil interior zone, and according to the law of electromagnetic induction, now the output sensitivity of receiving coil can be represented by the formula:
Because the dynamic range of inductive coil output sensitivity is larger, for fear of homophase pre-amplification circuit, occur the normal work of saturated and impact, so enlargement factor can not be too large, thereby the data amplitude that causes frequency range that output sensitivity is lower to collect is too little.
After adding tickler, receiving coil forms closed loop magnetic flux negative feedback loop, i.e. inductive coil inducted secondary field send into homophase pre-amplification circuit and amplify, and tickler is sent in the output of amplifying circuit simultaneously, thereby the negative feedback magnetic field of generation and secondary field opposite direction, offsets part secondary field.Now the output sensitivity of receiving coil can be represented by the formula:
In practical application, pass through to change feedback resistance R
fbresistance, change the dynamic range of receiving coil output sensitivity, thereby avoid due to the normal work of homophase pre-amplification circuit output saturation impact.
Embodiment 2
Data acquisition system (DAS) 1 is fixed on aerial data acquisition platform 2 upper surfaces, hangs in helicopter 4 bottoms, thereby reduce the electromagnetic interference (EMI) of helicopter to receiving trap by three groups of steel wires 3 that are greater than 80m.Z component receiving coil 5 is shaped as regular polygon, by being no less than eight groups of nylon suspension lanyard ropes 6 that are greater than 8m, hangs platform bottom aloft.Homophase pre-amplification circuit 7 is fixed on Z component receiving coil upside by firm banking, and be connected with receiving coil output terminal, the output of homophase pre-amplification circuit is delivered in data acquisition system (DAS) to the signal wire 8 of data acquisition system (DAS) via homophase pre-amplification circuit, by data acquisition system (DAS), carries out data acquisition and pre-service.
Z component receiving trap receiving coil is fixed on elasticity carbon skeleton 10 by being no less than the detachable firm banking 9 of eight groups, comprises inductive coil 11, tickler 12.Inductive coil is by 12 circle 10 core shielding line coilings, and any heart yearn one end of take in ten core shielding lines is starting point, and by counterclockwise ten heart yearns being connected into a wire, coil diameter is 8m, and coiling initiating terminal is output signal end, and tail end is earth terminal.The first screen layer 12 is provided with shielding copper mesh breakpoint I 13 and shielding copper mesh breakpoint II 14 with any two points of center of circle symmetry, shielding copper mesh breakpoint I 13 is connected with adjacent shields copper mesh breakpoint I 13, and shielding copper mesh breakpoint II 14 is connected with adjacent shields copper mesh breakpoint II 14.
By wide 2cm copper strips, in inductive coil outside, even spiral winding one encloses secondary shielding layer 15, and head and the tail do not join.Tickler 16 is parallel to inductive coil 11 coilings by wire in secondary shielding layer outside, and the number of turn is 3 circles, and coiling direction is identical with inductive coil, and coiling initiating terminal is feedback signal incoming end, and tail end is earth terminal.The earth terminal of secondary shielding layer 15, inductive coil 11 and tickler 16 all accesses the earth terminal of homophase pre-amplification circuit 7.
At the helicopter take-off venue assembling aviation Z axis electromagnetic prospecting system Z component receiving trap that inclines, fastening firm banking in assembling process, and receiving coil one side is installed and launched to be placed in to nylon rope, aerial data acquisition platform and steel wire in order.Before helicopter takes off, data acquisition system (DAS) is opened and started to gather, after taking off, ground experiment personnel record gets off the plane and starts and finish along the moment of survey line flight.The secondary field signal of data acquisition system (DAS) Real-time Collection storing received coil output in flight course, and the geographic location signal sent of the GPS module of receiving system inside.According to the aircraft of recording, start and finish, along the moment of survey line flight, from the data of data acquisition system stores, to intercept effectively along survey line secondary field signal, and then according to secondary field information, subsurface resistivity is made explanations.
Receiving coil is suspended on helicopter bottom, parallel with surface level.Underground medium is because the Z component secondary field (representing with B) that eddy effect produces acts on receiving coil interior zone, according to the law of electromagnetic induction,
Now the output sensitivity of receiving coil can be represented by the formula:
Because the dynamic range of inductive coil output sensitivity is larger, for fear of homophase pre-amplification circuit, occur the normal work of saturated and impact, so enlargement factor can not be too large, thereby the data amplitude that causes frequency range that output sensitivity is lower to collect is too little.
After adding tickler, receiving coil forms closed loop magnetic flux negative feedback loop, i.e. inductive coil inducted secondary field send into homophase pre-amplification circuit and amplify, and tickler is sent in the output of amplifying circuit simultaneously, thereby the negative feedback magnetic field of generation and secondary field opposite direction, offsets part secondary field.Now the output sensitivity of receiving coil can be represented by the formula:
In practical application, pass through to change feedback resistance R
fbresistance, change the dynamic range of receiving coil output sensitivity, thereby avoid due to the normal work of homophase pre-amplification circuit output saturation impact.
Claims (6)
1. an aviation Z axis electromagnetic prospecting system Z component receiving trap that inclines, it is characterized in that, to be fixed on acquisition platform (2) by acquisition system (1), acquisition platform (2) is greater than long wire rope (3) hanging of 80m in helicopter (4) bottom by three groups, Z component receiving coil (5) is hung in acquisition platform (2) bottom by hanging rope (6), be fixed on Z component receiving coil (5), pre-amplification circuit (7) is connected with the output terminal of Z component receiving coil (5), the output of pre-amplification circuit (7) connects and composes through signal wire (8) and acquisition system (1).
2. according to the aviation Z axis claimed in claim 1 sub-electromagnetic prospecting system Z component receiving trap that inclines, it is characterized in that, Z component receiving coil (5) is to be no less than eight groups of detachable firm bankings (9) fixed inductors (11) and tickler (13) formation by being equipped with on diameter 3.8m-10m circle or regular polygon elasticity carbon skeleton (10).
3. according to the aviation Z axis claimed in claim 2 sub-electromagnetic prospecting system Z component receiving trap that inclines, it is characterized in that, inductive coil (11) is by 12 circle ten core shielding line coilings, any heart yearn one end of take in ten core shielding lines is starting point, by clockwise or counter clockwise direction, ten heart yearns are connected into a wire, coiling initiating terminal is output signal end, and tail end is earth terminal, and every circle ten core shielding lines are outer to be shielded by the first screen layer (12).
4. according to the aviation Z axis claimed in claim 3 sub-electromagnetic prospecting system Z component receiving trap that inclines, it is characterized in that, the first screen layer (12) is provided with shielding copper mesh breakpoint I (13) and shielding copper mesh breakpoint II (14) with any two points of center of circle symmetry, shielding copper mesh breakpoint I (13) is connected with adjacent shields copper mesh breakpoint I (13), and shielding copper mesh breakpoint II (14) is connected with adjacent shields copper mesh breakpoint II (14).
5. according to the aviation Z axis claimed in claim 2 sub-electromagnetic prospecting system Z component receiving trap that inclines, it is characterized in that, tickler (16) is parallel to inductive coil (11) coiling by 3 circle wires in secondary shielding layer (15) outside, coiling direction is identical with inductive coil (11), coiling initiating terminal is feedback signal incoming end, and tail end is earth terminal.
6. according to the aviation Z axis claimed in claim 5 sub-electromagnetic prospecting system Z component receiving trap that inclines, it is characterized in that, secondary shielding layer (15) is by wide 2cm copper strips even spiral winding outside inductive coil (11), and head and the tail do not join, and the earth terminal of secondary shielding layer (15), inductive coil (11) and tickler (16) all accesses the earth terminal of homophase pre-amplification circuit (7).
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443415A (en) * | 2014-11-27 | 2015-03-25 | 湖南航天机电设备与特种材料研究所 | Carrying structure for aviation transient electromagnetic coil |
| CN104865608A (en) * | 2015-05-22 | 2015-08-26 | 吉林大学 | Time-domain airborne electromagnetic method motion noise detection apparatus and inhibition method |
| CN105204076A (en) * | 2015-10-19 | 2015-12-30 | 吉林大学 | Transient electromagnetic detection motion noise suppressing device and method for helicopter |
| CN108761358A (en) * | 2018-04-22 | 2018-11-06 | 成都理工大学 | The manufacturing method of fluxgate sensor magnetic probe |
| CN113093294A (en) * | 2021-04-15 | 2021-07-09 | 中国科学院空天信息创新研究院 | Magnetic field sensor |
| CN114114429A (en) * | 2021-11-23 | 2022-03-01 | 东华理工大学 | Ground-space frequency dip sounding device and method |
| CN116299718A (en) * | 2023-03-03 | 2023-06-23 | 中国科学院地质与地球物理研究所 | Semi-aviation electromagnetic apparent resistivity measurement system and method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030169045A1 (en) * | 2002-03-06 | 2003-09-11 | Whitton Raymond Macklin | Method and apparatus for a rigidly joined together and floating bucking and receiver coil assembly for use in airborne electromagnetic survey systems |
| US20100237870A1 (en) * | 2009-03-17 | 2010-09-23 | Geo Equipment Manufacturing Limited | Geophysical Prospecting Using Electric And Magnetic Components Of Natural Electromagnetic Fields |
| US20110148421A1 (en) * | 2008-08-29 | 2011-06-23 | Geotech Airborne Limited | Bucking Coil and B-Field Measurement System And Apparatus for Time Domain Electromagnetic Measurements |
| CN102176063A (en) * | 2011-02-21 | 2011-09-07 | 吉林大学 | Primary field self-counteracting device for time-domain airborne electromagnetic method |
| CN102249005A (en) * | 2011-04-14 | 2011-11-23 | 陈斌 | Towed bird helicopter-borne time domain airborne electromagnetic detection system |
| CN102763007A (en) * | 2009-11-27 | 2012-10-31 | 吉欧泰科航空物探有限公司 | Receiver coil assembly for airborne geophysical surveying with noise mitigation |
| WO2013067624A1 (en) * | 2011-11-08 | 2013-05-16 | Fugro Canada Corp. | Airborne electromagnetic system with rigid loop structure comprised of lightweight modular non-rotational frames |
-
2014
- 2014-06-24 CN CN201410289739.9A patent/CN104020497B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030169045A1 (en) * | 2002-03-06 | 2003-09-11 | Whitton Raymond Macklin | Method and apparatus for a rigidly joined together and floating bucking and receiver coil assembly for use in airborne electromagnetic survey systems |
| US20110148421A1 (en) * | 2008-08-29 | 2011-06-23 | Geotech Airborne Limited | Bucking Coil and B-Field Measurement System And Apparatus for Time Domain Electromagnetic Measurements |
| US20100237870A1 (en) * | 2009-03-17 | 2010-09-23 | Geo Equipment Manufacturing Limited | Geophysical Prospecting Using Electric And Magnetic Components Of Natural Electromagnetic Fields |
| CN102763007A (en) * | 2009-11-27 | 2012-10-31 | 吉欧泰科航空物探有限公司 | Receiver coil assembly for airborne geophysical surveying with noise mitigation |
| CN102176063A (en) * | 2011-02-21 | 2011-09-07 | 吉林大学 | Primary field self-counteracting device for time-domain airborne electromagnetic method |
| CN102249005A (en) * | 2011-04-14 | 2011-11-23 | 陈斌 | Towed bird helicopter-borne time domain airborne electromagnetic detection system |
| WO2013067624A1 (en) * | 2011-11-08 | 2013-05-16 | Fugro Canada Corp. | Airborne electromagnetic system with rigid loop structure comprised of lightweight modular non-rotational frames |
Non-Patent Citations (2)
| Title |
|---|
| 王世隆 等: "同心补偿式直升机时间域航空电磁法吊舱校准装置研究", 《地球物理学报》 * |
| 符磊 等: "磁通负反馈空心线圈传感器特性和噪声研究", 《仪器仪表学报》 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443415A (en) * | 2014-11-27 | 2015-03-25 | 湖南航天机电设备与特种材料研究所 | Carrying structure for aviation transient electromagnetic coil |
| CN104865608A (en) * | 2015-05-22 | 2015-08-26 | 吉林大学 | Time-domain airborne electromagnetic method motion noise detection apparatus and inhibition method |
| CN104865608B (en) * | 2015-05-22 | 2017-07-14 | 吉林大学 | Time-domain AEM motion artifacts detection means and suppressing method |
| CN105204076A (en) * | 2015-10-19 | 2015-12-30 | 吉林大学 | Transient electromagnetic detection motion noise suppressing device and method for helicopter |
| CN108761358A (en) * | 2018-04-22 | 2018-11-06 | 成都理工大学 | The manufacturing method of fluxgate sensor magnetic probe |
| CN108761358B (en) * | 2018-04-22 | 2021-07-23 | 成都理工大学 | Method for manufacturing magnetic probe of fluxgate sensor |
| CN113093294A (en) * | 2021-04-15 | 2021-07-09 | 中国科学院空天信息创新研究院 | Magnetic field sensor |
| CN114114429A (en) * | 2021-11-23 | 2022-03-01 | 东华理工大学 | Ground-space frequency dip sounding device and method |
| CN114114429B (en) * | 2021-11-23 | 2023-06-16 | 东华理工大学 | Device and method for sounding and exploring ground-air frequency inclinometer |
| CN116299718A (en) * | 2023-03-03 | 2023-06-23 | 中国科学院地质与地球物理研究所 | Semi-aviation electromagnetic apparent resistivity measurement system and method |
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