CN113093294A - Magnetic field sensor - Google Patents
Magnetic field sensor Download PDFInfo
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- CN113093294A CN113093294A CN202110408674.5A CN202110408674A CN113093294A CN 113093294 A CN113093294 A CN 113093294A CN 202110408674 A CN202110408674 A CN 202110408674A CN 113093294 A CN113093294 A CN 113093294A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
- G01V3/00—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation
- G01V3/08—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation operating with magnetic or electric fields produced or modified by objects or geological structures or by detecting devices
- G01V3/10—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation operating with magnetic or electric fields produced or modified by objects or geological structures or by detecting devices using induction coils
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
- G01V3/00—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation
- G01V3/08—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation operating with magnetic or electric fields produced or modified by objects or geological structures or by detecting devices
- G01V3/081—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation operating with magnetic or electric fields produced or modified by objects or geological structures or by detecting devices the magnetic field is produced by the objects or geological structures
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/30—Assessment of water resources
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Abstract
The invention provides a magnetic field sensor, which is used for aviation ground electromagnetic detection and comprises a detector shell and an induction coil, wherein the detector shell is provided with a magnetic field sensor; an installation cavity is formed inside the detector shell; the induction coil is arranged in the installation cavity and comprises a plurality of multi-core coils, each multi-core coil is provided with a head end wire head and a tail end wire head, the multi-core coils are sequentially arranged along the radial direction of the multi-core coil, the tail end wire head of each two adjacent multi-core coils is electrically connected to the head end wire head, and the head end wire head and the tail end wire head of each two multi-core coils at the end part are electrically connected; wherein the number of turns of the induction coil is adjusted by adjusting the number of the multi-core coils. The induction coil is arranged in the installation cavity and comprises a plurality of multi-core coils, and the multi-core coils with different quantities are selected and used according to different environments so as to be suitable for different environments.
Description
Technical Field
The invention relates to the field of induction coils, in particular to a magnetic field sensor.
Background
The aerial earth electromagnetic detection system utilizes the audio frequency band and the low-frequency band weak natural electromagnetic field signals with huge energy and widely and uniformly distributed to detect the underground target body. It has become a new trend of aviation geophysical exploration with high efficiency and large depth exploration. The key point of successful application of the aviation ground electromagnetic detection system lies in developing a low-noise magnetic field sensor which can be used for detecting weak natural field underground target response signals, and performing noise matching optimization on a platform, a receiver and a data processing method to improve the detection precision and stability of the electromagnetic field on an aviation dynamic platform.
The induction type magnetic field sensor is a magnetic field sensor with wide frequency band, high sensitivity and stable performance, and is widely applied to the fields of geophysical exploration, space detection, environment monitoring and the like. In recent years, with the development of high-precision aviation magnetotelluric methods, magnetic field measurement in a direction perpendicular to the ground surface plane has been receiving increased attention and attention. The magnetic field component in the direction is weaker than the horizontal component, and due to the restriction of physical principles, the sensitivity of the existing induction type magnetic field sensor is in direct proportion to the volume, length and weight of the sensor, and meanwhile, the realization of high sensitivity and miniaturization is very difficult, and the parameters of the sensor cannot be adjusted according to different geological conditions.
Disclosure of Invention
The invention mainly aims to provide a magnetic field sensor, and aims to solve the problem that the existing magnetic field sensor is inconvenient to use.
In order to achieve the above object, the present invention provides a magnetic field sensor for airborne ground electromagnetic surveying, comprising:
the detector comprises a detector shell, a detector body and a detector body, wherein an installation cavity is formed inside the detector shell; and the number of the first and second groups,
the induction coil is arranged in the installation cavity and comprises a plurality of multi-core coils, each multi-core coil is provided with a head end wire head and a tail end wire head, the multi-core coils are sequentially arranged along the radial direction of the multi-core coil, the tail end wire head of each two adjacent multi-core coils is electrically connected to the head end wire head, and the head end wire head and the tail end wire head of each two multi-core coils at the end part are electrically connected;
wherein the number of turns of the induction coil is adjusted by adjusting the number of the multi-core coils.
Optionally, the probe housing includes an annular mounting tube, and an inner cavity of the annular mounting tube forms the mounting cavity.
Optionally, the annular installation pipeline includes a plurality of installation straight pipes and a plurality of connection return bends, and is a plurality of pass through between the installation straight pipe a plurality of connection return bends interconnect.
Optionally, the detector shell further includes a damping sleeve, the damping sleeve is sleeved in the mounting cavity, a damping cavity is formed in the damping sleeve, and a damping structure is arranged in the damping cavity;
the induction coil is arranged in the damping cavity.
Optionally, the damping sleeve comprises:
the shock absorption device comprises a support bottom tube, a shock absorption groove and a shock absorption groove, wherein the support bottom tube is provided with the shock absorption groove; and the number of the first and second groups,
and the shielding cover plate is covered at the opening of the damping groove and forms the damping cavity together with the damping groove.
Optionally, the detector shell further includes two elastic ribs, two ends of each elastic rib are fixed to the inner side wall of the damping cavity, the extending directions of the two elastic ribs are arranged in a cross manner, and the two elastic ribs are used for jointly bearing the induction coil to form the damping structure; and/or the presence of a gas in the gas,
and the damping cavity is filled with a damping elastic material to form the damping structure.
Optionally, two the elasticity rib forms a bearing group jointly, bearing group sets up a plurality ofly, a plurality ofly bearing group is along the extending direction interval setting of shock attenuation chamber.
Optionally, the magnetic field sensor further includes a front end amplifier, and the front end amplifier is electrically connected to the induction coil.
Optionally, an amplifying circuit is arranged in the front-end amplifier, and the amplifying circuit includes a first operational amplifier, a second operational amplifier, a first NPN type triode, a second NPN type triode, a three-terminal adjustable current source, and a first PNP type triode;
the output pin of the first operational amplifier is connected to an OP pin and an F pin;
an inverting input pin of the second operational amplifier is connected to an output pin of the first operational amplifier, and an output pin of the second operational amplifier is connected to a homonymous input pin of the first operational amplifier;
a collector of the first NPN type triode is connected to an inverting input pin of the first operational amplifier, and a base of the first NPN type triode is connected to a pin S1;
a collector of the second NPN type triode is connected to a same-direction input pin of the first operational amplifier, and a base of the second NPN type triode is connected to a pin S2;
the positive electrode of the three-terminal adjustable current source is connected to the first NPN type triode and the emitter of the second NPN type triode;
and the collector of the first PNP type triode is connected to the negative electrode of the three-end adjustable current source, and the emitter of the first PNP type triode is connected to the SC pin.
Optionally, the magnetic field sensor further includes a plurality of connecting ropes, each of the connecting ropes includes a connecting end and a mounting end, the connecting ends are arranged oppositely, the connecting ends are mounted on the detector housing at intervals, and the mounting ends are used for being arranged on an external aircraft; and/or the presence of a gas in the gas,
and a shielding material is arranged between the induction coil and the detector shell.
According to the technical scheme provided by the invention, the magnetic field sensor is used for aviation ground electromagnetic detection, the induction coil is arranged in the installation cavity, based on the Faraday electromagnetic induction principle, when an aviation aircraft moves, the magnetic flux in the environment is induced through the change of induction voltage, the induction coil comprises a plurality of multi-core coils, and different numbers of multi-core coils are selected and used according to different environments, so that the problem that the induction coil cannot be adjusted after the setting is finished is solved, and the magnetic field sensor is suitable for different environments.
Drawings
FIG. 1 is a schematic perspective view of a magnetic field sensor according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of the induction coil of FIG. 1;
FIG. 3 is an enlarged schematic view of the connection at A in FIG. 2;
FIG. 4 is a schematic view of a connection structure of the external cable shown in FIG. 3;
FIG. 5 is a schematic perspective view of the sonde housing of FIG. 1;
FIG. 6 is a schematic perspective view of the straight pipe assembly of FIG. 5;
FIG. 7 is a schematic perspective view of the connecting elbow of FIG. 5;
FIG. 8 is a perspective view of the shock absorbing sleeve of FIG. 5;
FIG. 9 is a perspective view of the support base of FIG. 8;
fig. 10 is a schematic diagram of an amplifying circuit of a front-end amplifier according to the present invention.
The reference numbers illustrate:
| reference numerals | Name (R) | Reference numerals | Name (R) |
| 100 | |
13 | |
| 1 | |
2 | |
| 11 | |
21 | |
| 11a | Mounting |
21a | Head |
| 11b | Connecting |
21b | Tail |
| 12 | |
3 | |
| 121 | |
4 | Front- |
| 122 | |
5 | Connecting rope |
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to specific embodiments and the accompanying drawings.
It should be noted that, if directional indication is involved in the embodiment of the present invention, the directional indication is only used for explaining the relative positional relationship, the motion situation, and the like between the components in a certain posture, and if the certain posture is changed, the directional indication is changed accordingly.
In addition, if there is a description of "first", "second", etc. in an embodiment of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
The aerial earth electromagnetic detection system utilizes the audio frequency band and the low-frequency band weak natural electromagnetic field signals with huge energy and widely and uniformly distributed to detect the underground target body. It has become a new trend of aviation geophysical exploration with high efficiency and large depth exploration. The key point of successful application of the aviation ground electromagnetic detection system lies in developing a low-noise magnetic field sensor which can be used for detecting weak natural field underground target response signals, and performing noise matching optimization on a platform, a receiver and a data processing method to improve the detection precision and stability of the electromagnetic field on an aviation dynamic platform.
The induction type magnetic field sensor is a magnetic field sensor with wide frequency band, high sensitivity and stable performance, and is widely applied to the fields of geophysical exploration, space detection, environment monitoring and the like. In recent years, with the development of high-precision aviation magnetotelluric methods, magnetic field measurement in a direction perpendicular to the ground surface plane has been receiving increased attention and attention. The magnetic field component in the direction is weaker than the horizontal component, and due to the restriction of physical principles, the sensitivity of the existing induction type magnetic field sensor is in direct proportion to the volume, length and weight of the sensor, and meanwhile, the realization of high sensitivity and miniaturization is very difficult, and the parameters of the sensor cannot be adjusted according to different geological conditions.
The present invention provides a magnetic field sensor, which aims to solve the problem that the existing magnetic field sensor is inconvenient to use, wherein fig. 1 to 10 are an embodiment provided by the present invention.
Referring to fig. 1 to 2, the present invention provides a magnetic field sensor 100 for airborne ground electromagnetic detection, including a detector housing 1 and an induction coil 2; a mounting cavity is formed inside the detector shell 1, the induction coil 2 is arranged in the mounting cavity, the induction coil 2 includes a plurality of multi-core coils 21, each multi-core coil 21 is formed with a head end stub 21a and a tail end stub 21b, the plurality of multi-core coils 21 are sequentially arranged along the radial direction of the multi-core coil, in two adjacent multi-core coils 21, the tail end stub 21b is electrically connected to the head end stub 21a, and the head end stubs 21a and the tail end stubs 21b of the two multi-core coils 21 at the end are electrically connected; wherein the number of turns of the induction coil is adjusted by adjusting the number of the multi-core coils.
In the technical scheme provided by the invention, the magnetic field sensor 100 is used for aviation ground electromagnetic detection, the induction coil 2 is arranged in the installation cavity, based on the faraday electromagnetic induction principle, when an aviation aircraft moves, magnetic flux in the environment is induced through the change of induction voltage, the induction coil 2 comprises a plurality of multi-core coils 21, and different numbers of multi-core coils 21 are selected and used according to different environments, so that the problem that the induction coil 2 cannot be adjusted after the setting is finished is avoided, and the magnetic field sensor is suitable for different environments.
It should be noted that the selection of the multi-core coil 21 may be selected according to actual situations, and the number of cables in the used multi-core coil 21 or the number of cables in the multi-core coil 21 may be adjusted according to different application environments and application parameters, so as to reduce interference by grounding the cables in the unused multi-core coil 21 through shielding.
Referring to fig. 3 to 4, in the present embodiment, taking the number of cables in the multi-core coil 21 as 40 cores as an example, the multi-core coil 21 is configured with 4 turns, wherein 37 cores in each multi-core coil 21 are connected to a circuit signal input terminal, and 3 cores are connected to a circuit ground as a shield.
In addition, in two adjacent multicore coils 21, tail end stub 21b electric connection to head end stub 21a docks through crimping or through the plug connector, the plug connector only need guarantee make tail end stub 21b with head end stub 21a dock can, and it is no longer repeated here.
In the present embodiment, the head ends 21a and the tail ends 21b of the two multi-core coils 21 at the ends are electrically connected by the external connection cable 3.
Referring to fig. 5, in the present embodiment, the probe casing 1 includes an annular mounting pipe 11, and an inner cavity of the annular mounting pipe 11 forms the mounting cavity. So that the induction coil 2 is disposed in the installation cavity, and the annular structure of the induction coil 2 is ensured to be stable, and the weight and volume of the detector housing 1 are reduced, thereby facilitating the use of the magnetic field sensor 100.
Further, referring to fig. 6 to 7, the annular installation pipeline 11 includes a plurality of installation straight pipes 11a and a plurality of connection bent pipes 11b, and the installation straight pipes 11a are connected to each other through the connection bent pipes 11 b. With forming annular installation pipeline 11, and pass through installation straight tube 11a with connecting bend 11b concatenation forms, is convenient for annular installation pipeline 11's installation and transportation, detachable transportation back splice when using, simultaneously, can select the installation straight tube 11a of different quantity to the condition of difference with connecting bend 11b to form not annular installation pipeline 11 of equidimension.
It should be noted that there are various connection manners between the installation straight tube 11a and the connection bent tube 11b, such as bolting, inserting, etc., in this embodiment, the installation straight tube 11a is inserted into the connection bent tube 11b and is fixed by bolts.
On the other hand, referring to fig. 8, the detector housing 1 further includes a damping sleeve 12, the damping sleeve 12 is sleeved in the mounting cavity, a damping cavity is formed in the damping sleeve 12, and a damping structure is disposed in the damping cavity; the induction coil 2 is arranged in the damping cavity. Will induction coil 2 is provided with in the shock attenuation chamber, prevent induction coil 2 from being in produce in the annular installation pipeline 11 and rock, and then lead to producing vibration noise.
Specifically, the damping sleeve 12 includes a supporting bottom tube 121 and a shielding cover plate 122; a damping groove is formed on the supporting bottom tube 121; the shielding cover plate 122 covers the opening of the damping groove, and forms the damping cavity together with the damping groove. So as to facilitate the installation of the induction coil 2 into the damping chamber.
In an embodiment of the present invention, referring to fig. 9, the detector housing 1 further includes two elastic ribs 13, two of the elastic ribs 13 are disposed, two ends of each elastic rib 13 are fixed on an inner side wall of the damping cavity, extending directions of the two elastic ribs 13 are arranged in a cross manner, and the two elastic ribs 13 are used for jointly supporting the induction coil to form the damping structure. Two elastic ribs 13 are arranged in a crossed manner to form a cross point, the induction coil 2 is dragged on the cross point, when the detector is used, the induction coil 2 only has downward force actually, and a certain supporting force can be provided when the detector shell 1 vibrates by dragging the induction coil 2, so that the stability of the induction coil 2 is ensured.
Also, the shock-absorbing cavity is filled with a shock-absorbing elastic material to form the shock-absorbing structure. The damping elastic material prevents the induction coil 2 from shaking in the damping chamber. Specifically, in this embodiment, the damping elastic material is a sponge material, which is cheap and has a good damping effect.
It should be noted that the above-mentioned two technical features related to the use of elastic ribs 13 and of the shock-absorbing elastic material can be alternatively present or present at the same time, and it is obvious that the technical effect brought by the presence of the same time is the best.
Furthermore, two elastic ribs 13 form a bearing group together, the bearing group is provided with a plurality of bearing groups, and the plurality of bearing groups are arranged at intervals along the extension direction of the damping cavity. In order to protect the induction coil 2.
It should be noted that the damping sleeve 12 may be made of various materials, such as PVC, polyoxymethylene or PEAK, and is not limited in this regard.
In addition, in order to amplify the weak magnetic field signal induced by the coil, the magnetic field sensor 100 further includes a front end amplifier 4, and the front end amplifier 4 is electrically connected to the induction coil 2. So as to realize the signal amplification of weak magnetic field signals.
In this embodiment, after the multi-core coils 21 are connected, the head ends 21a and the tail ends 21b of the two multi-core coils 21 at the ends are electrically connected through the external cable 3, and further connected to the front-end amplifier 4.
Specifically, referring to fig. 10, an amplifying circuit is disposed in the front-end amplifier 4, and the amplifying circuit includes a first operational amplifier, a second operational amplifier, a first NPN type triode, a second NPN type triode, a three-terminal adjustable current source, and a first PNP type triode; the output pin of the first operational amplifier is connected to an OP pin and an F pin; an inverting input pin of the second operational amplifier is connected to an output pin of the first operational amplifier, and an output pin of the second operational amplifier is connected to a homonymous input pin of the first operational amplifier; a collector of the first NPN type triode is connected to an inverting input pin of the first operational amplifier, and a base of the first NPN type triode is connected to a pin S1; a collector of the second NPN type triode is connected to a same-direction input pin of the first operational amplifier, and a base of the second NPN type triode is connected to a pin S2; the positive electrode of the three-terminal adjustable current source is connected to the first NPN type triode and the emitter of the second NPN type triode; and the collector of the first PNP type triode is connected to the negative electrode of the three-end adjustable current source, and the emitter of the first PNP type triode is connected to the SC pin. The low-noise amplification circuit adopts BJTs or FET pair transistors to build an instrument amplifier, the voltage noise is less than 4 nV/V Hz, the current noise is less than 0.1 pA/V Hz, the maximum working bandwidth is 0.1Hz-10kHz, the low-frequency and high-frequency noise of the sensor can be well considered, the low-noise requirement of the sensor in the whole bandwidth is met, and the identification capability of low-frequency weak signals of the sensor is greatly improved.
In addition, for the convenience of the use of magnetic field sensor 100, magnetic field sensor 100 still includes many connecting rope 5, each connecting rope 5 all includes the link and the installation end that are relative setting, and is a plurality of the link interval is installed extremely on detector housing 1, it is a plurality of the installation end is used for locating on the external aircraft. The magnetic field sensor 100 is driven to move in the air through the connecting rope 5 so as to detect the magnetic field.
In this embodiment, a shielding material is disposed between the induction coil 2 and the detector housing 1, and the shielding material is provided with multiple embodiments, specifically, in an embodiment provided by the present invention, a copper foil is spirally wound around the induction coil 2 as a center, and the thickness of the copper foil is controlled to be 0.1mm to 0.66mm, so as to satisfy the working bandwidth of the sensor; in another embodiment provided by the invention, the sensor cable is wrapped by a braided shielding paper, for example, a copper shielding paper, and the thickness of the braided shielding paper is 0.1mm-0.66 mm. The shielding material is single point grounded at the cable joint.
It should be noted that the above-mentioned two related technical features of the connecting cord 5 and the shielding material may be present alternatively or simultaneously, and it is obvious that the technical effect brought by the simultaneous presence is the best.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A magnetic field sensor for airborne ground electromagnetic surveying, comprising:
the detector comprises a detector shell, a detector body and a detector body, wherein an installation cavity is formed inside the detector shell; and the number of the first and second groups,
the induction coil is arranged in the installation cavity and comprises a plurality of multi-core coils, each multi-core coil is provided with a head end wire head and a tail end wire head, the multi-core coils are sequentially arranged along the radial direction of the multi-core coil, the tail end wire head of each two adjacent multi-core coils is electrically connected to the head end wire head, and the head end wire head and the tail end wire head of each two multi-core coils at the end part are electrically connected;
wherein the number of turns of the induction coil is adjusted by adjusting the number of the multi-core coils.
2. The magnetic field sensor of claim 1, wherein the probe housing comprises an annular mounting tube, an inner cavity of the annular mounting tube forming the mounting cavity.
3. The magnetic field sensor according to claim 2, wherein said annular mounting conduit comprises a plurality of mounting straight tubes and a plurality of connecting bent tubes, wherein a plurality of said mounting straight tubes are connected to each other by a plurality of said connecting bent tubes.
4. The magnetic field sensor according to claim 2, wherein the probe housing further comprises a shock absorbing sleeve, the shock absorbing sleeve is sleeved in the mounting cavity, a shock absorbing cavity is formed in the shock absorbing sleeve, and a shock absorbing structure is arranged in the shock absorbing cavity;
the induction coil is arranged in the damping cavity.
5. The magnetic field sensor of claim 4, wherein the shock absorbing sleeve comprises:
the shock absorption device comprises a support bottom tube, a shock absorption groove and a shock absorption groove, wherein the support bottom tube is provided with the shock absorption groove; and the number of the first and second groups,
and the shielding cover plate is covered at the opening of the damping groove and forms the damping cavity together with the damping groove.
6. The magnetic field sensor according to claim 4, wherein the detector housing further comprises two elastic ribs, two ends of each elastic rib are fixed on the inner side wall of the damping cavity, the extending directions of the two elastic ribs are arranged in a cross manner, and the two elastic ribs are used for jointly bearing the induction coil to form the damping structure; and/or the presence of a gas in the gas,
and the damping cavity is filled with a damping elastic material to form the damping structure.
7. The magnetic field sensor according to claim 6, wherein two of said elastic ribs together form a plurality of load-bearing groups, and a plurality of said load-bearing groups are arranged at intervals along the extension direction of said damping chamber.
8. The magnetic field sensor of claim 1, further comprising a front end amplifier electrically connected to the sense coil.
9. The magnetic field sensor according to claim 8, wherein an amplification circuit is disposed within the front-end amplifier, the amplification circuit comprising a first operational amplifier, a second operational amplifier, a first NPN transistor, a second NPN transistor, a three-terminal adjustable current source, and a first PNP triode;
the output pin of the first operational amplifier is connected to an OP pin and an F pin;
an inverting input pin of the second operational amplifier is connected to an output pin of the first operational amplifier, and an output pin of the second operational amplifier is connected to a homonymous input pin of the first operational amplifier;
a collector of the first NPN type triode is connected to an inverting input pin of the first operational amplifier, and a base of the first NPN type triode is connected to a pin S1;
a collector of the second NPN type triode is connected to a same-direction input pin of the first operational amplifier, and a base of the second NPN type triode is connected to a pin S2;
the positive electrode of the three-terminal adjustable current source is connected to the first NPN type triode and the emitter of the second NPN type triode;
and the collector of the first PNP type triode is connected to the negative electrode of the three-end adjustable current source, and the emitter of the first PNP type triode is connected to the SC pin.
10. The magnetic field sensor according to claim 1, wherein the magnetic field sensor further comprises a plurality of connecting ropes, each connecting rope comprises a connecting end and a mounting end which are oppositely arranged, the connecting ends are mounted on the detector shell at intervals, and the mounting ends are used for being arranged on an external aircraft; and/or the presence of a gas in the gas,
and a shielding material is arranged between the induction coil and the detector shell.
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| CN104020497A (en) * | 2014-06-24 | 2014-09-03 | 吉林大学 | Z component receiving device for airborne Z-axis tipper electromagnetic survey system |
| 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 |
| CN106199741A (en) * | 2016-07-04 | 2016-12-07 | 哈尔滨工业大学 | A kind of pod propulsion time domain aviation transient electromagnetic exploration system based on lightweight gas tube supporting construction |
| US20200241163A1 (en) * | 2019-01-25 | 2020-07-30 | Geotech Ltd. | Natural em source airborne geophysical surveying system |
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