CN108562942B - Time domain aeroelectromagnetic method receiving coil attitude change suppression device and manufacturing method - Google Patents
Time domain aeroelectromagnetic method receiving coil attitude change suppression device and manufacturing method Download PDFInfo
- Publication number
- CN108562942B CN108562942B CN201810087314.8A CN201810087314A CN108562942B CN 108562942 B CN108562942 B CN 108562942B CN 201810087314 A CN201810087314 A CN 201810087314A CN 108562942 B CN108562942 B CN 108562942B
- Authority
- CN
- China
- Prior art keywords
- receiving coil
- connecting point
- coil
- point
- binding rope
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Life Sciences & Earth Sciences (AREA)
- Electromagnetism (AREA)
- Environmental & Geological Engineering (AREA)
- Geology (AREA)
- General Life Sciences & Earth Sciences (AREA)
- General Physics & Mathematics (AREA)
- Geophysics (AREA)
- Geophysics And Detection Of Objects (AREA)
Abstract
The invention relates to a device for inhibiting the attitude change of a time domain aeroelectromagnetic receiving coil and a manufacturing method thereof. The flexible or rigid binding rope is connected with the bearing point of the receiving coil along the radial direction of the receiving coil and the flexible binding rope is connected with the bearing point of the receiving coil along the axial direction of the receiving coil, so that the attitude balance of the receiving coil is ensured, the binding rope enables the receiving coil not to generate moment in the pitching and rolling directions, and the generation of motion noise is fundamentally inhibited. The damping fluid is utilized to play a role in vibration isolation, the moving resistance of the receiving coil is increased, the spatial displacement of the receiving coil is further limited, and the primary field compensation effect is improved. The limitation of application is overcome.
Description
The technical field is as follows:
the invention relates to a device for inhibiting the attitude change of a receiving coil of a helicopter time domain aeroelectromagnetic method, in particular to a time domain electromagnetic detection receiving device of a pod type helicopter.
Background art:
the time domain electromagnetic detection device of the pod type helicopter takes the helicopter as a carrier and carries a transmitting coil, a compensating coil and a receiving coil through a hanging rope. The transmitting coil can transmit bipolar periodic heavy current with fixed frequency to excite the eddy current effect of the underground medium to generate a changed magnetic field signal, the receiving coil receives the changed magnetic field signal, the changed magnetic field signal is acquired in real time through the receiving system, and then the acquired data is processed and interpreted to complete geological exploration. When the bipolar periodic heavy current passes through the transmitting coil, the bipolar periodic heavy current reversely flows through the compensating coil, so that a weak magnetic environment under the condition of large transmitting current is provided for the receiving coil, the saturation of an amplifier is avoided, a receiving circuit is protected, and the process is called primary field compensation; in order to ensure the primary field compensation effect, the space displacement of the receiving coil should be limited within a certain range. In the helicopter flight detection process, based on Faraday's law of electromagnetic induction, when the receiving coil receives underground medium magnetic field signals, the receiving coil cuts the geomagnetic field due to changes of pitch angles and roll angles caused by mechanical vibration, so that motion noise is mixed in, and the detection effect is seriously deteriorated. The motion noise is the same as the texture generated by a detection magnetic field signal, and the method for eliminating the motion noise through data processing has little effect, so that the change of the pitch angle and the roll angle of a receiving coil is limited on a mechanical structure from a motion noise source, the attitude change of the receiving coil is restrained, and the motion noise is weakened, thereby being an important research direction in a helicopter time domain electromagnetic method.
CN 104865608B discloses a time domain aeroelectromagnetic method motion noise detection apparatus and suppression method, which obtains motion noise by measuring geomagnetic field and receiving coil attitude information at the same time, and then eliminates the motion noise influence by a data processing method, however, a new noise source is introduced by measuring geomagnetic field and receiving coil attitude in real time, and the detection precision is limited, and the effective implementation is difficult;
CN 105204076B, "helicopter transient electromagnetic detection motion noise suppression device and noise suppression method" calculates and obtains the corresponding physical parameters of the damping structure through the mechanical damping principle, rationally designs the mechanical structure, then combines the digital filtering method to suppress the motion noise, combines the data processing method through the damping principle, has quite strict requirements on the mechanical damping structure and the material parameters, and has a plurality of problems in the material selection and the manufacturing and installation process. In High performance rotational vibration isolator published by AndrewSunderland et al, university of western and australia, 2013 (a. sunderland et al, "High performance rotational vibration isolator," review of Scientific Instruments, vol.84, (10), pp.105111,2013.), a ball-type vibration isolator is disclosed, which achieves the effect of vibration isolation of a sensor by injecting damping liquid into a ball body and simultaneously applying spring damping, but the ball-type vibration isolator has a complicated structure and is difficult to install in a helicopter time domain electromagnetic detection system, thereby failing to achieve primary field compensation. In 2013, the company GEOTECH discloses "DOUBLE-speed RECEIVER COIL SYSTEM and application data unit of WO 2009/135296 a 1. by designing a two-stage rope damping device, the vibration isolation effect of a receiving COIL based on a helicopter platform is realized, and the purpose of suppressing motion noise is achieved.
The invention content is as follows:
the invention aims to solve the problem that the prior receiving coil introduces motion noise due to the change of a pitch angle and a roll angle caused by vibration in the flying process, and provides a device for restraining the space displacement of the receiving coil by the attitude change of the receiving coil, so that the device is suitable for a hard bracket or a soft bracket in a central mode or an eccentric mode, weakens the motion noise by reducing the moments in the pitch direction and the roll direction, and is suitable for a device for restraining the attitude change of the receiving coil in a helicopter time domain aeroelectromagnetic method;
the invention also aims to provide a manufacturing method of the device for inhibiting the attitude change of the receiving coil of the helicopter in the time domain aeroelectromagnetic method.
The invention aims to overcome the problems of poor damping effect and even vibration aggravation of a traditional helicopter time domain electromagnetic damping device caused by uneven stress distribution of a damping structure, overcomes the gravity of a receiving coil through a vertical direction binding chain of the damping device, limits the displacement of the receiving coil through a horizontal direction binding chain, ensures the primary field compensation effect, avoids the moment of the receiving coil in the pitch angle and roll angle directions, and fundamentally avoids introducing motion noise.
The purpose of the invention is realized by the following technical scheme:
the attitude change suppression device for the helicopter time domain aeroelectromagnetic method receiving coil consists of an upper fixed support 51, a receiving coil 52 and a lower fixed support 54, wherein the receiving coil 5 with the attitude change suppression device is formed by uniformly arranging a connecting point 511, a connecting point 512, a connecting point 513, a connecting point 514, a connecting point 515 and a connecting point 516 on the inner circumferential surface of the fixed support 51, and a receiving coil bearing connecting point 517 is arranged at the central point of the circular inner surface of the top layer; the radial cross section of the receiving coil 52 is circular, the receiving coil 52 is wound in the axial direction of the receiving coil in a differential structure, fixed connection points 521-526 are uniformly arranged on the outer surface of the circumference of the receiving coil, and a receiving coil bearing connection point 527 is arranged at the center point of the circular outer surface of the top layer of the receiving coil; the constraint structure is composed of nonmagnetic rigid or flexible ropes, the constraint ropes are composed of 531-536, and respectively form constraint chains of the receiving coil in the radial direction by 511-; the upper fixing bracket 51, the receiver coil 52 and the tether rope constitute a damper chamber 55.
The manufacturing method of the device for inhibiting the attitude change of the receiving coil of the helicopter in the time domain by the aeroelectromagnetic method comprises the following steps:
A. determining whether the transmitting coil 3, the compensating coil 4 and the receiving coil are in a concentric mode or an eccentric mode according to an aerial survey task, and determining the size of the receiving coil according to the compensation effect requirement of a high-current primary field;
B. according to the size of the receiving coil, a disc-shaped coil is made of nonmagnetic materials, connection points 521, 522, 523, 524, 525 and 526 are uniformly distributed on the circumferential outer surface of the disc-shaped coil, and a gravity bearing point 527 of the receiving coil is arranged at the center of the disc-shaped coil;
C. according to the size of the receiving coil 52, the sizes of the upper fixing support 51 and the lower fixing support 54 are determined, a receiving coil bearing point 517 is arranged at the center of the upper fixing support and axially corresponds to the receiving coil gravity bearing point 527, connection points 511, 512, 513, 514, 515 and 516 are uniformly distributed on the circumference of the inner surface of the upper fixing support and radially correspond to the receiving coil connection points 521, 522, 523, 524 and 526 one to one;
D. flexible or rigid binding ropes 531, 532, 533, 534, 535, 536 are used for sequentially linking the connecting points 511 and 521, 512 and 522, 513 and 523, 514 and 524, 515 and 525, 516 and 526 along the radial direction of the receiving coil; flexible or rigid constraining ropes 537 are axially linked with the receiver coil bearing points 517-527 along the receiver coil to ensure that all constraining ropes have no moment in the pitch and roll directions of the receiver coil;
E. fixing an upper fixing support 51 and a lower fixing support 54 through nylon screws, forming a damping cavity 55 in the middle space between the upper fixing support 51 and the lower fixing support 54, and manufacturing a receiving coil sensor 5 with a posture change suppression device;
F. the helicopter 1 is provided with a transmitting coil 3, a compensating coil 4 and a receiving coil sensor 5 with an attitude change inhibiting device through a hanging rope 2; the magnetic field signal received by the sensor is transmitted to a receiving system 7 in the cabin by a cable 6, and is collected and stored in real time;
G. after the flight mission is completed, ground staff carries out subsequent processing on the acquired data to complete geological exploration work.
Has the advantages that: the invention is made of nonmagnetic materials, does not introduce electromagnetic interference and has no influence on the detection result. Receiving coils with different sizes and a receiving coil posture change suppression device are selected according to primary field compensation requirements, and after the receiving coils are linked through flexible or rigid binding ropes 531-536, the spatial positions of the receiving coils are limited, and a primary field compensation effect is guaranteed.
The attitude balance of the receiving coil is ensured by sequentially linking the connecting points 511 and 521, 512 and 522, 513 and 523, 514 and 524, 515 and 525 and 516 and 526 by the flexible or rigid binding ropes 531-536 along the radial direction of the receiving coil and linking the bearing point 517 and 527 of the receiving coil by the flexible or rigid binding ropes 537 along the axial direction of the receiving coil, and the design of the binding ropes ensures that the receiving coil does not generate moment in the pitching and rolling directions, thereby fundamentally inhibiting the generation of motion noise. The damping fluid is utilized to play a role in vibration isolation, the moving resistance of the receiving coil is increased, the spatial displacement of the receiving coil is further limited, and the primary field compensation effect is improved. The receiving coil sensor 5 with the attitude change suppression device can be suitable for a hard support or soft support helicopter time domain electromagnetic detection system in a central mode or an eccentric mode, can meet the requirements of different systems in different modes, and overcomes the limitation of application.
Description of the drawings:
FIG. 1 helicopter time domain electromagnetic method detection principle
FIG. 2 shows that the helicopter time domain aeroelectromagnetic method receiving coil attitude changes the suppression device
FIG. 3 is a front view of a device for suppressing changes in attitude of a time-domain aeroelectromagnetic receiving coil of a helicopter
FIG. 4 is a top view of a device for suppressing changes in attitude of a time-domain aeroelectromagnetic receiving coil of a helicopter
The system comprises a helicopter 1, a hanging rope 2, a transmitting coil 3, a compensating coil 4, a receiving coil 5 with an attitude change suppression device, a cable 6 and a receiving system 7; 51 upper fixed support, 52 receiving coil, 54 lower fixed support, 55 damping chamber;
511, 512, 513, 514, 515, 516, 517, and a receiving coil bearing connection point;
521, 522, 523, 524, 525, 526 and 527, respectively, receiving an upper coil connection point, a lower coil connection point, and a lower coil connection point;
531 restraint ropes, 532 restraint ropes, 533 restraint ropes, 534 restraint ropes, 535 restraint ropes, 536 restraint ropes, 537 load-bearing ropes;
the specific implementation mode is as follows:
the invention is described in further detail below with reference to the following figures and examples:
the device for inhibiting the attitude change of the receiving coil of the helicopter in the time domain aeroelectromagnetic method comprises a fixed support, the receiving coil and a binding structure. The fixed bracket 51 and the fixed bracket base 54 are made of nonmagnetic materials, the inner circumferential surface of the fixed bracket is uniformly provided with fixed connection points 511, 512, 513, 514, 515 and 516, and the central point of the circular inner surface of the top layer of the fixed bracket 51 is provided with a receiving coil bearing connection point 517; the receiving coil 52 is made of nonmagnetic material, the radial cross section of the receiving coil is circular, the receiving wire is wound in the axial direction of the receiving wire in a differential structure, the circumferential outer surface of the receiving wire is uniformly provided with fixed connection points 521, 522, 523, 524, 525 and 526, and the central point of the circular outer surface of the top layer of the receiving coil is provided with a receiving coil bearing connection point 527; the constraint structure is a nonmagnetic rigid or flexible rope and consists of 531, 532, 533, 534, 535 and 536, and is respectively connected in a manner of 511-; the 7 binding chains limit the spatial position of the receiving coil, so that the large-current primary field compensation effect is ensured, meanwhile, the moments of the receiving coil in the pitching and rolling directions cannot be generated, and the generation of motion noise is avoided. The middle area of the device consisting of the fixed support, the receiving coil and the binding structure has a part of gap, and non-magnetic damping liquid 55 can be injected according to the requirement of actual conditions to form the receiving coil sensor 5 with the attitude change suppression device.
A receiving coil sensor 5 with an attitude change suppression device, a compensation coil 4 and a transmitting coil 3 form a pod device of a helicopter time domain electromagnetic detection system, and the pod device is carried by a helicopter 1 to fly through a hanging rope 2; in the flight process, electromagnetic signals acquired by the receiving coil are transmitted to a receiving system 7 in the cabin through a cable 6, data acquisition and storage are completed, and a geological exploration task is completed through subsequent data processing.
The manufacturing method of the device for inhibiting the attitude change of the receiving coil of the helicopter in the time domain by the aeroelectromagnetic method comprises the following steps:
A. determining whether the transmitting coil 3, the compensating coil 4 and the receiving coil are in a concentric mode or an eccentric mode, and determining the size of the receiving coil according to the requirement of a large-current primary field compensation effect;
B. according to the size of the receiving coil, a disc-shaped coil is made of nonmagnetic materials, uniformly distributed connection points 521, 522, 523, 524, 525 and 526 are arranged in the middle of the axis of the outer circumferential surface of the disc-shaped coil, and a gravity bearing point 527 of the receiving coil is arranged in the center of the circular area on the top layer of the disc-shaped coil;
C. determining the size of the fixed bracket 51 according to the size of the receiving coil, manufacturing the fixed bracket by using a nonmagnetic material, and arranging a receiving coil bearing point 517 at the center of a top-layer circular area on the inner surface of the fixed bracket, wherein the receiving coil bearing point 517 corresponds to a receiving coil gravity bearing point 527, and the connection direction of the two points is along the axial direction of the receiving coil; uniformly distributed connection points 511, 512, 513, 514, 515 and 516 and a receiving coil connection point 521 are arranged on the circumferential area of the inner surface of the antenna; 522; 523; 524; 526; 526 are in one-to-one correspondence, ensuring that the radial direction of the receiving coil is ensured;
E. the fixed support 51 and the fixed support base 54 are fixed through nylon screws, and nonmagnetic damping liquid 55 is injected into a gap between the fixed support 51 and the fixed support base 54 according to the requirement of actual conditions to form the receiving coil sensor 5 with the attitude change suppression device;
F. the helicopter 1 is provided with a transmitting coil 3, a compensating coil 4 and a receiving coil sensor 5 with an attitude change inhibiting device through a hanging rope 2; the magnetic field signal received by the sensor is transmitted to a receiving system 7 in the cabin by a cable 6, and is collected and stored in real time;
G. after the flight mission is completed, ground staff carries out subsequent processing on the acquired data to complete geological exploration work.
The receiving coil sensor 5 with the attitude change suppression device is made of a completely nonmagnetic material, and the interior of the receiving coil sensor is sequentially linked with the connecting points 511 and 521, 512 and 522, 513 and 523, 514 and 524, 515 and 525 and 516 and 526 along the radial direction of the receiving coil by flexible or rigid binding ropes 531, 532, 533, 534, 535 and 536; the receiver coil bearing points 517 and 527 are linked in the receiver coil axial direction by flexible or rigid tie-down ropes 537. The receiving coils are respectively connected and restrained from the radial direction and the axial direction of the receiving coils through restraint chains 511, 531, 512, 532, 522, 513, 533, 523, 514, 534, 524, 515, 535, 525, 516, 536, 526 and 517, and the nonmagnetic damping liquid 55 realizes the vibration isolation of the receiving coils and increases the moving resistance of the receiving coils, and firstly, the attitude balance of the receiving coils is ensured; secondly, all the binding ropes do not generate moment in the pitch and roll directions of the receiving coil, so that the generation of motion noise is fundamentally inhibited; in addition, the binding rope realizes primary field compensation by limiting the spatial position of the receiving coil, so that the binding rope can be suitable for a time domain electromagnetic detection system of a hard bracket or a soft bracket helicopter in a central mode or an eccentric mode, the requirements of different systems in different modes can be met, and the application limitation is overcome.
Example 1
For a time domain electromagnetic detection system of a soft support helicopter in a central mode, a transmitting coil 3 and a compensating coil 4 are concentric circle structures in the same plane, and the size of a receiving coil 52 is calculated based on the size of the transmitting coil and the size of a fixed support 51 and the size of a fixed support base 54 by utilizing a primary field compensation principle.
After the size is determined, the material is made of a completely nonmagnetic material.
Uniformly distributed connecting points 521, 522, 523, 524, 525 and 526 are manufactured at the middle position of the axis of the circumferential outer surface of the receiving coil, and a gravity bearing point 527 of the receiving coil is manufactured at the central position of the circular area of the top layer.
A receiving coil bearing point 517 is arranged at the center of a top circular area on the inner surface of the fixed support 51, the receiving coil bearing point is corresponding to a receiving coil gravity bearing point 527, and the connection direction of the two points is along the axial direction of the receiving coil; uniformly distributed connection points 511, 512, 513, 514, 515 and 516 and a receiving coil connection point 521 are arranged on the circumferential area of the inner surface of the antenna; 522; 523; 524; 526; 526 are in one-to-one correspondence, ensuring that the radial direction of the receiving coil is ensured;
connecting points 511 and 521, 512 and 522, 513 and 523, 514 and 524, 515 and 525 and 516 and 526 are sequentially linked along the radial direction of the receiving coil by using flexible or rigid binding ropes 531, 532, 533, 534, 535 and 536; the receiver coil bearing points 517 and 527 are linked in the receiver coil axial direction by flexible or rigid tie-down ropes 537.
Debugging all the binding ropes, ensuring that the 517-; completely eliminating the pitch and roll direction moments of the receiving coils.
The fixed bracket 51 is fixed to the fixed bracket base 54, and the reception coil sensor 5 with the attitude change suppression device is assembled.
A receiving coil sensor 5 with an attitude change suppression device is arranged in a plane formed by the transmitting coil 3 and the compensating coil 4 and is arranged at the center of a concentric circle, and the transmitting coil, the transmitting coil and the compensating coil form a concentric mode.
A transmitting coil 3, a compensating coil 4, and a receiving coil sensor 5 with an attitude change suppressing device are bound by a hanging rope 2, and are mounted on a helicopter 1.
And the magnetic field signal received by the sensor is transmitted to a receiving system 7 in the cabin by using a cable 6 for real-time acquisition and storage.
And carrying out a flight detection task, and after the flight detection is finished, handing the data stored by the receiving system 7 to ground workers for data processing and interpretation to finish the geological exploration work.
Example 2
For the time domain electromagnetic detection system of the helicopter with the eccentric mode, the transmitting coil 3 and the compensating coil 4 are eccentric circular structures in the same plane, and the size of the receiving coil 52 is calculated by utilizing a primary field compensation principle based on the structure and the size of the eccentric circular structures, so that the sizes of the fixed support 51 and the fixed support base 54 are determined.
After the size is determined, the material is made of a completely nonmagnetic material.
Uniformly distributed connecting points 521, 522, 523, 524, 525 and 526 are manufactured at the middle position of the axis of the circumferential outer surface of the receiving coil, and a gravity bearing point 527 of the receiving coil is manufactured at the central position of the circular area of the top layer.
A receiving coil bearing point 517 is arranged at the center of a top circular area on the inner surface of the fixed support 51, the receiving coil bearing point is corresponding to a receiving coil gravity bearing point 527, and the connection direction of the two points is along the axial direction of the receiving coil; uniformly distributed connection points 511, 512, 513, 514, 515 and 516 and a receiving coil connection point 521 are arranged on the circumferential area of the inner surface of the antenna; 522; 523; 524; 526; 526 are in one-to-one correspondence, ensuring that the radial direction of the receiving coil is ensured;
connecting points 511 and 521, 512 and 522, 513 and 523, 514 and 524, 515 and 525 and 516 and 526 are sequentially linked along the radial direction of the receiving coil by using flexible or rigid binding ropes 531, 532, 533, 534, 535 and 536; the receiver coil bearing points 517 and 527 are linked in the receiver coil axial direction by flexible or rigid tie-down ropes 537.
Debugging all the binding ropes, ensuring that the 517-; completely eliminating the pitch and roll direction moments of the receiving coils.
The fixed bracket 51 and the fixed bracket base 54 are fixed, and then a nonmagnetic liquid damping material (e.g., kerosene, distilled water, etc.) is injected into the intermediate cavity formed by the combination, and a sealing treatment is performed, thereby completing the fabrication of the receiving coil sensor 5 with the attitude change suppression device.
A receiving coil sensor 5 with an attitude change suppression device is arranged in a plane formed by the transmitting coil 3 and the compensating coil 4 and is arranged at the position of the center of a circle of the compensating coil 4, and the transmitting coil sensor, the receiving coil sensor and the compensating coil form an eccentric structure in the same plane.
A transmitting coil 3, a compensating coil 4, and a receiving coil sensor 5 with an attitude change suppressing device are bound by a hanging rope 2, and are mounted on a helicopter 1.
And the magnetic field signal received by the sensor is transmitted to a receiving system 7 in the cabin by using a cable 6 for real-time acquisition and storage.
And carrying out a flight detection task, and after the flight detection is finished, handing the data stored by the receiving system 7 to ground workers for data processing and interpretation to finish the geological exploration work.
Claims (2)
1. A posture change suppression device of a time domain aeroelectromagnetic method receiving coil is composed of an upper fixing support (51), a receiving coil (52) and a lower fixing support (54), and is characterized in that an upper fixing support connecting point a (511), an upper fixing support connecting point b (512), an upper fixing support connecting point c (513), an upper fixing support connecting point d (514), an upper fixing support connecting point e (515) and an upper fixing support connecting point f (516) are uniformly arranged on the inner circumferential surface of the upper fixing support (51), and a receiving coil bearing connecting point (517) is arranged at the center point of the circular inner surface of the top layer; the radial cross section of the receiving coil (52) is circular, the receiving coil (52) is wound in the axial direction of the receiving coil in a differential structure, the circumferential outer surface of the receiving coil is uniformly provided with a receiving coil upper connecting point g (521), a receiving coil upper connecting point h (522), a receiving coil upper connecting point i (523), a receiving coil upper connecting point j (524), a receiving coil upper connecting point k (525) and a receiving coil upper connecting point l (526), and the center point of the top circular outer surface of the receiving coil is provided with a receiving coil gravity bearing point (527); the binding structure is formed by nonmagnetic rigid or flexible ropes, the binding rope consists of a binding rope I (531), a binding rope II (532), a binding rope III (533), a binding rope IV (534), a binding rope V (535) and a binding rope VI (536), and the binding rope is respectively composed of an upper fixed bracket connection point a (511) -a binding rope I (531) -a receiving coil upper connection point g (521), an upper fixed bracket connection point b (512) -a binding rope II (532) -a receiving coil upper connection point h (522), an upper fixed bracket connection point c (513) -a binding rope III (533) -a receiving coil upper connection point i (523), an upper fixed bracket connection point d (514) -a binding rope IV (534) -a receiving coil upper connection point j (524), an upper fixed bracket connection point e (515) -a binding rope V (535) -a receiving coil upper fixed bracket connection point k (525) and an upper fixed bracket connection point f (531) (516) The binding rope VI (536) -the upper receiving coil connecting point l (526) form a binding chain of the receiving coil in the radial direction, the attitude change of the receiving coil in the radial direction is restrained, the receiving coil bearing connecting point (517) -the bearing rope (537) -the receiving coil gravity bearing point (527) form a binding chain for bearing the gravity of the receiving coil, the ring attitude change of the receiving coil in the axial direction is restrained, and the seven binding chains define the spatial position of the receiving coil, so that the receiving coil cannot generate moments in the pitching and rolling directions, and the generation of motion noise is avoided; a damping chamber (55) is formed by the upper fixing bracket (51), the receiving coil (52) and the binding rope.
2. The method for manufacturing the attitude change suppression device for the time domain aeroelectromagnetic method receiving coil according to claim 1, characterized by comprising the following steps:
A. determining whether a transmitting coil (3), a compensating coil (4) and a receiving coil (52) are in a concentric mode or an eccentric mode according to an aerial survey task, and determining the size of the receiving coil (52) according to the compensation effect requirement of a large-current primary field;
B. according to the size of the receiving coil (52), a disc-shaped coil is made of nonmagnetic materials, a receiving coil upper connecting point g (521), a receiving coil upper connecting point h (522), a receiving coil upper connecting point i (523), a receiving coil upper connecting point j (524), a receiving coil upper connecting point k (525) and a receiving coil upper connecting point l (526) are uniformly distributed on the circumferential outer surface of the disc-shaped coil, and a receiving coil gravity bearing point (527) is arranged at the center of the disc-shaped coil;
C. determining the sizes of an upper fixed support (51) and a lower fixed support (54) according to the size of a receiving coil (52), arranging a receiving coil bearing connecting point (517) at the central position of the upper fixed support (51) and axially corresponding to a receiving coil gravity bearing point (527), uniformly arranging an upper fixed support connecting point a (511), an upper fixed support connecting point b (512), an upper fixed support connecting point c (513), an upper fixed support connecting point d (514), an upper fixed support connecting point e (515) and an upper fixed support connecting point f (516) on the circumference of the inner surface of the upper fixed support (51), and radially corresponding to connecting points g-l (521-526) on the receiving coil one by one;
D. respectively linking an upper fixed support connecting point a (511) -an upper receiving coil upper connecting point g (521), an upper fixed support connecting point b (512) -a upper receiving coil upper connecting point h (522), an upper fixed support connecting point c (513) -a upper receiving coil upper connecting point i (523), an upper fixed support connecting point d (514) -a upper receiving coil upper connecting point j (524), an upper fixed support connecting point e (515) -a upper receiving coil upper connecting point k (525) and an upper fixed support connecting point f (516) -a upper receiving coil upper connecting point l (526) in sequence along the radial direction of the receiving coil by using a flexible or rigid binding rope I (531), a binding rope II (532), a binding rope III (533), a binding rope IV (534) and a binding rope VI (536); linking the receiver coil load bearing connection point (517) -the receiver coil gravity bearing point (527) with flexible or rigid load bearing ropes (537) axially along the receiver coil to ensure that there is no moment in the pitch and roll directions of the receiver coil for all the tether ropes;
E. fixing an upper fixing support (51) and a lower fixing support (54) through nylon screws, forming a damping cavity (55) in the middle space between the upper fixing support (51) and the lower fixing support (54), and manufacturing a receiving coil sensor (5) with a posture change suppression device;
F. the helicopter (1) is provided with a transmitting coil (3), a compensating coil (4) and a receiving coil sensor (5) with an attitude change suppression device through a hanging rope (2); the magnetic field signal received by the sensor is transmitted to a receiving system (7) in the engine room by a cable (6) and is collected and stored in real time;
G. after the flight mission is completed, ground staff carries out subsequent processing on the acquired data to complete geological exploration work.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810087314.8A CN108562942B (en) | 2018-01-30 | 2018-01-30 | Time domain aeroelectromagnetic method receiving coil attitude change suppression device and manufacturing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810087314.8A CN108562942B (en) | 2018-01-30 | 2018-01-30 | Time domain aeroelectromagnetic method receiving coil attitude change suppression device and manufacturing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108562942A CN108562942A (en) | 2018-09-21 |
| CN108562942B true CN108562942B (en) | 2020-06-23 |
Family
ID=63531095
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810087314.8A Active CN108562942B (en) | 2018-01-30 | 2018-01-30 | Time domain aeroelectromagnetic method receiving coil attitude change suppression device and manufacturing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108562942B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109917478B (en) * | 2019-04-01 | 2020-04-24 | 吉林大学 | Magnetic resonance water detection system and method for improving amplitude of acquired signal |
| CN110361785B (en) * | 2019-06-21 | 2021-04-20 | 中国科学院地质与地球物理研究所 | Aviation transient electromagnetic method receiving compensation device |
| CN110989010B (en) * | 2019-12-02 | 2022-02-15 | 吉林大学 | Transient electromagnetic exploration device and method based on eccentric coil compensation |
| CN111175834B (en) * | 2020-01-16 | 2021-06-22 | 吉林大学 | Towed transient electromagnetic detection device and method based on whole-process acquisition technology |
| CN112882114B (en) * | 2021-01-14 | 2021-11-19 | 吉林大学 | Complex-geology-oriented transient electromagnetic self-adaptive transverse constraint inversion method |
| CN115933005B (en) * | 2022-11-11 | 2024-05-17 | 中国科学院地质与地球物理研究所 | Device and processing method for counteracting attitude errors of semi-aviation electromagnetic system |
| CN116500692B (en) * | 2023-06-26 | 2023-10-27 | 吉林大学 | Optimization method for small loop transient electromagnetic detection |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105204076B (en) * | 2015-10-19 | 2017-07-14 | 吉林大学 | Helicopter transient electromagnetic detecting motion artifacts restraining device and noise suppressing method |
| CN106199740A (en) * | 2016-07-04 | 2016-12-07 | 哈尔滨工业大学 | A kind of aviation transient electromagnetic exploration system receives the vibration damping fixed support device of sensor |
-
2018
- 2018-01-30 CN CN201810087314.8A patent/CN108562942B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108562942A (en) | 2018-09-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108562942B (en) | Time domain aeroelectromagnetic method receiving coil attitude change suppression device and manufacturing method | |
| AU2010324493B2 (en) | Receiver coil assembly for airborne geophysical surveying with noise mitigation | |
| US9372275B2 (en) | Receiver coil assembly with air and ferromagnetic cored sensors for geophysical surveying | |
| US8362779B2 (en) | Double-suspension receiver coil system and apparatus | |
| CN104865608A (en) | Time-domain airborne electromagnetic method motion noise detection apparatus and inhibition method | |
| CN105204076B (en) | Helicopter transient electromagnetic detecting motion artifacts restraining device and noise suppressing method | |
| CN102176063B (en) | Primary field self-counteracting device for time-domain airborne electromagnetic method | |
| CA2914288C (en) | Apparatus for airborne geophysical prospecting using both natural and controlled source fields and method | |
| CN108227013A (en) | A kind of reception device for transient electromagnetic exploration | |
| Liu et al. | Design of cable parallel air-core coil sensor to reduce motion-induced noise in helicopter transient electromagnetic system | |
| AU2012380303A1 (en) | Receiver coil assembly with air and ferromagnetic cored sensors for geophysical surveying | |
| CN115826069A (en) | Unmanned aerial vehicle aviation magnetic measurement device and method based on proton magnetometer | |
| Fornacon et al. | The magnetic field experiment onboard Equator-S and its scientific possibilities | |
| Storetvedt et al. | Palaeomagnetic re-examination of the basal Caithness Old Red Sandstone; aspects of local and regional tectonics | |
| CN113791451A (en) | Semi-aviation electromagnetic receiving system carrying structure based on unmanned aerial vehicle | |
| Ma et al. | Correction of receiver noise in half-airborne transient electromagnetic method with electric source | |
| Sunderland et al. | Low-frequency rotational isolator for airborne exploration | |
| Thiede et al. | Motion Noise Reduction for Airborne EM using Natural Signal in DESMEX | |
| CN219770175U (en) | Magnetic sensor hanging device carried on flying platform | |
| CN216351276U (en) | Semi-aviation electromagnetic receiving system carrying structure based on unmanned aerial vehicle | |
| CN115288666A (en) | Nuclear magnetic logging while drilling instrument probe with separated transmitting and receiving coils | |
| Palangio et al. | Project and Manufacturing of an Autolevelling Vectorial Magnetometer for Volcanic Areas Monitoring |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |