CN115201926B - Deep fracture interpretation method and system based on aviation electromagnetic joint inversion technology - Google Patents
Deep fracture interpretation method and system based on aviation electromagnetic joint inversion technology Download PDFInfo
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Abstract
The invention provides a deep fracture interpretation method and system based on an aviation electromagnetic joint inversion technology, comprising the following steps: acquiring aviation transient electromagnetic data and aviation magnetotelluric data, and respectively preprocessing the acquired aviation transient electromagnetic data and aviation magnetotelluric data; establishing a constraint item based on the preprocessed aviation transient electromagnetic data, constructing an inversion objective function of the aviation magnetotelluric data based on the constraint item, and inverting to obtain apparent resistivity results; and interpreting the deep fracture according to the apparent resistivity result. The method performs joint inversion on aviation magnetotelluric data based on aviation transient electromagnetism, improves inversion precision based on joint inversion, improves recognition precision of shallow structures, meets engineering data requirements of deep fracture engineering, and can provide basis for engineering line selection, site selection and engineering construction in areas with extremely poor terrain conditions and difficult ground geophysical prospecting.
Description
Technical Field
The invention relates to the technical field of geophysical exploration, in particular to a deep fracture interpretation method and system based on an aviation electromagnetic joint inversion technology.
Background
In engineering investigation, the deep fracture is often an important factor influencing engineering line selection and site selection due to the characteristics of huge scale, strong destructiveness, variable geological structure, complex engineering properties and the like. Along with the economic development, the engineering investigation projects of China are gradually developed to difficult regions with poor terrain conditions, so that the investigation difficulty is increased, and the cost is greatly increased and a good effect is not necessarily obtained at the same time when the traditional method is used for investigating the deep fracture in the regions. The aviation electromagnetic method is not limited by the terrain condition, is convenient and quick, and the like, so that the aviation electromagnetic method is an effective means for detecting and identifying the deep fracture in the difficult mountain area with extremely poor terrain condition and is widely applied.
The aeroelectromagnetic method mainly comprises an aero transient electromagnetic method (VTEM) and an aero magnetotelluric method (ZTEM). In the existing aviation electromagnetic-based deep fracture interpretation method, one mode is as follows: the method for detecting the deep fracture by adopting the single aviation electromagnetic is simple in model and calculation. For example, in chinese patent application publication No. CN111897015a, an airborne electromagnetic method in a deep fracture detection method based on an airborne electromagnetic method is referred to as an airborne electromagnetic method (ZTEM), which detects a deep fracture by using a single airborne electromagnetic method, but there is often a certain difference between results generated by a single airborne electromagnetic method, resulting in a problem of multiple interpretation of the deep fracture interpretation, and the accuracy is not high.
The second mode is as follows: and constructing complex inversion to perform joint inversion of aviation electromagnetic data, so that the inversion precision of an aviation electromagnetic method is improved, and the accuracy of identifying and interpreting deep and large breaks is improved. For example: the application publication number is CN110058317A Chinese patent, which discloses a joint inversion method of aviation transient electromagnetic data and aviation magnetotelluric data. The joint inversion result adopted by the method can effectively improve the low-frequency (deep) inversion precision, is suitable for geophysical exploration of a large area, but does not meet the characteristic of finer requirements on shallow structures in practical engineering.
Disclosure of Invention
The invention aims to overcome the defect of low inversion precision of a single aviation electromagnetic method in the prior art, and provides a deep fracture interpretation method and a deep fracture interpretation system based on an aviation electromagnetic joint inversion technology, which perform joint inversion on aviation transient electromagnetic and aviation magnetotelluric through a time-frequency conversion strategy, so that the joint inversion precision is improved, and meanwhile, the model complexity is reduced.
In order to achieve the above object, the present invention provides the following technical solutions:
a deep fracture interpretation method based on an aviation electromagnetic joint inversion technology comprises the following steps:
acquiring aviation transient electromagnetic data and aviation magnetotelluric data, and respectively preprocessing the acquired aviation transient electromagnetic data and aviation magnetotelluric data;
establishing a constraint item based on the preprocessed aviation transient electromagnetic data, constructing an inversion objective function of the aviation magnetotelluric data based on the constraint item, and inverting to obtain apparent resistivity results;
and interpreting the deep fracture according to the apparent resistivity result.
According to a specific embodiment, in the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology, the establishing constraint terms based on the preprocessed aviation transient electromagnetic data includes:
converting the observation time and electromagnetic response corresponding to the aviation transient electromagnetic data into a time constant and an amplitude;
based on the time constant and the amplitude obtained by conversion, matching is carried out in a pre-established time constant and amplitude mapping relation diagram, and then aviation transient electromagnetic data of a frequency domain is obtained;
the constraint term is established based on aviation transient electromagnetic data of a frequency domain.
According to a specific embodiment, in the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology, the observation time and electromagnetic response corresponding to the aviation transient electromagnetic data are converted into time constants and amplitudes through the following formula:
wherein τ i Is a time constant, alpha i Is the amplitude, t i And
the center time of the ith time trace and the component value of the observed electromagnetic response, k is the number of time trace intervals, respectively.
According to a specific embodiment, in the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology, the inversion objective function is:
in phi, phi d (m) represents an aero magnetotelluric objective function, Φ m (m) represents the smoothest model constraint, lambda represents the regularization factor,
then it is a constraint term for aviation transient electromagnetic based, where β is a preset weight value.
According to a specific embodiment, in the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology, the preprocessing of the acquired aviation transient electromagnetic data and aviation magnetotelluric data respectively includes:
carrying out advanced cut-off, isolated point deletion and single-point smoothing treatment on the acquired aviation transient electromagnetic data;
and performing transverse filtering processing on the acquired aeromagnetotelluric data.
According to a specific embodiment, in the method for interpreting deep fractures based on the aviation electromagnetic joint inversion technology, the interpreting the deep fractures according to the apparent resistivity result includes:
and obtaining gradient modulus of the apparent resistivity result, and interpreting the deep fracture based on the gradient modulus band range.
According to a specific embodiment, in the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology, the gradient modulus of the apparent resistivity result is obtained by the following formula:
wherein, |grad ρ xy Apparent resistivity gradient modulus at (x, y), Δρ 1 Δρ is the change in apparent resistivity in the x-direction 2 Is the amount of change in apparent resistivity in the y-direction.
In another aspect, the invention provides a deep fracture interpretation system based on an aviation electromagnetic joint inversion technology, which is characterized by comprising a processor, a network interface and a memory, wherein the processor, the network interface and the memory are mutually connected, the memory is used for storing a computer program, the computer program comprises program instructions, and the processor is configured to call the program instructions to execute the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology.
Compared with the prior art, the invention has the beneficial effects that: .
According to the method provided by the embodiment of the invention, the aviation transient electromagnetic data and the aviation magnetotelluric data are respectively preprocessed; establishing a constraint item based on the preprocessed aviation transient electromagnetic data, constructing an inversion objective function of the aviation magnetotelluric data based on the constraint item, and inverting to obtain apparent resistivity results; interpreting the deep fracture according to the apparent resistivity result; the method performs joint constraint inversion on aviation magnetotelluric data based on aviation transient electromagnetic, effectively improves the accuracy of high-frequency (shallow) inversion, meets the data requirement of engineering deep-large fracture identification, is beneficial to the identification and interpretation of the deep-large fracture, and further provides basis for engineering line selection, site selection and engineering construction in areas with extremely poor terrain conditions and difficult ground geophysical prospecting development.
Drawings
FIG. 1 is a flow chart of a deep fracture interpretation method based on an aviation electromagnetic joint inversion technology according to an embodiment of the invention;
FIG. 2 is a graph of pre-established time constants versus amplitude according to an embodiment of the present invention;
FIG. 3 is a three-dimensional slice of apparent resistivity obtained by performing joint inversion on a region using the method provided by the present invention in accordance with an embodiment of the present invention;
FIG. 4 is a schematic diagram of a deep fracture interpretation obtained by performing joint inversion on a region using the method according to the embodiment of the present invention;
FIG. 5 is a block diagram of a deep fracture interpretation system based on an aviation electromagnetic joint inversion technique according to an embodiment of the invention.
Detailed Description
The present invention will be described in further detail with reference to test examples and specific embodiments. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Example 1
FIG. 1 illustrates a deep fracture interpretation method based on an airborne electromagnetic joint inversion technique, according to an exemplary embodiment of the invention, the method comprising:
s1, acquiring aviation transient electromagnetic data and aviation magnetotelluric data, and respectively preprocessing the acquired aviation transient electromagnetic data and aviation magnetotelluric data;
s2, establishing a constraint item based on the preprocessed aviation transient electromagnetic data, constructing an inversion objective function of the aviation magnetotelluric data based on the constraint item, and inverting to obtain apparent resistivity results;
and S3, interpreting the deep fracture according to the apparent resistivity result.
In the embodiment, the aviation magnetotelluric data are subjected to joint constraint inversion based on aviation transient electromagnetic, so that the accuracy of high-frequency (shallow) inversion is effectively improved, the data requirement of engineering deep-large fracture identification is met, the identification and interpretation of the deep-large fracture are facilitated, and further, in areas with extremely poor terrain conditions and difficult ground geophysical prospecting, the basis is provided for engineering line selection, site selection and engineering construction.
In one possible implementation manner, in the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology, the S1 specifically includes: respectively carrying out data analysis and data preprocessing on different aviation electromagnetic method data; among them, the aeroelectromagnetic method is mainly classified into an aero transient electromagnetic method (VTEM) and an aero magnetotelluric method (ZTEM). The data analysis and data preprocessing of the VTEM mainly comprises the steps of analyzing interference conditions and effective responses suffered by a single measuring point by drawing an induced electromotive force curve acquired by the single measuring point, and carrying out preprocessing actions such as late truncation, flying spot deletion, single-point smoothing processing and the like. The ZTEM data analysis and data preprocessing are to draw the same frequency point curve graph of all measuring points to perform noise analysis and processing, and to perform partial segment rejection, a certain degree of transverse filtering and other processing on the data according to the signal-to-noise ratio, so that the interference is reduced as much as possible on the basis of retaining effective signals.
In a possible implementation manner, in the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology, in S2, the establishing a constraint term based on the preprocessed aviation transient electromagnetic data includes:
converting the observation time and electromagnetic response corresponding to the aviation transient electromagnetic data into a time constant and an amplitude;
based on the time constant and the amplitude obtained by conversion, matching is carried out in a pre-established time constant and amplitude mapping relation diagram, and then aviation transient electromagnetic data of a frequency domain is obtained;
the constraint term is established based on aviation transient electromagnetic data of a frequency domain.
Specifically, firstly, performing time-frequency conversion on the preprocessed VTEM time domain data in the step 1, converting the VTEM data from the time domain to the frequency domain, and then establishing a joint inversion objective function of ZTEM based on the VTEM in the frequency domain.
In one possible implementation manner, the time-frequency conversion on the VTEM time domain data specifically includes the following steps: and performing apparent resistivity conversion by adopting a conductivity imaging method based on a pseudo-layer half-space model. It is first assumed that the electromagnetic response decay curve can be approximated by a piecewise exponential function over time, and then the observed time and electromagnetic response are converted to a time constant (τ i ) And amplitude (. Alpha i )。
Wherein t is i And
the central time of the ith time channel and the Z component value of the observed electromagnetic response are respectively, k (more than or equal to 1) is the interval number of the time channels, and the method aims at qualityThe good amount of data k may take 1, while when the data quality is poor, k may take 4. The apparent conductivity (σa) may utilize a series of τ i And alpha i The constructed relationship table is obtained by inquiring, and the relationship diagram of time constant and amplitude is shown in figure 2. Then converting the center time t corresponding to the secondary field time channel into a corresponding frequency value f through a conversion formula, wherein the conversion formula is as follows:
f＝1.0/(3.9t)
in a possible implementation manner, in the step 2, an inversion objective function of the aeromagnetotelluric data is constructed based on the constraint term, and specifically includes:
establishing a VTEM and ZTEM joint inversion objective function, establishing an aviation electromagnetic joint inversion objective function based on time-frequency conversion for inversion, adding a constraint item of the VTEM apparent resistivity data after the time-frequency conversion into the ZTEM inversion objective function, wherein the inversion objective function is as follows:
in phi, phi d (m) represents an aero magnetotelluric objective function, Φ m (m) represents the smoothest model constraint, λ represents the regularization factor, and new additions
The term is then a constraint term on the apparent resistivity data. A coefficient term β is introduced, which functions similarly to the trade-off function of the regularization factor λ, to balance the weights between the tilt data objective function and the apparent resistivity data objective function.
It will be appreciated that transient electromagnetic data (VTEM) is typically high in frequency and is primarily used for shallow structure identification, magnetotelluric data (ZTEM) is typically low in frequency and can characterize deep structures; therefore, the inversion objective function constructed by the embodiment inverts ZTEM based on VTEM constraint, and simultaneously endows the VTEM and the ZTEM with adjustable weight values, so that the precision of high-frequency data can be effectively ensured on the basis of low-frequency data inversion, deep and large breaks in a deep structure can be effectively identified, and shallow structures can be effectively depicted.
In one possible implementation, the weight adjustment is performed on beta and lambda in the objective function according to the frequency requirement of the actual deep fracture of the engineering; specifically, when the geological exploration result is larger than the preset frequency, setting beta > lambda, wherein the VTEM occupies larger weight, further improving the identification accuracy of the high-frequency part, and when the current region detection result is smaller than the preset frequency, the ZTEM occupies larger weight. Preferably, the predetermined frequency is 5kHz.
In one possible implementation manner, in the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology, the S3 specifically includes:
on the basis of obtaining a reliable apparent resistivity joint inversion result, according to the relative difference of the apparent resistivity and the gradient modulus band range of the apparent resistivity, the method interprets the structural characteristics such as the trend and the tendency of deep fracture, and the like, and specifically comprises the following steps:
and obtaining gradient modulus for the apparent resistivity of the joint inversion, and interpreting the deep fracture according to the gradient modulus band range of the apparent resistivity. And directly and comprehensively analyzing and interpreting the structural characteristics of the deep fracture according to the apparent resistivity result by combining geological background information.
According to the gradient modulus analysis method, the interpretation accuracy of deep fracture can be effectively improved.
Further, in the step 3, the gradient modulus is obtained for the apparent resistivity of the joint inversion, and the gradient modulus is obtained for the apparent resistivity by the following formula:
in the formula, |grad ρ xy Apparent resistivity gradient modulus at (x, y), Δρ 1 Δρ is the change in apparent resistivity in the x-direction 2 Is the amount of change in apparent resistivity in the y-direction.
In one possible implementation manner, the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology further comprises the following steps: and 4, verifying and correcting the result by combining engineering requirements according to the interpretation result, wherein the method specifically comprises the following steps of:
according to objective and reliable deep fracture interpretation results, combining engineering line selection and site selection requirements, arranging drilling holes at important positions of deep fracture, verifying the interpretation results, and correcting the previous interpretation deep fracture results through the drilling holes.
In a further embodiment of the invention, the deep fracture interpretation method of the aviation electromagnetic joint inversion technology provided by the embodiment of the invention is adopted to perform joint inversion and deep fracture interpretation on aviation electromagnetic data (including aviation transient electromagnetic VTEM and aviation magnetotelluric ZTEM) actually measured in a certain area.
The three-dimensional slice diagram of the region aviation electromagnetic joint inversion apparent resistivity by the method provided by the embodiment of the invention is shown in fig. 3, and as shown in fig. 3, a plurality of joint constraint inversion three-dimensional result slice diagrams exist in the diagram, the apparent resistivity distribution form between adjacent slice diagrams can be seen to be similar, the abnormity is obvious, and the joint inversion result is objective and reliable. FIG. 4 is a graph of the results of interpretation of deep fractures in the region, which is based on objective and reliable inversion results, and is combined with geological background data to perform comprehensive recognition interpretation on the deep fractures. The apparent difference in apparent resistivity in each slice in fig. 4 (the warm tone is relatively high-resistance, the cool tone is relatively low-resistance), and there are apparent interfaces of high-resistance and low-resistance between 12500-14000 and 20000-21000, and the depth is large, and the interfaces are presumed to be deep breaks by combining with geological background information, and are respectively named as F1 and F2. F1 and F2 are both NW-SE trend, and the overall cutting depth is larger.
Therefore, the deep fracture interpretation method based on the aviation electromagnetic method can effectively reduce the multiple interpretation of inversion of the aviation electromagnetic method, improve the objectivity of the joint inversion result of the aviation electromagnetic method, and further improve the accuracy of recognition interpretation of the deep fracture.
In another aspect of the present invention, as shown in fig. 5, there is further provided a deep fracture interpretation system based on an aeroelectromagnetic method, the system including a processor, a network interface, and a memory, the processor, the network interface, and the memory being connected to each other, wherein the memory is configured to store a computer program, the computer program including program instructions, and the processor is configured to invoke the program instructions to perform the deep fracture interpretation method based on the aeroelectromagnetic method.
In an embodiment of the invention, the processor may be an integrated circuit chip having signal processing capabilities. The processor may be a general purpose processor, a digital signal processor (Digital Signal Processor, DSP for short), an application specific integrated circuit (Application Specific Integrated Circuit, ASIC for short), a field programmable gate array (Field Programmable GateArray, FPGA for short), or other programmable logic device, discrete gate or transistor logic device, discrete hardware components.
The disclosed methods, steps, and logic blocks in the embodiments of the present invention may be implemented or performed. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like. The steps of the method disclosed in connection with the embodiments of the present invention may be embodied directly in the execution of a hardware decoding processor, or in the execution of a combination of hardware and software modules in a decoding processor. The software modules may be located in a random access memory, flash memory, read only memory, programmable read only memory, or electrically erasable programmable memory, registers, etc. as well known in the art. The processor reads the information in the storage medium and, in combination with its hardware, performs the steps of the above method.
The storage medium may be memory, for example, may be volatile memory or nonvolatile memory, or may include both volatile and nonvolatile memory.
The nonvolatile Memory may be a Read-Only Memory (ROM), a Programmable ROM (PROM), an Erasable PROM (EPROM), an electrically Erasable ROM (Electrically EPROM, EEPROM), or a flash Memory.
The volatile memory may be a random access memory (RandomAccess Memory, RAM for short) which acts as an external cache. By way of example, and not limitation, many forms of RAM are available, such as Static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (Double Data RateSDRAM), enhanced SDRAM (ESDRAM), synchronous DRAM (SLDRAM), and direct memory bus RAM (directracram, DRRAM).
The storage media described in embodiments of the present invention are intended to comprise, without being limited to, these and any other suitable types of memory.
It should be understood that the system disclosed in the present invention may be implemented in other manners. For example, the modules may be divided into only one logic function, and there may be other manners of dividing the modules when actually implemented, for example, a plurality of units or components may be combined or may be integrated into another system, or some features may be omitted or not performed. Alternatively, the communication connection between the modules may be an indirect coupling or a communication connection through some interfaces, servers or units, and may be in electrical or other forms.
In addition, each functional module in the embodiments of the present invention may be integrated in one processing unit, or each module may exist alone physically, or two or more modules may be integrated in one processing unit. The integrated units may be implemented in hardware or in software functional units.
The integrated units, if implemented in the form of software functional units and sold or used as stand-alone products, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present invention may be embodied essentially or in part or all of the technical solution or in part in the form of a software product stored in a storage medium, including instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a Read-Only Memory (ROM), a random access Memory (RAM, randomAccess Memory), a removable hard disk, a magnetic disk, or an optical disk, or other various media capable of storing program codes.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (6)
1. The deep fracture interpretation method based on the aviation electromagnetic joint inversion technology is characterized by comprising the following steps of:
acquiring aviation transient electromagnetic data and aviation magnetotelluric data, and respectively preprocessing the acquired aviation transient electromagnetic data and aviation magnetotelluric data;
establishing a constraint item based on the preprocessed aviation transient electromagnetic data, constructing an inversion objective function of the aviation magnetotelluric data based on the constraint item, and inverting to obtain apparent resistivity results;
interpreting the deep fracture according to the apparent resistivity result;
the establishing constraint terms based on the preprocessed aviation transient electromagnetic data comprises the following steps:
converting the observation time and electromagnetic response corresponding to the aviation transient electromagnetic data into a time constant and an amplitude;
based on the time constant and the amplitude obtained by conversion, matching is carried out in a pre-established time constant and amplitude mapping relation diagram, and then aviation transient electromagnetic data of a frequency domain is obtained;
establishing the constraint item based on aviation transient electromagnetic data of a frequency domain;
the inversion objective function is:
in phi, phi d (m) represents an aero magnetotelluric objective function, Φ m (m) represents the smoothest model constraint, lambda represents the regularization factor,
the constraint term for the apparent resistivity of the aviation transient electromagnetic data is adopted, wherein beta is a preset weight value.
2. The deep fracture interpretation method based on aviation electromagnetic joint inversion technology as claimed in claim 1, wherein the observation time and electromagnetic response corresponding to the aviation transient electromagnetic data are converted into time constants and amplitudes by the following formula:
wherein τ i Is a time constant, alpha i Is the amplitude, t i And
the center time of the ith time trace and the component value of the observed electromagnetic response, k is the number of time trace intervals, respectively.
3. The deep fracture interpretation method based on the aviation electromagnetic joint inversion technology as claimed in claim 1 or 2, wherein the preprocessing of the acquired aviation transient electromagnetic data and aviation magnetotelluric data respectively comprises:
carrying out advanced cut-off, isolated point deletion and single-point smoothing treatment on the acquired aviation transient electromagnetic data;
and performing transverse filtering processing on the acquired aeromagnetotelluric data.
4. The deep fracture interpretation method based on the aviation electromagnetic joint inversion technique as claimed in claim 1 or 2, wherein the interpretation of the deep fracture from the apparent resistivity results comprises:
and obtaining gradient modulus of the apparent resistivity result, and interpreting the deep fracture based on the gradient modulus band range.
5. The deep fracture interpretation method based on the aviation electromagnetic joint inversion technique as claimed in claim 4, wherein the gradient modulus of the apparent resistivity result is obtained by:
wherein, |grad ρ xy Apparent resistivity gradient modulus at (x, y), Δρ 1 Δρ is the change in apparent resistivity in the x-direction 2 Is the amount of change in apparent resistivity in the y-direction.
6. A deep fracture interpretation system based on aeroelectromagnetic joint inversion technology, comprising a processor, a network interface and a memory, the processor, the network interface and the memory being interconnected, wherein the memory is configured to store a computer program comprising program instructions, the processor being configured to invoke the program instructions to perform the deep fracture interpretation method based on aeroelectromagnetic joint inversion technology as claimed in any of claims 1-5.
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| US8275592B2 (en) * | 2008-04-07 | 2012-09-25 | Westerngeco L.L.C. | Joint inversion of time domain controlled source electromagnetic (TD-CSEM) data and further data |
| CN110058317B (en) * | 2019-05-10 | 2020-09-08 | 成都理工大学 | Aviation transient electromagnetic data and aviation magnetotelluric data joint inversion method |
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