CN115201926A - 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, which 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 term based on the preprocessed aviation transient electromagnetic data, constructing an inversion target function of the aviation magnetotelluric data based on the constraint term, and further performing inversion to obtain an apparent resistivity result; and interpreting the deep and large fracture according to the apparent resistivity achievement. The method carries out joint inversion on the aviation magnetotelluric data based on aviation transient electromagnetism, improves the inversion accuracy based on the joint inversion, simultaneously improves the identification accuracy of shallow structures, meets the engineering data requirements of deep and large fracture engineering, and further can provide a basis for engineering route selection, site selection and engineering construction in areas with extremely poor terrain conditions and difficult ground geophysical prospecting development.
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, deep and large fractures are often important factors influencing engineering line selection and site selection due to the characteristics of large scale, strong destructiveness, variable geological structure, complex engineering properties and the like. Along with economic development, the engineering investigation project of China is gradually developed to the difficult regions with poor terrain conditions, so that the investigation difficulty is increased, and the investigation of deep fractures in the regions by using the traditional method not only can greatly improve the cost, but also can not necessarily obtain better effect. The aeroelectromagnetic method is not limited by terrain conditions, is convenient and quick, and the like, so that the aeroelectromagnetic method is an effective means for detecting and identifying deep and large fractures and is widely applied in severe mountainous areas with extremely poor terrain conditions.
The aeroelectromagnetic method mainly includes aerotransient electromagnetic method (VTEM) and aerogeoelectromagnetic method (ZTEM). In the existing aviation electromagnetic-based deep and large fracture interpretation method, one mode is as follows: the method for detecting the deep and large fracture by adopting single aviation electromagnetism is simple in model and simple in calculation. For example, chinese patent application publication No. CN111897015A discloses that an aeroelectromagnetic method in a deep and large fracture detection method based on an aeroelectromagnetic method is referred to as an aeroelectromagnetic method (ZTEM), which detects a deep and large fracture by using a single aeroelectromagnetic method, but results generated by a single aeroelectromagnetic method often have a certain difference, which causes a ambiguity problem in deep and large fracture interpretation, and the accuracy is not high.
The second way is: and the complex inversion is constructed to carry out joint inversion of the aeroelectromagnetic data, so that the inversion precision of the aeroelectromagnetic method is improved, and the accuracy of deep fracture identification and interpretation 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 method obtains a conductivity grid number by performing two-dimensional conversion and one-dimensional processing on the aviation magnetotelluric, and performs joint constraint inversion on the aviation transient electromagnetic based on data corresponding to the magnetotelluric. The joint inversion result adopted by the method can effectively improve the low-frequency (deep) inversion accuracy, and is suitable for geophysical exploration in a large-area, but the characteristic that the requirement on a shallow structure is more precise is not met in the practical engineering aspect.
Disclosure of Invention
The invention aims to overcome the defect of low inversion accuracy of a single aeroelectromagnetic method in the prior art, and provides a deep and large fracture interpretation method and system based on an aeroelectromagnetic joint inversion technology.
In order to achieve the above purpose, the invention provides the following technical scheme:
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 term based on the preprocessed aviation transient electromagnetic data, constructing an inversion target function of the aviation magnetotelluric data based on the constraint term, and further performing inversion to obtain an apparent resistivity result;
and interpreting the deep and large fracture according to the apparent resistivity achievement.
According to a specific embodiment, in the deep fracture interpretation method based on the joint aviation electromagnetic inversion technique, the establishing of the constraint term based on the preprocessed aviation transient electromagnetic data includes:
converting the observation time and the electromagnetic response corresponding to the aviation transient electromagnetic data into a time constant and an amplitude;
matching is carried out in a pre-established time constant and amplitude mapping relation graph based on the time constant and the amplitude obtained through conversion, and then aviation transient electromagnetic data of a frequency domain are obtained;
the constraint term is established based on frequency domain airborne transient electromagnetic data.
According to a specific embodiment, in the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology, the observation time and the electromagnetic response corresponding to the aviation transient electromagnetic data are converted into a time constant and an amplitude by the following formula:
wherein, tau i Is a time constant, α i Is amplitude, t i And
the center time of the ith time-channel and the component value of the observed electromagnetic response, respectively, and k is the time-channel interval number.
According to a specific implementation mode, in the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology, the inversion objective function is as follows:
in the formula phi d (m) represents the magnetotelluric objective function of the aviation, phi m (m) represents the smoothest model constraint, λ represents the regularization factor,
then is a constraint term for airborne transient electromagnetic based, where β is a preset weight value.
According to a specific implementation mode, in the deep fracture interpretation method based on the aviation electromagnetic joint inversion technology, the preprocessing the acquired aviation transient electromagnetic data and aviation magnetotelluric data respectively includes:
performing late truncation, isolated point deletion and single-point smoothing on the acquired aviation transient electromagnetic data;
and carrying out transverse filtering processing on the acquired aviation magnetotelluric data.
According to a specific embodiment, in the deep and large fracture interpretation method based on the joint inversion technique of aeronautical and electromagnetic fields, the interpreting the deep and large fracture according to the apparent resistivity result includes:
and solving the gradient modulus of the apparent resistivity achievement, and interpreting the deep and large fracture based on the gradient modulus band range.
According to a specific embodiment, in the deep and large fracture interpretation method based on the aviation electromagnetic joint inversion technique, the gradient modulus of the apparent resistivity result is obtained by the following formula:
wherein, | grad ρ xy I is the apparent resistivity gradient modulus at (x, y), Δ ρ 1 Δ ρ as the amount of change in resistivity in the x direction 2 Is the amount of change in the apparent resistivity in the y-direction.
In another aspect of the present invention, a deep fracture interpretation system based on an airborne electromagnetic joint inversion technique is provided, and is characterized by comprising a processor, a network interface and a memory, wherein the processor, the network interface and the memory are connected with each other, 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 airborne electromagnetic joint inversion technique.
Compared with the prior art, the invention has the beneficial effects that: .
The method provided by the embodiment of the invention respectively preprocesses the acquired aviation transient electromagnetic data and aviation magnetotelluric data by acquiring the aviation transient electromagnetic data and the aviation magnetotelluric data; establishing a constraint term based on the preprocessed aviation transient electromagnetic data, constructing an inversion target function of the aviation magnetotelluric data based on the constraint term, and further performing inversion to obtain an apparent resistivity result; interpreting the deep and large fractures according to the apparent resistivity result; the method carries out joint constraint inversion on the aviation magnetotelluric data based on aviation transient electromagnetism, effectively improves the accuracy of high-frequency (shallow) inversion, meets the data requirement of engineering deep fracture identification, is beneficial to identifying and interpreting deep fractures, and provides a basis for engineering route selection, site selection and engineering construction in regions 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 technique according to an embodiment of the invention;
FIG. 2 is a pre-established relationship between time constant and 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 according to an embodiment of the present invention;
FIG. 4 is an explanatory diagram of a deep fracture obtained by jointly inverting a region according to the method of the present invention;
fig. 5 is a structural block diagram of a deep fracture interpretation system based on the aviation electromagnetic joint inversion technique according to an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to test examples and specific embodiments. It should be understood that the scope of the above-described subject matter of the present invention is not limited to the following examples, and any technique realized based on the contents of the present invention is within the scope of the present invention.
Example 1
FIG. 1 illustrates a deep fracture interpretation method based on the joint inversion technique of aeroelectromagnetic, according to an exemplary embodiment of the present invention, the method including:
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 term based on the preprocessed aviation transient electromagnetic data, constructing an inversion target function of the aviation magnetotelluric data based on the constraint term, and further performing inversion to obtain apparent resistivity results;
and S3, interpreting the deep and large fracture according to the apparent resistivity result.
In the embodiment, joint constraint inversion is carried out on aviation magnetotelluric data based on aviation transient electromagnetism, the accuracy of high-frequency (shallow) inversion is effectively improved, the data requirement of engineering deep fracture identification is met, deep fracture identification and interpretation are facilitated, and then, a basis is provided for engineering route selection, site selection and engineering construction in regions with extremely poor terrain conditions and difficult ground geophysical prospecting development.
In a possible implementation manner, in the deep fracture interpretation method based on the joint aviation electromagnetic inversion technique, the S1 specifically includes: respectively carrying out data analysis and data preprocessing on different aeroelectromagnetic method data; among them, the aeroelectromagnetic method is largely classified into an aerotransient electromagnetic method (VTEM) and an aerogeoelectromagnetic method (ZTEM). The data analysis and data preprocessing of the VTEM mainly comprises the steps of analyzing the interference situation and effective response of a point by drawing an induced electromotive force curve collected by the point, and carrying out preprocessing actions such as late truncation, flying point deletion, single-point smoothing and the like. The data analysis and data preprocessing of the ZTEM are to analyze and process noise by drawing a same-frequency point curve graph of all measuring points, and to perform processing such as partial segmentation rejection, certain degree of transverse filtering and the like on data according to the signal-to-noise ratio of the data, so that the interference is reduced as much as possible on the basis of keeping effective signals.
In a possible implementation manner, in the deep fracture interpretation method based on the joint inversion technique of airborne electromagnetism, in S2, the establishing a constraint term based on the preprocessed airborne transient electromagnetic data includes:
converting the observation time and the electromagnetic response corresponding to the aviation transient electromagnetic data into a time constant and an amplitude;
matching is carried out in a pre-established time constant and amplitude mapping relation graph based on the time constant and the amplitude obtained through conversion, and then aviation transient electromagnetic data of a frequency domain are obtained;
the constraint term is established based on the frequency domain airborne transient electromagnetic data.
Specifically, firstly, time-frequency conversion is carried out on the VTEM time domain data which is preprocessed in the step 1, VTEM data are converted into a frequency domain from the time domain, and then a joint inversion target function of the ZTEM is established based on the VTEM of the frequency domain.
In one possible implementationIn the above method, the performing 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. First, assuming that the decay curve of the electromagnetic response can be approximated by a piecewise exponential function with respect to time, the observed time and the electromagnetic response are then converted to a time constant (τ) i ) Sum amplitude (alpha) i )。
Wherein, t i And
the central time of the ith time channel and the component value of the observed electromagnetic response Z are respectively, k (more than or equal to 1) is the time channel interval number, 1 can be taken for the data k with good quality, and when the data quality is poor, k can be taken as 4. The apparent conductivity (. Sigma.a) can be measured using a series of τ i And alpha i The constructed relation table is inquired to obtain a relation graph of the time constant and the amplitude, and the relation graph is shown in figure 2. Then, converting the central time t corresponding to the secondary field time channel into a corresponding frequency value f by a conversion formula, wherein the conversion formula is as follows:
f＝1.0/(3.9t)
in a possible implementation manner, in step 2, constructing an inversion objective function of the aviation magnetotelluric data based on the constraint term specifically includes:
establishing a VTEM and ZTEM joint inversion target function, establishing an aviation electromagnetic joint inversion target function based on time-frequency conversion for inversion, adding a constraint term of VTEM apparent resistivity data after time-frequency conversion into the ZTEM inversion target function, wherein the inversion target function is as follows:
in the formula phi d (m) represents the magnetotelluric objective function of aviation, phi m (m) represents the smoothest model constraint, λ represents the regularization factor, newly added
The term is a constraint term on the apparent resistivity data. A coefficient term beta is introduced, which functions similarly to the trade-off function of the regularization factor lambda, to balance the weight between the dip data objective function and the apparent resistivity data objective function.
It will be appreciated that the frequency of transient electromagnetic data (VTEM) is typically high, primarily for shallow formation identification, and that magnetotelluric data (ZTEM) is typically low, allowing deep formations to be characterized; therefore, in this embodiment, the inversion objective function is based on VTEM constraint inversion ZTEM, and adjustable weight values are given to VTEM and ZTEM, so that the accuracy of high-frequency data can be effectively guaranteed on the basis of low-frequency data inversion, deep and large fractures in a deep structure can be effectively identified, and a shallow structure can be effectively depicted.
In one possible implementation, the weight of beta and lambda in the objective function is adjusted according to the frequency requirement of the actual deep fracture of the project; specifically, when the current area detection result is greater than the predetermined frequency, β > λ is set as the geological survey result, and the VTEM is weighted more heavily to further improve the accuracy of identifying the high-frequency part, and when the current area detection result is less than the predetermined frequency, the ZTEM is weighted more heavily. Preferably, the predetermined frequency is 5kHz.
In a possible implementation manner, in the deep fracture interpretation method based on the joint inversion technique of aeronautical electromagnetism, the S3 specifically includes:
on the basis of obtaining a reliable apparent resistivity joint inversion result, the method is used for interpreting the structural characteristics of deep fracture trend, tendency and the like according to the relative difference of apparent resistivity and the range of an apparent resistivity gradient modulus band, and specifically comprises the following steps:
and (5) solving gradient modulus for the apparent resistivity of the combined inversion, and interpreting the deep fracture according to the range of the apparent resistivity gradient modulus. And in addition, geological background data can be combined, and the structural characteristics of deep and large fractures can be directly and comprehensively analyzed and interpreted according to apparent resistivity results.
According to the embodiment, the gradient modulus analysis method can effectively improve the interpretation accuracy of deep and large fractures.
Further, in step 3, a gradient modulus is obtained for the apparent resistivity of the joint inversion, and the gradient modulus is obtained by the following formula:
wherein | grad · ρ xy I is the apparent resistivity gradient modulus at (x, y), Δ ρ 1 Δ ρ as the amount of change in resistivity in the x direction 2 Is the amount of change in the apparent resistivity in the y-direction.
In a possible implementation manner, the deep fracture interpretation method based on the joint inversion technique of aeronautical electromagnetism further includes: step 4, according to the interpretation result, combining with the engineering requirement, well drilling verification and correcting the result, specifically comprising:
according to objective and reliable deep and large fracture interpretation results, drilling holes are arranged at key positions of deep and large fracture attention in combination with requirements of engineering line selection and site selection, and the interpretation results before are corrected through the results of the drilling holes while the interpretation results are verified.
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 carry out joint inversion and deep fracture interpretation on aviation electromagnetic data (including aviation transient electromagnetic VTEM and aviation magnetotelluric ZTEM) measured in a certain area.
Fig. 3 shows a three-dimensional slice diagram of apparent resistivity of the aviation electromagnetic joint inversion in the area by using the method provided by the embodiment of the invention, and as shown in fig. 3, a plurality of joint constraint inversion three-dimensional result slice diagrams exist in the diagram, so that the apparent resistivity distribution forms between adjacent slice diagrams are similar and are obvious in abnormality, which indicates that the joint inversion result is objective and reliable. FIG. 4 is a diagram of the interpretation result of deep and large fractures in the area, and the deep and large fractures are comprehensively identified and interpreted by combining geological background data on the basis of objective and reliable inversion results. Wherein, the apparent resistivity difference of each slice in fig. 4 is obvious (warm tone is relatively high resistance, cold tone is relatively low resistance), and between 12500-14000, 20000-21000 there are obvious interfaces of high resistance and low resistance, and the depth is large, and the depth is conjectured to be deep fracture by combining geological background data, and the fracture is respectively named as F1 and F2. F1 and F2 are both in NW-SE trend, and the whole cutting depth is larger.
Therefore, the deep and large fracture interpretation method based on the aviation electromagnetic method provided by the embodiment of the invention can effectively reduce the multiple interpretation of the aviation electromagnetic method inversion, improve the objectivity of the aviation electromagnetic method joint inversion result, and further improve the accuracy of deep and large fracture identification interpretation.
In another aspect of the present invention, as shown in fig. 5, there is also provided an avionics method-based deep fracture interpretation system, which includes a processor, a network interface and a memory, wherein the processor, the network interface and the memory are connected with each other, the memory is used for storing a computer program, the computer program includes program instructions, and the processor is configured to call the program instructions to execute the avionics method-based deep fracture interpretation 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 (DSP), an Application Specific Integrated Circuit (ASIC), a Field Programmable Gate Array (FPGA) or other Programmable logic device, discrete gate or transistor logic device, discrete hardware component.
The various methods, steps and logic blocks disclosed 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 directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software modules in the decoding processor. The software modules may be located in ram, flash, rom, prom, or eprom, registers, etc. as is well known in the art. The processor reads the information in the storage medium and completes the steps of the method in combination with the hardware.
The storage medium may be a memory, for example, which may be volatile memory or nonvolatile memory, or which 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 PROM (EEPROM), or a flash Memory.
The volatile Memory may be a Random Access Memory (RAM) which serves as an external cache. By way of example, and not limitation, many forms of RAM are available, such as Static Random Access Memory (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double Data Rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), SLDRAM (SLDRAM), and Direct Rambus RAM (DRRAM).
The storage media described in connection with the embodiments of the invention are intended to comprise, without being limited to, these and any other suitable types of memory.
It should be understood that the disclosed system may be implemented in other ways. For example, the division of the modules into only one logical function may be implemented in another way, for example, multiple units or components may be combined or integrated into another system, or some features may be omitted, or not implemented. In addition, the communication connection between the modules may be an indirect coupling or communication connection of the server or the unit through some interfaces, and may be an electrical or other form.
In addition, functional modules in the embodiments of the present invention may be integrated into one processing unit, or each module may exist alone physically, or two or more modules are integrated into one processing unit. The integrated unit may be implemented in the form of hardware, or may also be implemented in the form of a software functional unit.
The integrated unit, if implemented in the form of a software functional unit and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute 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), a removable hard disk, a magnetic disk, or an optical disk, which can store program codes.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (8)
1. A deep fracture interpretation method based on an aviation electromagnetic joint inversion technology is characterized by 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 term based on the preprocessed aviation transient electromagnetic data, constructing an inversion target function of the aviation magnetotelluric data based on the constraint term, and further performing inversion to obtain an apparent resistivity result;
and interpreting the deep and large fracture according to the apparent resistivity achievement.
2. The method for interpreting the deep fractures based on the joint inversion technique of the aeromagnetic system according to claim 1, wherein the establishing of the constraint term based on the preprocessed aeromagnetic transient electromagnetic data comprises:
converting the observation time and the electromagnetic response corresponding to the aviation transient electromagnetic data into a time constant and an amplitude;
matching is carried out in a pre-established time constant and amplitude mapping relation graph based on the time constant and the amplitude obtained through conversion, and then aviation transient electromagnetic data of a frequency domain are obtained;
the constraint term is established based on the frequency domain airborne transient electromagnetic data.
3. The method for interpreting deep fractures based on the joint aviation electromagnetic inversion technique according to claim 2, wherein the corresponding observed time and electromagnetic response of the aviation transient electromagnetic data are converted into time constants and amplitudes through the following formulas:
wherein, tau i Is a time constant, α i Is amplitude, t i And
the center time of the ith time-channel and the component value of the observed electromagnetic response, respectively, and k is the time-channel interval number.
4. The deep fracture interpretation method based on the joint inversion technique of aeronautics and electromagnetics according to claim 1, wherein the inversion objective function is:
in the formula phi d (m) represents the magnetotelluric objective function of aviation, phi m (m) represents the smoothest model constraint, λ represents the regularization factor,
then a constraint term based on the first apparent resistivity is applied, where β is a preset weight value.
5. The deep fracture interpretation method based on the joint aviation electromagnetic inversion technology as claimed in any one of claims 1 to 4, wherein the preprocessing of the acquired aviation transient electromagnetic data and aviation magnetotelluric data respectively comprises:
performing late truncation, isolated point deletion and single-point smoothing on the acquired aviation transient electromagnetic data;
and carrying out transverse filtering processing on the acquired aviation magnetotelluric data.
6. The deep fracture interpretation method based on the joint inversion technique of aeronautics and electromagnetics as claimed in any one of claims 1 to 4, wherein the interpreting the deep fracture according to the apparent resistivity result comprises:
and solving the gradient modulus of the apparent resistivity achievement, and interpreting the deep fracture based on the gradient modulus band range.
7. The deep fracture interpretation method based on the joint inversion technique of aeronautics and electromagnetics according to claim 6, wherein the gradient modulus of the apparent resistivity achievement is found by the following formula:
wherein, | grad. Rho xy I is the apparent resistivity gradient modulus at (x, y), Δ ρ 1 Δ ρ as the amount of change in resistivity in the x direction 2 Is the amount of change in the apparent resistivity in the y-direction.
8. An aviation electromagnetic joint inversion technology-based deep fracture interpretation system, comprising a processor, a network interface and a memory, wherein the processor, the network interface and the memory are connected with each other, wherein 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 aviation electromagnetic joint inversion technology-based deep fracture interpretation method according to any one of claims 1 to 7.
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