Airgun synchronous ignition control method, system, electronic device and storage medium

Abstract

This invention relates to the field of geophysical exploration technology, and provides a method, system, electronic device, and storage medium for controlling the synchronized ignition of air guns. The method is applied to a marine seismic source control system and includes: determining the ignition time deviation of the air gun based on historical ignition monitoring data and the ignition command corresponding to the historical ignition monitoring data; determining the target delay of data transmission by monitoring the data transmission delay between the GSC module and each AGC module in the marine seismic source control system; summing the ignition time in the current ignition command controlling the air gun to ignite and the target delay to obtain a first ignition time for controlling the air gun to ignite; and controlling the air gun to ignite based on the first ignition time and the ignition time deviation. The aim is to improve the ignition accuracy of the marine seismic source control system in controlling the synchronized ignition of multiple air guns.

Description

Technical Field

[0001] This invention relates to the field of geophysical exploration technology, and in particular to a method, system, electronic device and storage medium for synchronous ignition control of a gas gun. Background Technology

[0002] Marine geophysical airgun seismic sources are primarily used in marine seismic exploration. They generate shock wavelets for exploration and are an important new type of equipment in marine exploration, offering advantages such as no pollution, wide bandwidth, stable performance, and high resolution, playing a vital role in specific applications. Seismic exploration in reservoirs and lakes provides crucial support for industry personnel. Based on this, a digital marine seismic source control system suitable for marine geophysical exploration was designed using digital technology. The system's functions are divided into above-water and underwater parts. The above-water part mainly displays data and implements control, while the underwater part has a distributed structure. Waveforms are digitally processed through front-end circuits to achieve real-time monitoring of the airgun seismic source. The digital marine seismic source control system is used to control the excitation of marine airgun seismic sources. Its main functions include controlling the excitation of the airgun seismic source, real-time acquisition of airgun synchronization signals, near-field wavelet signals, pressure, and depth data, and monitoring the excitation quality of the airgun seismic source. The system has very high requirements for the ignition time of the air guns, requiring all air guns to be ignited synchronously. However, during signal transmission, different air guns receive the ignition command with different time delays, resulting in low accuracy of the synchronization of different air guns. Summary of the Invention

[0003] In view of this, the present invention provides a method, system, electronic device, and storage medium for controlling the synchronous ignition of air guns. The aim is to improve the ignition accuracy of a marine seismic source control system in controlling the synchronous ignition of multiple air guns.

[0004] This invention provides a method for synchronous ignition control of an air gun, which is applied to a marine seismic source control system, comprising:

[0005] The ignition time deviation of the air gun is determined based on the historical ignition monitoring data of the air gun and the ignition command corresponding to the historical ignition monitoring data.

[0006] The target delay for data transmission is determined by monitoring the data transmission delay between the GSC module and each AGC module in the marine seismic source control system.

[0007] The ignition time in the current ignition command that controls the air gun to ignite is summed with the target delay to obtain the first ignition time for controlling the air gun to ignite.

[0008] The air gun is controlled to ignite based on the first ignition time and the ignition time deviation.

[0009] Optionally, controlling the air gun to ignite based on the first ignition time and the ignition time deviation includes:

[0010] The second ignition time is obtained by subtracting the first ignition time from the ignition time deviation.

[0011] When the second ignition time is reached, an ignition command is sent to the air gun via the AGC module to control the air gun to ignite.

[0012] Optionally, determining the ignition time deviation of the air gun based on historical ignition monitoring data and the ignition command corresponding to the historical ignition monitoring data includes:

[0013] Based on multiple historical ignition monitoring data of the air gun, multiple actual ignition times of the air gun are determined.

[0014] Multiple ignition time deviations of the air gun are obtained by subtracting the multiple actual ignition times from the ignition times when the corresponding AGC modules send ignition commands to the air gun.

[0015] The ignition time deviation of the air gun is obtained by processing the multiple ignition time deviations.

[0016] Optionally, determining the ignition time deviation of the air gun based on historical ignition monitoring data and the ignition command corresponding to the historical ignition monitoring data includes:

[0017] Based on the historical ignition monitoring data of the air gun at the previous moment, the actual ignition time of the air gun at the previous moment is determined.

[0018] The ignition time deviation of the air gun is obtained by subtracting the actual ignition time from the ignition time at which the AGC module sends the ignition command to the air gun at the previous moment.

[0019] Optionally, the method further includes:

[0020] The ignition of the air gun is monitored in real time to obtain ignition monitoring data;

[0021] The ignition monitoring data is transmitted back and stored to determine the ignition time deviation of the air gun.

[0022] Compared with prior art, the present invention has the following advantages:

[0023] The present invention provides a synchronous ignition control for an air gun, which determines the ignition time deviation of the air gun based on historical ignition monitoring data and the ignition command corresponding to the historical ignition monitoring data; determines the target delay of data transmission by monitoring the data transmission delay between the GSC module and each AGC module in the marine seismic source control system; sums the ignition time in the current ignition command that controls the air gun to ignite with the target delay to obtain the first ignition time for controlling the air gun to ignite; and controls the air gun to ignite based on the first ignition time and the ignition time deviation. Therefore, the time delay in transmitting the ignition command through the line is first considered to obtain a first ignition time. Controlling the air gun to ignite based on this first ignition time eliminates the time delay in transmitting the ignition command, thus improving the ignition accuracy of synchronous ignition when multiple air guns ignite. Furthermore, considering the time delay between sending the ignition command and the air gun receiving the command and executing the ignition task, an ignition time deviation is obtained. Controlling the air gun to ignite based on the first ignition time and the ignition time deviation eliminates not only the time delay in transmitting the ignition command through the line but also the time delay between sending the ignition command and the air gun receiving the command and executing the ignition task, further improving the ignition accuracy of synchronous ignition when multiple air guns ignite.

[0024] A second aspect of this invention provides a synchronous ignition control system for air guns. The aim is to improve the ignition accuracy of a marine seismic source control system in controlling the synchronous ignition of multiple air guns.

[0025] The present invention provides an air gun synchronous ignition control system, the system comprising at least a host module, a GSC module and an AGC module;

[0026] The host module is used to determine the ignition time deviation of the air gun based on the historical ignition monitoring data of the air gun and the ignition command corresponding to the historical ignition monitoring data.

[0027] The AGC module is used to receive the ignition command sent by the GSC module, determine the target delay of data transmission by monitoring the data transmission delay between the GSC module in the marine seismic source control system and itself, and sum the ignition time in the current ignition command that controls the air gun to ignite the air gun to obtain the first ignition time for controlling the air gun to ignite the air gun.

[0028] The AGC module is also used to control the air gun to ignite based on the first ignition time and the ignition time deviation.

[0029] A third aspect of the present invention provides an electronic device, including a processor, a communication interface, a memory, and a communication bus, wherein the processor, the communication interface, and the memory communicate with each other through the communication bus;

[0030] Memory, used to store computer programs;

[0031] The processor, when executing a program stored in memory, implements the steps of the air gun synchronous ignition control method described in the first aspect.

[0032] A fourth aspect of the present invention provides a computer-readable storage medium having a computer program stored thereon, wherein the computer program, when executed by a processor, implements the steps of the air gun synchronous ignition control method described in the first aspect above. Attached Figure Description

[0033] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0034] Figure 1 This is a flowchart of a method for controlling synchronized ignition of an air gun according to an embodiment of the present invention;

[0035] Figure 2 This is another flowchart of a method for controlling synchronous ignition of an air gun provided in an embodiment of the present invention;

[0036] Figure 3 This is a schematic diagram of a synchronous ignition control system for an air gun provided in an embodiment of the present invention. Detailed Implementation

[0037] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0038] Figure 1 This is a flowchart of a method for controlling synchronized ignition of an air gun according to an embodiment of the present invention, such as... Figure 1 As shown, this method is applied to a marine seismic source control system, including:

[0039] Step S101: Determine the ignition time deviation of the air gun based on the historical ignition monitoring data of the air gun and the ignition command corresponding to the historical ignition monitoring data;

[0040] Step S102: Determine the target delay for data transmission by monitoring the data transmission delay between the GSC module and each AGC module in the marine seismic source control system;

[0041] Step S103: Sum the ignition time in the current ignition command that controls the air gun to ignite and the target delay to obtain the first ignition time that controls the air gun to ignite.

[0042] Step S104: Control the air gun to ignite according to the first ignition time and the ignition time deviation.

[0043] In this embodiment of the invention, the marine seismic source control system includes a navigation system, a host, a time control unit (TCU), a gun string controller (GSC), multiple air gun control units (AGC) connected to air guns respectively, and multiple air guns, wherein one air gun control unit (AGC) corresponds to one air gun, and the two have a one-to-one correspondence.

[0044] In this embodiment of the invention, step S101 is executed by the host computer in the marine seismic source control system.

[0045] Specifically, after each air gun completes its ignition, the relevant sensors on each air gun collect monitoring data during ignition and transmit this data back to its corresponding air gun control unit (AGC). This module digitizes the ignition monitoring data returned by the sensors and then sends the digitized data back to the main unit for storage via the air gun group control module (GSC) and the time control module (TCU). These relevant sensors include gun motion sensors, near-field wavelet sensors, and depth / pressure sensors.

[0046] Meanwhile, the ignition command for a single ignition mission is generated by the Time Control Unit (TCU) within the marine seismic source control system. The generation process involves the construction vessel moving to the location designated by the navigation system. The navigation system sends the air gun point number (air gun number) and source number (the number of the air gun's platoon) to the main unit for this ignition mission. The main unit then processes the received air gun point number and source number and sends them to the TCU. Simultaneously, the navigation system sends the pulse signal corresponding to the ignition command to the TCU. The TCU then generates the actual ignition command based on this pulse signal. After receiving the pulse signal from the navigation system, the TCU calibrates its own time based on the received GPS signal from the navigation system to ensure the accuracy of the ignition command generation time. After time calibration, the TCU generates the ignition command based on the received air gun point number, source number, and pulse signal. This ignition command includes the ignition time indicating the air gun ignition.

[0047] After the timing control module (TCU) generates the ignition command, it sends the ignition command to the host so that the host can determine the ignition time deviation of the air gun based on the received ignition command. At the same time, the ignition command is sent to the air gun group control module (GSC).

[0048] Therefore, the host in the marine seismic source control system will receive each ignition command, and simultaneously receive historical ignition monitoring data obtained after each ignition command controls the air gun to perform the ignition task. Based on the received historical ignition monitoring data of the air gun and the ignition command corresponding to that historical ignition monitoring data, the host will determine the ignition time deviation of the air gun, that is, the time deviation between the time when the AGC corresponding to the air gun sends the ignition command to the air gun and the actual ignition time of the air gun. Furthermore, since multiple air guns will ignite simultaneously in one ignition task, the host in the marine seismic source control system will obtain the ignition time deviation of each of these multiple air guns by executing step S101.

[0049] For example, the air guns performing the ignition task include A, B, C, D, and E. The ignition time deviation to air gun A is determined based on the historical ignition monitoring data of air gun A and the corresponding ignition command. Similarly, the ignition time deviation to air gun B is determined based on the historical ignition monitoring data of air gun B and the corresponding ignition command. The ignition time deviation to air gun C is determined based on the historical ignition monitoring data of air gun C and the corresponding ignition command. The ignition time deviation to air gun D is determined based on the historical ignition monitoring data of air gun D and the corresponding ignition command. Finally, the ignition time deviation to air gun E is determined based on the historical ignition monitoring data of air gun E and the corresponding ignition command.

[0050] In this embodiment of the invention, due to the time delay in signal transmission through the lines, and the different time delays of different lines, the ignition command received by each air gun control unit (AGC) at different times during the distribution of the ignition command from the air gun group control module (GSC) to each air gun control unit (AGC) will result in a large deviation in the actual ignition time of each air gun, leading to low ignition accuracy for simultaneous ignition of multiple air guns. To solve this problem, this invention adds a preset duration to the ignition time in the ignition command after each air gun control unit (AGC) receives the ignition command. This means that after receiving the ignition command, the AGC does not immediately send it to its corresponding air gun, but waits until the preset duration is reached before sending the ignition command to its corresponding air gun to control it to ignite. This improves the ignition accuracy for simultaneous ignition of multiple air guns.

[0051] Specifically, steps S102 and S13 in this invention are executed by the respective air gun control units (AGCs) in the marine seismic source control system. After receiving the ignition command, each air gun control unit (AGC) parses and obtains the ignition time in the ignition command, and adds a preset duration to the ignition time in the ignition command to obtain the first ignition time.

[0052] For example, multiple air guns performing the ignition task include A, B, C, D, and E. The air gun control units (AGCs) corresponding to each air gun are A0, B0, C0, D0, and E0, respectively. The ignition time in the ignition command is T0. Since the time delay of the ignition command being distributed from the air gun group control module (GSC) to each air gun control unit (AGC) is different, it is assumed that the time when air gun control unit A0 receives the ignition command is T0+a0; the time when air gun control unit B0 receives the ignition command is T0+b0; the time when air gun control unit C0 receives the ignition command is T0+c0; the time when air gun control unit D0 receives the ignition command is T0+d0; and the time when air gun control unit E0 receives the ignition command is T0+e0. If each airgun control unit (AGC) immediately sends an ignition command to its corresponding airgun upon receiving the ignition command, the timing of these commands will differ. Consequently, the timing of each airgun receiving the command and executing the ignition will also differ, resulting in low ignition accuracy for simultaneous ignition of multiple airguns. To address this problem, after receiving the ignition command, each AGC analyzes the ignition time T0 and adds a preset duration to T0 to obtain a first ignition time. Upon reaching this first ignition time, each AGC sends its ignition command to its corresponding airgun. This ensures that each AGC sends its ignition command to its respective airgun at the same time, eliminating the time delay in the distribution of the ignition command from the airgun group control module (GSC) to the individual AGCs, thus improving the ignition accuracy for simultaneous ignition of multiple airguns.

[0053] In this embodiment of the invention, to avoid the problem that other air gun control units (AGCs) have already issued ignition commands at the first ignition time while the air gun control unit AGC corresponding to the line time delay has not yet received the ignition command, resulting in the first ignition time being lower than the sum of the ignition time T0 of the ignition command and the line time delay, for example, if the ignition time is T0, and the time delay from the air gun group control module (GSC) to the air gun control unit AGC corresponding to that air gun control unit AGC is 30µs, while the preset duration is only 20µs, when all other air gun control units AGCs have issued ignition commands at T0+20µs, that one air gun control unit AGC has not yet received the ignition command, thus reducing the ignition accuracy of multiple air guns igniting simultaneously, the aforementioned preset duration in this invention is greater than any line time delay from the air gun group control module (GSC) to the air gun control unit AGC in the execution of the ignition task. To ensure the air gun can ignite as quickly as possible, the preset duration should be a smaller value than the line time delay from the air gun group control module GSC to the air gun control unit AGC during the ignition process. Therefore, this invention determines the preset duration through the following implementation method: Specifically, multiple time delays are obtained by monitoring the data transmission delays between the GSC module and each AGC module in the marine seismic source control system. These multiple time delays are then processed to obtain the target delay for data transmission, which is the aforementioned preset duration. The first ignition time is obtained by adding this target delay to the ignition time in the current ignition command that controls the air gun to ignite.

[0054] One implementation method for processing the multiple time delays to obtain the target delay for data transmission is to take the maximum value among the multiple time delays and multiply it by a preset coefficient to obtain the final target delay. The preset coefficient is greater than 1. It should be understood that the above implementation method for processing the multiple time delays to obtain the target delay for data transmission is only a preferred embodiment. The determination of the target delay in this invention can also be achieved through other implementation methods, which are not specifically limited here.

[0055] In this embodiment of the invention, step S104 is executed by each airgun control unit (AGC) in the marine seismic source control system. Since there is a time delay when each AGC sends the ignition command to its corresponding airgun, and these time delays vary among different AGCs, the ignition accuracy of simultaneous ignition of multiple airguns is reduced. This time delay cannot be eliminated by the methods described in steps S102 and S103. To address this time delay and further improve the ignition accuracy of simultaneous ignition of multiple airguns, this invention uses the first ignition time and the ignition time deviation determined in step S101 to eliminate the time delay when the AGC sends the ignition command to the corresponding airgun, thereby further improving the ignition accuracy of simultaneous ignition of multiple airguns.

[0056] Specifically, each air gun control unit (AGC) obtains the actual ignition time of the ignition command sent by each AGC based on its own first ignition time and its own ignition time deviation. Each AGC then sends the ignition command to its corresponding air gun based on the actual ignition time it obtained, in order to control each air gun to ignite.

[0057] In this invention, controlling the air gun to ignite based on the first ignition time and the ignition time deviation includes: obtaining a second ignition time by subtracting the first ignition time and the ignition time deviation from the first ignition time; and sending an ignition command to the air gun via the AGC module when the second ignition time is reached, thereby controlling the air gun to ignite.

[0058] In this embodiment of the invention, each air gun control unit (AGC) calculates a second ignition time by subtracting its first ignition time from its own ignition time deviation. Each AGC then issues an ignition command to its corresponding air gun at its second ignition time to control the air gun to perform the ignition task.

[0059] For example, the multiple air guns performing the ignition task include A, B, C, D, and E. The air gun control units (AGCs) corresponding to each air gun are A0, B0, C0, D0, and E0, respectively. The ignition time in the ignition command is T0, and the first ignition time of the air gun control unit (AGC) is T0+α. Step S101 determines the ignition time deviation of air gun A as a1 (that is, if the A0 air gun control unit issues an ignition command at time T1, then air gun A will ignite at time T1+a1); determines the ignition time deviation of air gun B as b1; determines the ignition time deviation of air gun C as c1; determines the ignition time deviation of air gun D as d1; and determines the ignition time deviation of air gun E as e1. The A0 air gun control unit will issue an ignition command to the corresponding air gun at time T0+α-a1; the B0 air gun control unit will issue an ignition command to the corresponding air gun at time T0+α-b1; the C0 air gun control unit will issue an ignition command to the corresponding air gun at time T0+α-c1; the D0 air gun control unit will issue an ignition command to the corresponding air gun at time T0+α-d1; and the E0 air gun control unit will issue an ignition command to the corresponding air gun at time T0+α-e1. This eliminates the time delay between the ignition command being sent from the air gun control unit (AGC) to the air gun, thereby further improving the ignition accuracy of simultaneous ignition from multiple air guns.

[0060] In this embodiment of the invention, when determining the target delay of the air gun control unit (AGC), a preset coefficient is determined based on the ignition time deviation of each AGC. This ensures that after each AGC obtains its first ignition time, the resulting second ignition time (after subtracting its ignition time deviation) is always greater than the time it received the ignition command. This is to prevent some AGCs from calculating a second ignition time that is less than the time they received the ignition command, thus causing a control malfunction because they failed to receive the ignition command when it should have sent it.

[0061] In this embodiment of the invention, after each air gun control unit (AGC) sends an ignition command at the second ignition time, it feeds back the feedback information, including the second ignition time, to the host through the time control module (TCU) and the air gun group control module (GSC), so that the host can determine the ignition time deviation based on the feedback information.

[0062] In this invention, determining the ignition time deviation of the air gun based on historical ignition monitoring data and the ignition command corresponding to the historical ignition monitoring data includes: determining multiple actual ignition times of the air gun based on multiple historical ignition monitoring data; obtaining multiple ignition time deviations of the air gun by subtracting the multiple actual ignition times from the ignition times when the corresponding AGC modules send ignition commands to the air gun; and obtaining the ignition time deviation of the air gun by processing the multiple ignition time deviations.

[0063] In one embodiment of the invention, one method for determining the ignition time deviation of an air gun is as follows: For any air gun among all air guns performing the ignition task, multiple historical ignition monitoring data are obtained by monitoring multiple ignition processes of that air gun (one historical ignition monitoring data corresponds to one ignition). The host computer then parses these multiple historical ignition monitoring data to obtain multiple actual ignition times for that air gun.

[0064] Simultaneously, by utilizing the feedback information from the air gun control unit (AGC) corresponding to each of the multiple historical ignition monitoring data, the host obtains multiple ignition times—that is, multiple second ignition times—when the air gun control unit (AGC) sends ignition commands to each air gun. By subtracting the multiple actual ignition times from their respective corresponding second ignition times, multiple ignition time deviations are obtained.

[0065] The final ignition time deviation of any given air gun is obtained by averaging the multiple ignition time deviations. This final ignition time deviation is then determined as the ignition time deviation for subsequent ignition tasks performed by that air gun.

[0066] In this invention, determining the ignition time deviation of the air gun based on historical ignition monitoring data and the ignition command corresponding to the historical ignition monitoring data includes: determining the actual ignition time of the air gun at the previous moment based on historical ignition monitoring data of the air gun at the current moment; and obtaining the ignition time deviation of the air gun by subtracting the actual ignition time from the ignition time at which the AGC module sends the ignition command to the air gun at the previous moment.

[0067] In an embodiment of the present invention, another way to determine the ignition time deviation of the air gun is to use the ignition time deviation determined by each ignition task to solve for the second ignition time when the air gun control unit AGC issues the ignition command next time.

[0068] Specifically, for any air gun among all air guns performing the ignition task, the host analyzes the historical ignition monitoring data of that air gun from the previous moment to obtain the actual ignition time of that air gun at the current moment. Using the feedback information from the AGC (Automatic Generator Control Unit) of the air gun corresponding to the historical ignition monitoring data from the previous moment, the host obtains the ignition time at which the AGC sent the ignition command at the previous moment, i.e., the second ignition time. By subtracting the actual ignition time from the previous moment's second ignition time, the ignition time deviation of that air gun at the current moment is obtained, which is used to calculate the second ignition time at which the AGC of the air gun issues the ignition command at the current moment.

[0069] In this invention, the method further includes: real-time monitoring of the ignition of the air gun to obtain ignition monitoring data; and transmitting and storing the ignition monitoring data to determine the ignition time deviation of the air gun.

[0070] In this embodiment of the invention, the relevant sensors on each air gun will monitor the ignition of its own air gun in real time to obtain ignition monitoring data for each ignition task. After obtaining the ignition monitoring data, the ignition monitoring data is transmitted back to the host computer for calculation of the ignition time deviation of each air gun, as well as for the determination and analysis of other relevant data.

[0071] In embodiments of the present invention, such as Figure 2 As shown, the air gun synchronous ignition control method provided by the present invention mainly includes three stages: ignition preparation stage, ignition stage, and data feedback stage.

[0072] During the ignition preparation phase, after the construction vessel moves to the location designated by the navigation system, the navigation system sends the air gun point number (air gun number) and source number (the number of the air gun's array) to the main unit. The main unit then processes the received air gun point number and source number and sends them to the time control module (TCU). Simultaneously, the navigation system sends the pulse signal corresponding to the ignition command to the TCU. After receiving the command from the navigation system, the TCU calibrates its own time based on the GPS signal it receives from the navigation system.

[0073] During the ignition phase, the Time Control Unit (TCU) receives the air gun point number and source number from the host and the pulse signal from the navigation system, processes them for a preset duration (preferably 50µs), and integrates the ignition time with the air gun point number and source number for this operation into an ignition command. The TCU then sends the integrated ignition command to the Air Gun Group Control Module (GSC) and returns the ignition command to the host, which stores this command to calculate the ignition time deviation for subsequent air guns. Upon receiving the ignition command, the GSC sends ignition commands to each air gun control unit (AGC). Each AGC, upon receiving the ignition command, calculates the actual ignition time for each air gun based on the ignition time deviation, which is the second ignition time when the AGC issues its ignition command. After calculating the second ignition time for each AGC, it issues an ignition command to its corresponding air gun at its respective second ignition time to control the synchronous firing of all air guns. Although the time delay in sending the ignition command from the air gun control unit (AGC) to the air gun has been eliminated based on the previous ignition timing deviation, the ignition timing deviation of an air gun varies each time due to the superposition of various factors. The previous ignition timing deviation only partially eliminates the time delay in sending the ignition command from the AGC to the air gun. In the current ignition task, the actual ignition time of the air gun will still have a certain error compared to the calculated desired ignition time. This error will be received and recorded by relevant sensors near the air gun and used to determine the ignition timing deviation for this ignition task. The actual ignition time of the air gun will be transmitted back to the navigation system, which will record this time for post-construction data analysis and also transmit it back to the main unit for subsequent determination of the ignition timing deviation for this ignition task.

[0074] During the data feedback phase, after the air gun completes its ignition, the relevant sensors on the air gun transmit the collected ignition monitoring data back to the air gun control unit (AGC). This digitized ignition monitoring data is then sent back to the host unit via the air gun group control module (GSC) and the time control module (TCU). Upon receiving the transmitted ignition monitoring data, the host unit first stores the data and then uses an algorithm to calculate the ignition time deviation for each air gun. This deviation is then transmitted back to the corresponding air gun control unit (AGC) via the time control module (TCU) and the air gun group control module (GSC). Based on the ignition time deviation, the AGC determines the second ignition time for issuing the ignition command to ensure synchronized firing of the air guns.

[0075] This completes the timing control process for the air gun ignition. As long as this process is maintained throughout the subsequent operation of the system, it can be ensured that the air guns can be ignited synchronously with a time error of no more than 0.1ms.

[0076] The actual ignition time of the air gun will be transmitted back to the navigation system, which will record the time for data analysis and other purposes after construction.

[0077] This invention also provides an air gun synchronous ignition control system 300, such as... Figure 3 As shown, the system 300 includes at least a host module 301, a GSC module 302, and an AGC module 303;

[0078] The host module is used to determine the ignition time deviation of the air gun based on the historical ignition monitoring data of the air gun and the ignition command corresponding to the historical ignition monitoring data.

[0079] The AGC module is used to receive the ignition command sent by the GSC module, determine the target delay of data transmission by monitoring the data transmission delay between the GSC module in the marine seismic source control system and itself, and sum the ignition time in the current ignition command that controls the air gun to ignite the air gun to obtain the first ignition time for controlling the air gun to ignite the air gun.

[0080] The AGC module is also used to control the air gun to ignite based on the first ignition time and the ignition time deviation.

[0081] Optionally, the AGC module includes:

[0082] The second ignition time determination module is used to obtain the second ignition time by subtracting the first ignition time from the ignition time deviation to obtain the second ignition time when the AGC module sends the ignition command to the air gun.

[0083] The ignition command sending module is used to send an ignition command to the air gun via the AGC module when the second ignition time is reached, so as to control the air gun to ignite.

[0084] Optionally, the host module includes:

[0085] The first actual ignition time determination module is used to determine multiple actual ignition times of the air gun based on multiple historical ignition monitoring data of the air gun.

[0086] The first ignition time deviation determination module is used to obtain multiple ignition time deviations of the air gun by subtracting the multiple actual ignition times from the ignition time when the corresponding AGC module sends the ignition command to the air gun.

[0087] The second ignition time deviation determination module is used to obtain the ignition time deviation of the air gun by processing the multiple ignition time deviations.

[0088] Optionally, the host module includes:

[0089] The second actual ignition time determination module is used to determine the actual ignition time of the air gun in the previous moment based on the historical ignition monitoring data of the air gun in the previous moment of the current moment.

[0090] The ignition time deviation determination module is used to obtain the ignition time deviation of the air gun by subtracting the actual ignition time from the ignition time when the AGC module sends an ignition command to the air gun at the previous moment.

[0091] Optionally, the system 300 further includes:

[0092] The monitoring module is used to monitor the ignition of the air gun in real time and obtain ignition monitoring data;

[0093] The data feedback module is used to feed back and store the ignition monitoring data in order to determine the ignition time deviation of the air gun.

[0094] This invention also provides an electronic device, including a processor, a communication interface, a memory, and a communication bus, wherein the processor, the communication interface, and the memory communicate with each other through the communication bus; the memory is used to store computer programs; and the processor, when executing the program stored in the memory, implements the steps in the air gun synchronous ignition control method.

[0095] This invention also provides a computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the steps in the air gun synchronous ignition control method.

[0096] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0097] The various embodiments in this specification are described in a related manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, the system embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions of the method embodiments.

[0098] The above description is merely a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention are included within the scope of protection of the present invention.

Claims

1. A method for controlling synchronized ignition of an air gun, characterized in that, The method is applied to a marine seismic source control system, including: The ignition time deviation of the air gun is determined based on the historical ignition monitoring data of the air gun and the ignition command corresponding to the historical ignition monitoring data. The target delay for data transmission is determined by monitoring the data transmission delay between the GSC module and each AGC module in the marine seismic source control system. The ignition time in the current ignition command that controls the air gun to ignite is summed with the target delay to obtain the first ignition time for controlling the air gun to ignite. The air gun is controlled to ignite based on the first ignition time and the ignition time deviation. The step of controlling the air gun to ignite based on the first ignition time and the ignition time deviation includes: The second ignition time is obtained by subtracting the first ignition time from the ignition time deviation. When the second ignition time is reached, an ignition command is sent to the air gun via the AGC module to control the air gun to ignite.

2. The air gun synchronous ignition control method according to claim 1, characterized in that, The step of determining the ignition time deviation of the air gun based on historical ignition monitoring data and the ignition commands corresponding to the historical ignition monitoring data includes: Based on multiple historical ignition monitoring data of the air gun, multiple actual ignition times of the air gun are determined. Multiple ignition time deviations of the air gun are obtained by subtracting the multiple actual ignition times from the ignition times when the corresponding AGC modules send ignition commands to the air gun. The ignition time deviation of the air gun is obtained by processing the multiple ignition time deviations.

3. The air gun synchronous ignition control method according to claim 1, characterized in that, The step of determining the ignition time deviation of the air gun based on historical ignition monitoring data and the ignition commands corresponding to the historical ignition monitoring data includes: Based on the historical ignition monitoring data of the air gun at the previous moment, the actual ignition time of the air gun at the previous moment is determined. The ignition time deviation of the air gun is obtained by subtracting the actual ignition time from the ignition time at which the AGC module sends the ignition command to the air gun at the previous moment.

4. The air gun synchronous ignition control method according to claim 1, characterized in that, The method further includes: The ignition of the air gun is monitored in real time to obtain ignition monitoring data; The ignition monitoring data is transmitted back and stored to determine the ignition time deviation of the air gun.

5. A synchronous ignition control system for an air gun, characterized in that, The system includes at least a host module, a GSC module, and an AGC module; The host module is used to determine the ignition time deviation of the air gun based on the historical ignition monitoring data of the air gun and the ignition command corresponding to the historical ignition monitoring data. The AGC module is used to receive the ignition command sent by the GSC module, determine the target delay of data transmission by monitoring the data transmission delay between the GSC module in the marine seismic source control system and itself, and sum the ignition time in the current ignition command that controls the air gun to ignite the air gun to obtain the first ignition time for controlling the air gun to ignite the air gun. The AGC module is also used to control the air gun to ignite based on the first ignition time and the ignition time deviation. The AGC module includes: The second ignition time determination module is used to obtain the second ignition time by subtracting the first ignition time from the ignition time deviation to obtain the second ignition time when the AGC module sends the ignition command to the air gun. The ignition command sending module is used to send an ignition command to the air gun via the AGC module when the second ignition time is reached, so as to control the air gun to ignite.

6. An electronic device, characterized in that, It includes a processor, a communication interface, a memory, and a communication bus, wherein the processor, the communication interface, and the memory communicate with each other through the communication bus; Memory, used to store computer programs; The processor, when executing a program stored in the memory, implements the steps of the air gun synchronous ignition control method according to any one of claims 1-4.

7. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by the processor, it implements the steps in the air gun synchronous ignition control method as described in any one of claims 1-4.

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