Aerodynamic balance sound compensation system suitable for deep sea low frequency sound source and design method thereof

Abstract

The application provides a pneumatic balance sound compensation system suitable for a deep-sea low-frequency sound source and a design method thereof. The static pressure balance between a gas chamber and seawater is realized by converting the selected working gas liquid phase and gas phase, and further, the pneumatic imbalance caused by sound radiation is compensated by a mechanical margin in a certain volume V space, so as to effectively realize acoustic compensation. The certain volume V space is determined according to whether the dynamic pressure difference variable generated in the gas chamber space during the sound wave radiation process corresponding to the maximum sound source level of the sound source in the working state is less than the mechanical balance margin constraint condition of the certain volume V space. The mechanical balance margin constraint condition of the space is a structural mechanics bearing margin, including a thrust margin constraint when the motor power is selected. The application aims at the underwater working depth problem of the extended low-frequency sound source (low-frequency, high-sound source level and large-amplitude sound radiation source), and specifically aims at the sound compensation difficulty problem of the low-frequency and large-amplitude sound radiation source under the deep-sea static pressure condition.

Description

Technical Field

[0001] This invention belongs to the field of underwater acoustic engineering technology in the marine field, specifically relating to an aerodynamically balanced acoustic compensation system and its design method suitable for deep-sea low-frequency sound sources. Background Technology

[0002] In underwater acoustics engineering, traditional sound sources are typically piezoelectric transducers made of piezoelectric materials, operating in the mid-to-high frequency range. For low frequencies, bending transducers are used, allowing the sound source frequency to extend down to several hundred hertz. These sources generally perform well in shallow waters. However, as the operating depth increases, underwater sound sources face the challenge of compensating for hydrostatic pressure, and this difficulty increases with depth. While airbags can be used for sound compensation up to 100 meters, the compression of the gas rapidly reduces its compensation capability, eventually rendering it ineffective. Therefore, achieving deep-sea compensation for low-frequency sound sources presents significant technical challenges.

[0003] Foreign countries are also conducting relevant research on deep-sea compensation for low-frequency sound sources. According to data analysis, the United States and Japan have some literature on deep-sea compensation for low-frequency sound sources. Both the United States and Japan have used unconventional acoustic techniques, namely non-acoustic transducer technology, to realize low-frequency sound sources. In addition, American literature has reported a summary of suitable depth pressure compensation methods at different depths. It mentions that hydraulic compensation is a universal method suitable for all ocean depths, but the system is relatively complicated. In shallow seas, the problem is relatively simple, and airbags can be used for compensation. Summary of the Invention

[0004] This invention provides an aerodynamically balanced acoustic compensation system and its design method suitable for deep-sea low-frequency sound sources, addressing the problem of extending the underwater working depth of low-frequency sound sources (low-frequency, high-sound-level, large-amplitude sound radiation sources), specifically addressing the difficulty of acoustic compensation under deep-sea hydrostatic conditions for low-frequency, large-amplitude sound radiation sources.

[0005] This invention is achieved through the following technical solution:

[0006] A design method for an aerodynamically balanced acoustic compensation system suitable for deep-sea low-frequency sound sources is proposed. This method utilizes the liquid and gas phase conversion of a selected working gas to achieve static pressure balance between the gas chamber and seawater. Furthermore, it effectively achieves acoustic compensation by compensating for the dynamic pressure imbalance caused by sound radiation within a certain volume V space through mechanical margin compensation.

[0007] The space of a certain volume V is determined based on whether the dynamic pressure difference variable generated in the air chamber space and the external seawater pressure during the sound wave radiation process corresponding to the maximum sound source level when the sound source is in working state is less than the mechanical balance margin constraint condition of the space of a certain volume V.

[0008] The mechanical balance margin constraint of the space is the structural mechanical bearing margin, including the thrust margin constraint when selecting motor power.

[0009] Furthermore, the design method specifically involves achieving static pressure balance between the inner gas chamber and the outer seawater by selecting the liquid and gas phase conversion of the working gas, and further achieving acoustic compensation by compensating for the aerodynamic pressure imbalance caused by sound radiation through the pressure margin of the mechanical structure within a certain volume V. The selection of motor power and space volume V parameters are mutually influential and restrictive. The volume is confirmed and verified based on the selected motor, or the motor is selected and verified based on the volume.

[0010] Furthermore, the working gas is selected based on the working depth and the phase transition point of the gas.

[0011] Furthermore, the parameter selection for choosing and verifying the motor based on volume includes the following steps:

[0012] Step 1: Determine the maximum amplitude and drainage volume of the radiating plate based on the sound source level and the diameter of the radiating plate;

[0013] Step 2: Based on the maximum amplitude and drainage of the radiating plate in Step 1, initially select the space volume V within the usable space provided by the system device. Driven by the motor, the radiating plate reciprocates, causing the pressure in the air chamber to exhibit two states of periodic decrease and increase. Calculate the maximum value of the dynamic pressure difference change brought about by the reciprocating motion of the radiating plate to the gas in the air chamber of volume V when the sound source is working.

[0014] Step 3: Based on the maximum value of the dynamic pressure difference change in Step 2, obtain the maximum value of the force increment on the radiant plate due to acoustic radiation;

[0015] Step 4: Based on the requirements of the sound source level and the force increment in Step 3, select the power of the motor so that the thrust of the motor can meet the force required for the maximum sound source level radiation and the maximum value of the force increment caused by the dynamic pressure difference.

[0016] Step 5: Based on the motor power selected in Step 4, confirm whether the power supply system can guarantee power supply and whether the motor can be installed; if the requirements are met, end the parameter confirmation process; if not, return to Step 2, readjust the V setting, and repeat the subsequent steps until the requirements are met.

[0017] Furthermore, the method for confirming and verifying the motor volume specifically involves selecting the motor power level based on the sound source level and the power supply capacity of the working environment. The selection of the motor power level should ensure that the thrust provided by the motor covers the thrust required by the sound source level and leave an appropriate margin for withstanding dynamic pressure differences. Then, the volume of space V is calculated based on the pressure margin of the motor, and its feasibility is confirmed. If the space requirements are met, the parameter confirmation process ends; if not, a new selection is made until the requirements are met.

[0018] An aerodynamically balanced sound compensation system suitable for low-frequency sound sources in deep sea is provided. The sound compensation system is connected to the low-frequency sound source through a standard flange interface and is used in conjunction with the low-frequency sound source.

[0019] Furthermore, the sound compensation system includes a high-pressure gas cylinder I, a high-pressure gas cylinder II, a pressure-resistant gas tank, a sealed air chamber, a standard flange interface, and a gas path control system I and a gas path control system II. The high-pressure gas cylinder I is connected to the gas path control system I, the gas path control system I is connected to the pressure-resistant gas tank, the pressure-resistant gas tank is connected to the sealed air chamber, the sealed air chamber is connected to the standard flange interface, and the standard flange interface is connected to the sound radiation system.

[0020] The gas circuit control system I and gas circuit control system II are connected to the control console via cables;

[0021] All of the above connections are sealed connections.

[0022] Furthermore, the sound radiation system is a motor-driven low-frequency sound source with a compensation port or other low-frequency sound sources with an airbag that can be externally compensated, thus extending its working depth.

[0023] Furthermore, the gas circuit control system I includes differential pressure control switch I 51, differential pressure control switch II 52, differential pressure control switch III 53, multi-point depth control valve 54, and pressure reducing valve 55;

[0024] The high-pressure gas cylinder I 56 is connected to a pressure reducing valve 55. The pressure reducing valve 55 is connected to a differential pressure control switch III 53 and a multi-point depth control valve 54. The multi-point depth control valve 54 is connected to a differential pressure control switch II 52. The differential pressure control switch II 52 is connected to a sealed gas chamber 57.

[0025] The differential pressure control switch Ⅲ53 is connected to the differential pressure control switch Ⅰ51, and the differential pressure control switch Ⅰ51 is connected to the sealed air chamber 57;

[0026] The gas path control system I and the gas path control system II have the same structure.

[0027] The beneficial effects of this invention are:

[0028] This invention can be used with various existing sound sources that use ordinary airbag compensation to expand the working depth of the sound source, and is especially suitable for use with large amplitude Hertz-level low-frequency sound sources that use motors as drives.

[0029] This invention provides a typical practical device for a motor-driven low-frequency sound source operating at a depth of 300 meters underwater. It achieves backflow compensation of sound radiation at a depth of 300 meters by utilizing the liquid-to-gas phase conversion of selected carbon dioxide gas. With this compensation technology, effective sound radiation can be achieved at a depth of 300 meters.

[0030] The present invention selects the working gas based on the pressure at the working depth, and the phase change pressure of the working gas should be greater than the pressure value at the working depth. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the structure of the present invention.

[0032] Figure 2 This is a graph showing the relationship between the carbon dioxide phase state and pressure and temperature according to the present invention.

[0033] Figure 3 This is a schematic diagram of the gas path control system of the present invention.

[0034] Figure 4 This is a schematic diagram of the structure of the present invention when the extended arm is closed, wherein (a) is a schematic diagram of the single radiating plate structure when the extended arm is closed, and (b) is a schematic diagram of the double radiating structure when the extended arm is closed.

[0035] Figure 5 This is a schematic diagram of the structure of the extended arm of the present invention when it is unfolded, wherein (a) is a schematic diagram of the single radiating plate structure when the extended arm is unfolded, and (b) is a schematic diagram of the double radiating structure when the extended arm is unfolded. Detailed Implementation

[0036] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0037] A design method for an aerodynamically balanced acoustic compensation system suitable for deep-sea low-frequency sound sources is proposed. This method utilizes the liquid and gas phase conversion of a selected working gas to achieve static pressure balance between the gas chamber and seawater. Furthermore, it effectively achieves acoustic compensation by compensating for the dynamic pressure imbalance caused by sound radiation within a certain volume V space through mechanical margin compensation.

[0038] The space of a certain volume V is determined based on whether the dynamic pressure difference variable generated in the air chamber space and the external seawater pressure during the sound wave radiation process corresponding to the maximum sound source level when the sound source is in working state is less than the mechanical balance margin constraint condition of the space of a certain volume V.

[0039] The mechanical balance margin constraint of the space is the structural mechanical bearing margin, including the thrust margin constraint when selecting motor power.

[0040] Furthermore, the design method specifically involves achieving static pressure balance between the inner gas chamber and the outer seawater by selecting the liquid and gas phase conversion of the working gas, and further achieving acoustic compensation by compensating for the aerodynamic pressure imbalance caused by sound radiation through the pressure margin of the mechanical structure within a certain volume V. The selection of motor power and space volume V parameters are mutually influential and restrictive. The volume is confirmed and verified based on the selected motor, or the motor is selected and verified based on the volume.

[0041] Furthermore, the working gas is selected based on the working depth and the phase transition point of the gas.

[0042] In this example, the working depth is 300 meters, and the selected gas is carbon dioxide. Carbon dioxide is in the liquid phase under high pressure, and the pressure of the gas-liquid phase transition is 3.44 MPa, which is slightly greater than the ambient pressure at a depth of 300 meters. All gas selections using this method are protected by this patent.

[0043] Furthermore, the parameter selection for choosing and verifying the motor based on volume includes the following steps:

[0044] Step 1: Determine the maximum amplitude and drainage volume of the radiating plate based on the sound source level and the diameter of the radiating plate;

[0045] Step 2: Based on the maximum amplitude and drainage of the radiating plate in Step 1, initially select the space volume V within the usable space provided by the system device. Driven by the motor, the radiating plate reciprocates, causing the pressure in the air chamber to exhibit two states of periodic decrease and increase. Calculate the maximum value of the dynamic pressure difference change brought about by the reciprocating motion of the radiating plate to the gas in the air chamber of volume V when the sound source is working.

[0046] Step 3: Based on the maximum value of the dynamic pressure difference change in Step 2, obtain the maximum value of the force increment on the radiant plate due to acoustic radiation;

[0047] Step 4: Based on the requirements of the sound source level and the force increment in Step 3, select the power of the motor so that the thrust of the motor can meet the force required for the maximum sound source level radiation and the maximum value of the force increment caused by the dynamic pressure difference.

[0048] Step 5: Based on the motor power selected in Step 4, confirm whether the power supply system can guarantee power supply and whether the motor can be installed; if the requirements are met, end the parameter confirmation process; if not, return to Step 2, readjust the V setting, and repeat the subsequent steps until the requirements are met.

[0049] Furthermore, the method for confirming and verifying the motor volume specifically involves selecting the motor power level based on the sound source level and the power supply capacity of the working environment. The selection of the motor power level should ensure that the thrust provided by the motor covers the thrust required by the sound source level and leave an appropriate margin for withstanding dynamic pressure differences. Then, the volume of space V is calculated based on the pressure margin of the motor, and its feasibility is confirmed. If the space requirements are met, the parameter confirmation process ends; if not, a new selection is made until the requirements are met.

[0050] The following is a practical example based on the above method. Assuming a radiant sound source level of 160 (150) dB and a radiant plate with a diameter of 500, the maximum amplitude of the radiant plate is 2*0.53 cm, and the displacement is 2.1 L. Due to the reciprocating motion of the radiant plate driven by the motor, the pressure cycle in the air chamber exhibits two states: decrease and increase. Assuming the air chamber space is a volume of 300 L, the pressure difference caused by the reciprocating motion of the radiant plate is 0.0253 MPa. For a radiant plate of a given area, the resulting force increment is 4967 N. The thrust of the selected motor can meet the force increment, so a volume of 300 L is used. If the selected motor cannot cover the force increment requirement, the volume space is increased until the motor can cover the force increment requirement caused by the pressure difference. Alternatively, the force increment can be covered by improving the motor parameters.

[0051] Carbon dioxide gas is in the liquid phase under high pressure, such as Figure 2 As shown, the pressure for the gas-liquid phase transition is 3.44 MPa. This means that carbon dioxide is in a liquid state when the pressure is greater than 3.44 MPa, therefore a high-pressure gas cylinder can be used to store a sufficient amount of gas. Since the pressure in seawater increases by 1 atmosphere (0.1 MPa) for every 10 meters of depth, the pressure at a depth of 300 meters is 3 MPa. Therefore, carbon dioxide is in a gaseous phase at 3 MPa, making carbon dioxide gas suitable for compensating sound sources at depths around 300 meters. The principle for gas selection is that the phase transition pressure of the gas should be appropriately greater than the pressure corresponding to the working depth.

[0052] The specific compensation method of an aerodynamically balanced sound compensation system suitable for deep-sea low-frequency sound sources is as follows:

[0053] Under the control of the air circuit control system, the system is deployed in a segmented diving manner. During the deployment process, the air pressure in the air chamber is automatically controlled by the sound source diving depth compensation system to balance with the static pressure of seawater in the corresponding underwater environment until the predetermined working depth is reached and normal operation is achieved.

[0054] This application employs a segmented, stepped submersion control method to sink the sound source to the working depth and achieve pressure balance inside and outside the sound source. The gas cylinder is connected to the gas chamber via a gas path control system, which is as follows: Figure 3 As shown, it consists of a pressure reducing valve and two air circuit controls. The first air circuit control channel is designed to detect internal and external pressures, and controls a 50-meter differential pressure sensor through a depth sensor to perform pressure identification and control. The control air circuit is conditionally opened and closed. According to the diving depth of the sound source, the air circuit control switch is designed to be opened and closed in stages of 50 meters, 100 meters, 150 meters, 200 meters and 250 meters. It controls the first differential pressure switch. The differential pressure control value of the first differential pressure switch is set to 0.5MPa. The switch is opened when it is greater than 0.5MPa and closed when it is less than 0.5MPa. The pressure difference between the air pressure and water pressure in the control air chamber is always less than 0.5MPa, so that it is gradually balanced with the corresponding external water environment pressure (the process of gradually increasing pressure in the air chamber), ensuring that the entire structure is not damaged by pressure overload during the diving process. Once the predetermined working depth of 300 meters is reached, the second air circuit control channel is activated, activating the second differential pressure control switch to maintain a differential pressure of 0.01 MPa, thus balancing the static pressure within the air chamber with the static pressure at a depth of 300 meters (micro-adjustment). When the sound source reaches the working depth, it is activated via the main control console to begin operation, radiating sound waves in the water medium at the predetermined frequency and sound level.

[0055] The working principle of pneumatic balanced sound compensation is to dynamically adjust the pressure inside the air chamber through gas pressure control, so as to balance it with the external water pressure. In the pressure balance state, in order to ensure that the sound waves can be effectively radiated, it is necessary to ensure no sound backflow. This causes a change in the air pressure inside the air chamber, forming a negative pressure. Through reasonable parameter design, this change can be made less than the pressure difference control value of the lower two channels of the air circuit control system, so that the air pressure inside the air chamber remains in a balanced state. The force caused by the negative pressure is balanced by the motor design, and the increase in force caused by the negative pressure due to sound wave radiation can be covered by the motor's load capacity, thus ensuring that the sound source can work normally.

[0056] Compensation system such as Figure 1 As shown, it mainly consists of high-pressure gas cylinders (1, 2), pressure-resistant gas tanks, sealed gas chambers, flange sealing structure interfaces, gas path control system, and frame base. The compensation system is sealed to the sound radiation system, and the gas path control system is connected to the sound source control console.

[0057] The number of high-pressure gas cylinders needs to be determined based on the number of moles required for compensation. The number of moles of gas stored in each cylinder must be greater than the number required for compensation. In this example, two 10-liter high-pressure gas cylinders (15 MPa pressure) are used. The gas space volume required for compensation can be achieved using pressure-resistant gas tanks and sealed gas chambers. Commercially available standard pressure-resistant gas tanks can be used, selecting a size close to the required gas space volume (in this example, a 300-liter space volume is required, configured with a 200-liter gas tank and a 100-liter gas chamber). The sealed gas chamber is mainly used for compatibility and adjustment of the structure; in this example, it is used to house the electric motor, electric cylinder, and motor drive control components. (Provides a portion of the gas space volume required for compensation); flange sealing interface for structurally adapting and sealing the sealed gas chamber with the sound source radiation system; gas path control system, consisting of a pressure reducing valve and a gas pressure control module, the gas pressure control module is divided into two paths, one consisting of pressure detection and a 50-meter pressure differential control switch, and the other consisting of 300-meter depth detection and a micro-differential pressure control switch, realizing gas release control at a depth of 300 meters; cables, mainly used to provide the power required by the control valve, etc., the gas path control system is connected to the main control console control system through cables; universal mounting frame base, used to install and fix the various components.

[0058] This method is designed for a working depth of 300 meters and uses carbon dioxide gas as the working medium. Other working gases can also be selected depending on the working depth. High-pressure carbon dioxide cylinders provide a 15 MPa high-pressure gas source. Two cylinders are connected to a pressure-resistant gas tank via a gas circuit control subsystem consisting of a pressure reducing valve and a solenoid control valve. The pressure-resistant gas tank is connected to a sealed gas chamber. By controlling the opening and closing of the gas circuit, the gas pressure inside the gas chamber is kept dynamically balanced with the external water pressure. During descent, the solenoid valves are automatically controlled based on the pressure detected inside the gas chamber, causing them to open sequentially. When the gas pressure reaches the water pressure value at the working depth, the valves are closed. This balances the static pressure of the seawater with the pressure inside the gas chamber, while ensuring the required molar number of gases is met.

[0059] Parameter determination process: The size of the compensation space and the required number of gas moles are determined based on the working depth, taking into account a series of technical methods related to the overload capacity of motor-driven sound sources and piezoelectric sound sources. The process involves first determining the displacement and flow rate of the acoustic radiating plate through acoustic calculations based on the sound level and working depth of the sound source. Then, the required compensation space and number of gas moles are calculated based on the mechanical driving capability. Finally, the number of gas cylinders is selected based on the number of moles.

[0060] Therefore, the air chamber in this design primarily serves as the installation space for the motor. If other acoustic sources are used, there is no need to reserve space for motor installation; the air chamber and air tank can be combined in the design. The compensation device can be connected to the compensation chamber of a conventional underwater acoustic source (the compensation chamber is the air bladder of the sound source, and the dynamic balancing compensation device can replace the original air bladder) through a sealed flange interface, thus extending the working depth of the conventional sound source. The air circuit control system mainly coordinates with the release of control gas according to the descent conditions, ensuring that the pressure difference between the inside and outside of the sound source remains within a set control range during the descent process. This guarantees that the entire sound source device will not be damaged due to pressure overload and can emit large-amplitude sound waves.

[0061] An aerodynamically balanced sound compensation system suitable for low-frequency sound sources in deep sea is provided. The sound compensation system is connected to the low-frequency sound source through a standard flange interface and is used in conjunction with the low-frequency sound source.

[0062] Furthermore, the sound compensation system includes a high-pressure gas cylinder I, a high-pressure gas cylinder II, a pressure-resistant gas tank, a sealed air chamber, a standard flange interface, and a gas path control system I and a gas path control system II. The high-pressure gas cylinder I is connected to the gas path control system I, the gas path control system I is connected to the pressure-resistant gas tank, the pressure-resistant gas tank is connected to the sealed air chamber, the sealed air chamber is connected to the standard flange interface, and the standard flange interface is connected to the sound radiation system.

[0063] The gas circuit control system I and gas circuit control system II are connected to the control console via cables;

[0064] All of the above connections are sealed connections.

[0065] Furthermore, the sound radiation system is a motor-driven low-frequency sound source with a compensation port or other low-frequency sound sources with an airbag that can be externally compensated, thus extending its working depth.

[0066] Furthermore, the gas circuit control system I includes differential pressure control switch I 51, differential pressure control switch II 52, differential pressure control switch III 53, multi-point depth control valve 54, and pressure reducing valve 55;

[0067] The high-pressure gas cylinder I 56 is connected to a pressure reducing valve 55. The pressure reducing valve 55 is connected to a differential pressure control switch III 53 and a multi-point depth control valve 54. The multi-point depth control valve 54 is connected to a differential pressure control switch II 52. The differential pressure control switch II 52 is connected to a sealed gas chamber 57.

[0068] The differential pressure control switch Ⅲ53 is connected to the differential pressure control switch Ⅰ51, and the differential pressure control switch Ⅰ51 is connected to the sealed air chamber 57;

[0069] The gas path control system I and the gas path control system II have the same structure.

[0070] like Figure 3 As shown, the gas circuit control system I includes differential pressure control switch I1 with a pressure of 0.01 MPa, differential pressure control switch II2 with a pressure of 0.5 MPa, differential pressure control switch III3 with a pressure of 3 MPa, multi-point depth control valve 4, and pressure reducing valve 5;

[0071] The high-pressure gas cylinder I6 is connected to the pressure reducing valve 5. The pressure reducing valve 5 is connected to the differential pressure control switch III3 (3MPa) and the multi-point depth control valve 4. The multi-point depth control valve 4 is connected to the differential pressure control switch II2 (0.5MPa). The differential pressure control switch II2 (0.5MPa) is connected to the sealed gas chamber 7.

[0072] The differential pressure control switch Ⅲ3 (3MPa) is connected to the differential pressure control switch Ⅰ1 (0.01MPa), and the differential pressure control switch Ⅰ1 (0.01MPa) is connected to the sealed air chamber 7.

[0073] Furthermore, the bottom of the support frame 1 is equipped with an air tank 2 of the air chamber subsystem. Air circuit control subsystems 3 are respectively installed on the upper left and right outer sides of the air tank 2 of the air chamber subsystem. Each air circuit control subsystem 3 is connected to a gas cylinder 4. The air tank 2 of the air chamber subsystem is connected to the structural air chamber 5 of the air chamber subsystem via a sealed pipe 20. A motor 6 is installed at the bottom of the structural air chamber 5 of the air chamber subsystem. The motor 6 is connected to a motor controller 7 and provides kinetic energy to the electric cylinder 8. The output shaft of the electric cylinder 8 is connected to a radiation plate Ⅲ9. The radiation plate Ⅲ9 is connected to an elastic retractable airbag structure Ⅰ10. The elastic retractable airbag structure Ⅰ10 is connected to the structural air chamber 5 of the air chamber subsystem via a flange 11. A pressure sensor 12 is installed inside the structural air chamber 5 of the air chamber subsystem. On the outer side of the support frame 1, at the upper end of the radiation plate Ⅲ9, a boom 13-1 is installed. The boom 13-1 is longer than 1 meter, and a sound pressure sensor 13 is installed at the end of the boom 13-1.

[0074] Furthermore, the air tank 2 of the air chamber subsystem is installed at the bottom of the support frame 1. Air circuit control subsystems 3 are installed on the left and right sides of the upper end of the air tank 2, respectively. Each air circuit control subsystem 3 is connected to a gas cylinder 4. The air tank 2 of the air chamber subsystem is connected to the structural air chamber 5 of the air chamber subsystem via a sealed pipe 20. A motor 6 is installed at the bottom of the structural air chamber 5 of the air chamber subsystem. The motor 6 is connected to a motor controller 7 and provides kinetic energy to the electric cylinder 8. The output shaft of the electric cylinder 8 is connected to a reversing structure 15. The reversing structure 15 is connected to a radiation plate I 16 and a radiation plate II 17. The radiation plate I 16 is connected to a flexible retractable airbag structure I 18. The flexible retractable airbag structure I 18 is connected to the structural air chamber 5 of the air chamber subsystem via a flange 11.

[0075] The radiating plate II17 is connected to the elastic and expandable airbag structure II19, and the elastic and expandable airbag structure II19 is sealed to the structural air chamber 5 of the air chamber subsystem via flange 11.

[0076] An extension arm 13-1 is installed on the outside of the support frame 1, on the right or left side of the radiating plate I16 or radiating plate II17. The extension arm 13-1 is longer than 1 meter, and a sound pressure sensor 13 is installed at the end of the extension arm 13-1.

Claims

1. A design method for an aerodynamically balanced sound compensation system suitable for deep-sea low-frequency sound sources, characterized in that, By utilizing the liquid and gas phase conversion of the selected working gas, the static pressure balance between the gas chamber and seawater is achieved. Furthermore, acoustic compensation is effectively achieved by compensating for the dynamic pressure imbalance caused by sound radiation within a certain volume V space through mechanical margin compensation. The space of a certain volume V is determined based on whether the dynamic pressure difference variable generated in the air chamber space and the external seawater pressure during the sound wave radiation process corresponding to the maximum sound source level when the sound source is in working state is less than the mechanical balance margin constraint condition of the space of a certain volume V. The mechanical balance margin constraint of the space is the structural mechanical bearing margin, including the thrust margin constraint when selecting motor power; the selection of parameters of motor power and space volume V are mutually influential and restrictive, and the volume is confirmed and verified according to the selected motor or the motor is selected and verified according to the volume.

2. The design method of an aerodynamically balanced sound compensation device suitable for deep-sea low-frequency sound sources according to claim 1, characterized in that, The working gas is selected based on the working depth and the phase transition point of the gas.

3. The design method of an aerodynamically balanced sound compensation system suitable for deep-sea low-frequency sound sources according to claim 1, characterized in that, The parameter selection process for choosing and verifying the motor based on its volume includes the following steps: Step 1: Determine the maximum amplitude and drainage volume of the radiating plate based on the sound source level and the diameter of the radiating plate; Step 2: Based on the maximum amplitude and drainage of the radiating plate in Step 1, initially select the space volume V within the usable space provided by the system device. Driven by the motor, the radiating plate reciprocates, causing the pressure in the air chamber to exhibit two states of periodic decrease and increase. Calculate the maximum value of the dynamic pressure difference change brought about by the reciprocating motion of the radiating plate to the gas in the air chamber of volume V when the sound source is working. Step 3: Based on the maximum value of the dynamic pressure difference change in Step 2, obtain the maximum value of the force increment on the radiant plate due to acoustic radiation; Step 4: Based on the requirements of the sound source level and the force increment in Step 3, select the power of the motor so that the thrust of the motor can meet the force required for the maximum sound source level radiation and the maximum value of the force increment caused by the dynamic pressure difference. Step 5: Based on the motor power selected in Step 4, confirm whether the power supply system can guarantee power supply and whether the motor can be installed; if the requirements are met, end the parameter confirmation process; if not, return to Step 2, readjust the V setting, and repeat the subsequent steps until the requirements are met.

4. The design method of an aerodynamically balanced sound compensation system suitable for deep-sea low-frequency sound sources according to claim 1, characterized in that, The method for confirming and verifying the motor's volume is as follows: Select the motor power level based on the sound source level and the power supply capacity of the working environment. The selection of the motor power level should ensure that the thrust provided by the motor covers the thrust required by the sound source level and leave an appropriate margin for withstanding dynamic pressure differences. Then, calculate the volume of space V based on the motor's pressure bearing margin and confirm its feasibility. If the space requirements are met, the parameter confirmation process ends; if not, reselect until the requirements are met.

5. An aerodynamically balanced sound compensation system suitable for deep-sea low-frequency sound sources, characterized in that, The sound compensation system uses the design method of the aerodynamic balance sound compensation system applicable to deep-sea low-frequency sound sources as described in claim 1. The sound compensation system is connected to the low-frequency sound source through a standard flange interface and is used in conjunction with the low-frequency sound source.

6. The aerodynamically balanced sound compensation system for deep-sea low-frequency sound sources according to claim 5, characterized in that, The sound compensation system includes a high-pressure gas cylinder I, a high-pressure gas cylinder II, a pressure-resistant gas tank, a sealed air chamber, a standard flange interface, and a gas path control system I and a gas path control system II. The high-pressure gas cylinder I is connected to the gas path control system I, the gas path control system I is connected to the pressure-resistant gas tank, the pressure-resistant gas tank is connected to the sealed air chamber, the sealed air chamber is connected to the standard flange interface, and the standard flange interface is connected to the sound radiation system. The gas circuit control system I and gas circuit control system II are connected to the control console via cables; All of the above connections are sealed connections.

7. The aerodynamically balanced sound compensation system for deep-sea low-frequency sound sources according to claim 5, characterized in that, The sound radiation system is a motor-driven low-frequency sound source with a compensation port or other low-frequency sound sources with an airbag that can be connected to an external compensation system, thus extending its working depth.

8. The aerodynamically balanced sound compensation system for deep-sea low-frequency sound sources according to claim 5, characterized in that, The pneumatic control system I includes differential pressure control switch I, differential pressure control switch II, differential pressure control switch III, multi-point depth control valve, and pressure reducing valve; The high-pressure gas cylinder I is connected to a pressure reducing valve, which is connected to a differential pressure control switch III and a multi-point depth control valve. The multi-point depth control valve is connected to a differential pressure control switch II, which is connected to a sealed gas chamber. The differential pressure control switch Ⅲ is connected to the differential pressure control switch Ⅰ, and the differential pressure control switch Ⅰ is connected to the sealed air chamber; The gas path control system I and the gas path control system II have the same structure.

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