Space vehicle propellant safety management device accommodating temperature excursions and method of use

Abstract

The application provides a space vehicle propellant safety management device and a use method suitable for temperature alternation in the field of propellant on-orbit safety management devices, and belongs to the technical field of propellant on-orbit safety management devices.The device comprises a metal diaphragm tank, a compensation diaphragm box, a gas path pipeline and a liquid path pipeline, the gas path of the metal diaphragm tank and the gas path of the compensation diaphragm box are communicated through the gas path pipeline, and the liquid path of the metal diaphragm tank and the liquid path of the compensation diaphragm box are communicated through the liquid path pipeline; the metal diaphragm tank carries propellant, and the compensation diaphragm box is used for compensating the volume change of the propellant caused by temperature change.The large-volume metal diaphragm tank and the small-volume compensation diaphragm box are combined, the volume change of the propellant caused by the on-orbit temperature alternation of the metal diaphragm tank is compensated by the compensation diaphragm box, the position of the metal diaphragm is kept unchanged during the on-orbit operation of the vehicle, and the working reliability and safety of the metal diaphragm tank are improved.

Description

Technical Field

[0001] This invention relates to the field of on-orbit propellant safety management devices, and more specifically, to a spacecraft propellant safety management device and its usage method that adapts to temperature changes. Background Technology

[0002] During the operation of spacecraft, especially near-Earth orbit spacecraft, the propellant tanks experience alternating high and low temperature environments due to repeated and periodic changes in the angle of solar incidence and lighting conditions, resulting in certain changes in propellant volume.

[0003] Metal diaphragm tanks offer advantages such as high discharge efficiency, strong overload adaptability, and low sloshing. However, the metal diaphragm in these tanks lacks fatigue resistance due to repeated motion and cannot adapt to propellant volume changes caused by temperature fluctuations. If traditional temperature control methods are used, very strict control of the propellant temperature range is required to ensure the safe operation of the on-orbit metal diaphragm tank in alternating temperature environments.

[0004] Metal diaphragm tanks offer high reliability due to repeated fatigue testing and are commonly used in refillable systems. However, they are only suitable for cylindrical structures, resulting in heavier weight, longer dimensions, and relatively lower discharge efficiency. Adopting a metal diaphragm tank system entirely would require sacrificing some space and weight resources.

[0005] Developing a spacecraft propellant safety management device that can adapt to temperature changes while also taking into account system space and weight resources has become an urgent need in the current development of space propulsion systems.

[0006] Currently, no descriptions or reports of technologies similar to this invention have been found in China, nor have any similar publicly available information been collected domestically or internationally. Summary of the Invention

[0007] To address the shortcomings of existing technologies, the purpose of this invention is to provide a spacecraft propellant safety management device and its usage method that adapts to temperature fluctuations.

[0008] According to the present invention, a spacecraft propellant safety management device adapted to temperature alternation includes a metal diaphragm tank, a compensation diaphragm box, a gas pipeline, and a liquid pipeline. The gas pipeline of the metal diaphragm tank and the gas pipeline of the compensation diaphragm box are connected through the gas pipeline, and the liquid pipeline is connected to the liquid pipeline of the metal diaphragm tank and the liquid pipeline of the compensation diaphragm box.

[0009] The metal diaphragm tank holds the propellant, while the compensation diaphragm box is used to compensate for the volume change of the propellant due to temperature variations.

[0010] Preferably, the metal diaphragm tank includes a gas interface, a tank gas chamber, a metal diaphragm, a tank liquid chamber, and a liquid interface. The gas interface is located on the tank gas chamber, the tank gas chamber is separated from the tank liquid chamber by the metal diaphragm, and the tank liquid chamber is provided with a liquid interface.

[0011] The gas interface connects to the gas pipeline. The gas chamber of the tank is used to carry the pressurized gas, and the liquid chamber of the tank is used to carry the propellant. The pressurized gas and the propellant are separated by a metal diaphragm. The liquid interface connects to the liquid pipeline.

[0012] Preferably, the compensation diaphragm includes a gas passage end cap, a diaphragm air chamber, a diaphragm assembly, a diaphragm liquid chamber, and a liquid passage end cap. The diaphragm air chamber is provided with a gas passage end cap, and the diaphragm air chamber is separated from the diaphragm liquid chamber by the diaphragm assembly. The diaphragm liquid chamber is provided with a liquid passage end cap.

[0013] The gas passage end cap is connected to the gas passage pipeline. The diaphragm gas chamber is used to carry the pressurized gas, the diaphragm liquid chamber is used to carry the propellant, the diaphragm assembly is used to separate the pressurized gas and the propellant, and the diaphragm assembly adopts a stretchable design. The diaphragm assembly dynamically adjusts the volume ratio of the diaphragm gas chamber and the diaphragm liquid chamber. The liquid passage end cap is connected to the liquid passage pipeline.

[0014] Preferably, the gas pipeline connects the gas pipeline interface to the gas pipeline end cap, thereby realizing the connection between the storage tank gas chamber and the diaphragm gas chamber;

[0015] The liquid pipeline connects the liquid interface to the liquid end cap, thereby enabling communication between the storage tank liquid chamber and the membrane box liquid chamber.

[0016] Preferably, when the temperature of the spacecraft rises, the propellant in the tank liquid chamber enters the diaphragm liquid chamber through the liquid pipeline and drives the diaphragm assembly to move, which increases the volume of the diaphragm liquid chamber and decreases the volume of the diaphragm gas chamber. After the diaphragm gas chamber is compressed, the excess gas enters the tank gas chamber through the gas end cap, gas pipeline and gas interface and makes the system reach pressure balance.

[0017] When the temperature of the spacecraft drops, the propellant flows back from the diaphragm fluid chamber through the fluid pipeline into the storage tank fluid chamber.

[0018] Preferably, the compensation diaphragm box utilizes the reciprocating motion of the diaphragm box assembly to achieve dynamic changes in the volume of the diaphragm box liquid cavity, compensating for the volume changes of propellant in the metal diaphragm tank, thereby avoiding fatigue failure that may occur due to the reciprocating movement of the metal diaphragm in the metal diaphragm tank, and achieving safe propellant management of the spacecraft under periodic temperature changes.

[0019] Preferably, the starting pressure difference of the metal diaphragm tank is the tank air chamber pressure minus the tank liquid chamber pressure, and the reverse pressure difference of the metal diaphragm tank is the tank liquid chamber pressure minus the tank air chamber pressure.

[0020] The starting pressure differential of the metal diaphragm tank is greater than 0.07 MPa, and the reverse pressure differential when the metal diaphragm flips is greater than 0.2 MPa. The metal diaphragm moves downward and pushes the propellant in the tank's liquid chamber downstream.

[0021] When the starting pressure difference of the metal diaphragm tank is less than or equal to 0.07 MPa and the reverse pressure difference of the metal diaphragm is less than or equal to 0.2 MPa, the metal diaphragm will not move.

[0022] Preferably, the starting pressure difference of the compensation diaphragm box is not greater than 0.02 MPa, and the starting pressure difference of the compensation diaphragm box is less than that of the metal diaphragm by 0.07 MPa;

[0023] The starting pressure difference of the compensating diaphragm is the pressure in the air chamber of the diaphragm minus the pressure in the liquid chamber of the diaphragm.

[0024] The present invention also provides a method for using a spacecraft propellant safety management device adapted to temperature changes, the specific operating steps of which are as follows:

[0025] S1. First, evacuate the gas path, then evacuate the liquid path.

[0026] S2. Fill the diaphragm according to the principle of "the diaphragm can withstand a negative pressure difference of up to 0.3 MPa" and maintain the "negative pressure difference of up to 0.3 MPa" during the ground preparation stage;

[0027] S3. At the same time, the metal diaphragm is in the initial position, and the diaphragm assembly of the compensation diaphragm box is in the maximum stroke tension state.

[0028] S4. Before launch, pressurize and fill the metal diaphragm tank.

[0029] Preferably, in step S4, since the pressure difference of the compensation diaphragm box is small when it starts, the compensation diaphragm box moves first after pressurization. The metal diaphragm only starts working when the positive pressure difference of the compensation diaphragm box after being pressurized is greater than or equal to the pressure difference of the metal diaphragm. After pressurization is completed, the pressure of the gas and liquid chambers reaches equilibrium. At this time, the metal diaphragm remains in the corresponding position, while the diaphragm box assembly is in the compressed position.

[0030] Compared with the prior art, the present invention has the following beneficial effects:

[0031] This invention combines a large-volume metal diaphragm tank with a small-volume compensation diaphragm box. The propellant volume change caused by the alternating temperature in the orbit of the metal diaphragm tank is compensated by the compensation diaphragm box, ensuring that the position of the metal diaphragm remains stationary during the spacecraft's orbital operation, thereby improving the operational reliability and safety of the metal diaphragm tank. Attached Figure Description

[0032] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0033] Figure 1 This is a schematic diagram of the propellant safety management device in this invention;

[0034] Figures 2-6 These are all schematic diagrams illustrating the method of using the propellant safety management device in this invention.

[0035] The diagram is labeled as follows: 1. Metal diaphragm tank; 11. Gas interface; 12. Tank gas chamber; 13. Metal diaphragm; 14. Tank liquid chamber; 15. Liquid interface; 2. Compensating diaphragm box; 21. Gas end cap; 22. Diaphragm box gas chamber; 23. Diaphragm box assembly; 24. Diaphragm box liquid chamber; 25. Liquid end cap; 3. Gas pipeline; 4. Liquid pipeline. Detailed Implementation

[0036] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0037] Example 1

[0038] This invention provides a spacecraft propellant safety management device adapted to temperature alternation, such as... Figure 1 As shown, the system includes a metal diaphragm tank 1, a compensation diaphragm box 2, a gas pipeline 3, and a liquid pipeline 4. The gas pipelines of the metal diaphragm tank 1 and the compensation diaphragm box 2 are connected by the gas pipeline 3, and the liquid pipeline 4 connects the liquid pipelines of the metal diaphragm tank 1 and the compensation diaphragm box 2. The metal diaphragm tank 1 carries the propellant, and the compensation diaphragm box 2 is used to compensate for the volume change of the propellant due to temperature variations. The metal diaphragm tank 1 has a larger volume, determined by the mission requirements of the spacecraft; the compensation diaphragm box 2 has a smaller volume, determined by the analysis of the on-orbit temperature fluctuations of the spacecraft.

[0039] The metal diaphragm tank 1 includes a gas interface 11, a tank gas chamber 12, a metal diaphragm 13, a tank liquid chamber 14, and a liquid interface 15. The gas interface 11 is located on the tank gas chamber 12, which is separated from the tank liquid chamber 14 by the metal diaphragm 13. The tank liquid chamber 14 is provided with the liquid interface 15. The gas interface 11 is connected to the gas pipeline 3. The tank gas chamber 12 is used to carry pressurized gas, and the tank liquid chamber 14 is used to carry propellant. The pressurized gas and propellant are separated by the metal diaphragm 13. The liquid interface 15 is connected to the liquid pipeline 4. When the starting pressure difference of the metal diaphragm tank 1 (pressure of tank gas chamber 12 - pressure of tank liquid chamber 14) > 0.07 MPa, the reverse pressure difference (pressure of tank liquid chamber 14 - pressure of tank gas chamber 12) that causes the metal diaphragm 13 to flip is greater than 0.2 MPa. The metal diaphragm 13 moves downward and pushes the propellant in the tank liquid chamber 14 downstream. When the pressure of tank gas chamber 12 - pressure of tank liquid chamber 14 is ≤ 0.07 MPa and the pressure of tank liquid chamber 14 - pressure of tank gas chamber 12 is ≤ 0.2 MPa, the metal diaphragm 13 does not move.

[0040] The compensation diaphragm 2 includes a gas path end cap 21, a diaphragm chamber 22, a diaphragm assembly 23, a diaphragm liquid chamber 24, and a liquid path end cap 25. The starting pressure difference of the compensation diaphragm 2 (pressure in the diaphragm chamber 22 - pressure in the diaphragm liquid chamber 24) is no greater than 0.02 MPa, and the starting pressure difference of the compensation diaphragm 2 is less than that of the metal diaphragm 13 (0.07 MPa). The diaphragm chamber 22 is equipped with a gas path end cap 21. The diaphragm chamber 22 is separated from the diaphragm liquid chamber 24 by the diaphragm assembly 23. The diaphragm assembly 23 has high reliability and can achieve thousands of small stretches and dozens of full stretches, thereby compensating for the propellant volume changes caused by the periodic and periodic temperature changes of the spacecraft. The diaphragm liquid chamber 24 is equipped with a liquid path end cap 25. The gas path end cap 21 is connected to the gas path pipeline 3, and the gas path pipeline 3 connects the gas path interface 11 to the gas path end cap 21, thereby realizing the connection between the storage tank gas chamber 12 and the diaphragm chamber 22. The diaphragm gas chamber 22 is used to carry pressurized gas, the diaphragm liquid chamber 24 is used to carry propellant, and the diaphragm assembly 23 is used to separate the pressurized gas and propellant. The diaphragm assembly 23 adopts a stretchable design and dynamically adjusts the volume ratio of the diaphragm gas chamber 22 and the diaphragm liquid chamber 24. The liquid passage head 25 is connected to the liquid passage pipeline 4, and the liquid passage pipeline 4 connects the liquid passage interface 15 to the liquid passage head 25, thereby realizing the connection between the tank liquid chamber 14 and the diaphragm liquid chamber 24.

[0041] When the spacecraft's on-orbit temperature changes, the system can dynamically adjust to an equilibrium state: When the spacecraft's temperature rises, the propellant in the reservoir liquid chamber 14 enters the diaphragm liquid chamber 24 through the liquid passage 4 and drives the diaphragm assembly 23 to move, increasing the volume of the diaphragm liquid chamber 24 and decreasing the volume of the diaphragm gas chamber 22. The excess gas after compression in the diaphragm gas chamber 22 enters the reservoir gas chamber 12 through the gas passage end cap 21, gas passage 3, and gas passage interface 11, bringing the system to pressure balance; when the spacecraft's temperature drops, the propellant flows back from the diaphragm liquid chamber 24 into the reservoir liquid chamber 14 through the liquid passage 4. The compensating diaphragm 2 uses the reciprocating motion of the diaphragm assembly 23 to achieve dynamic changes in the volume of the diaphragm liquid chamber 24, compensating for the volume changes of the propellant in the metal diaphragm reservoir 1, thereby avoiding fatigue failure that may occur due to the reciprocating displacement of the metal diaphragm 13 in the metal diaphragm reservoir 1, and achieving safe propellant management of the spacecraft under periodic temperature changes.

[0042] Example 2

[0043] The present invention also provides a method for using the spacecraft propellant safety management device adapted to temperature alternation in Embodiment 1, such as... Figure 2-6 As shown, the specific operation steps are as follows:

[0044] S1, such as Figure 2 As shown, the gas path is first evacuated. At this time, the metal diaphragm 13 is in the initial state (the gas chamber 12 of the storage tank is at its minimum and the liquid chamber 14 of the storage tank is at its maximum), and the diaphragm assembly 23 of the compensation diaphragm box 2 is in the maximum stretching state (the gas chamber 22 of the diaphragm box is at its minimum and the liquid chamber 24 of the diaphragm box is at its maximum).

[0045] S2, such as Figure 3 As shown, the liquid path is then evacuated. At this time, the metal diaphragm 13 is still in the initial state (the gas chamber 12 of the storage tank is at its smallest and the liquid chamber 14 of the storage tank is at its largest), and the diaphragm assembly 23 of the compensation diaphragm box 2 is in a naturally extended state.

[0046] S3, such as Figure 4 As shown, the filling is carried out according to the principle of "the compensation diaphragm 2 can withstand a negative pressure difference of up to 0.3 MPa (liquid chamber > gas chamber)" and the "compensation diaphragm 2 can withstand a negative pressure difference of up to 0.3 MPa" is maintained during the ground preparation stage; during this period, the metal diaphragm 13 is in the initial position and the diaphragm assembly 23 of the compensation diaphragm 2 is in the maximum stroke tension state.

[0047] S4, such as Figure 5As shown, the metal diaphragm tank 1 is pressurized and filled before launch. Since the pressure difference of the compensation diaphragm box 2 is small when it starts, the compensation diaphragm box 2 moves first after pressurization. The metal diaphragm box 13 only starts to work when the positive pressure difference of the compensation diaphragm box 2 after being pressurized is greater than or equal to the pressure difference of the metal diaphragm 13. After pressurization is completed, the pressure of the gas and liquid chambers reaches equilibrium. At this time, the metal diaphragm 13 is held in the corresponding position, while the diaphragm box assembly 23 is in the compressed position.

[0048] During the time a spacecraft is docked in orbit, according to Figure 6 As shown, when the spacecraft temperature rises, the propellant in the reservoir liquid chamber 14 enters the diaphragm liquid chamber 24 through the liquid passage 4, driving the diaphragm assembly 23 to move. This increases the volume of the diaphragm liquid chamber 24 and decreases the volume of the diaphragm gas chamber 22. Excess gas in the compressed diaphragm gas chamber 22 enters the reservoir gas chamber 12 through the gas passage end cap 21, gas passage 3, and gas passage interface 11, bringing the system to pressure balance. When the spacecraft temperature drops, the propellant flows back from the diaphragm liquid chamber 24 into the reservoir liquid chamber 14 through the liquid passage 4.

[0049] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0050] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A spacecraft propellant safety management device adapted to temperature alternation, characterized in that, It includes a metal diaphragm storage tank (1), a compensation diaphragm box (2), a gas pipeline (3), and a liquid pipeline (4). The gas pipeline of the metal diaphragm storage tank (1) and the gas pipeline of the compensation diaphragm box (2) are connected through the gas pipeline (3). The liquid pipeline (4) is connected to the liquid pipeline of the metal diaphragm storage tank (1) and the liquid pipeline of the compensation diaphragm box (2). The metal diaphragm tank (1) carries the propellant, and the compensation diaphragm box (2) is used to compensate for the volume change of the propellant due to temperature changes; The starting pressure difference of the metal diaphragm tank (1) is the pressure of the tank air chamber (12) minus the pressure of the tank liquid chamber (14), and the reverse pressure difference of the metal diaphragm tank (1) is the pressure of the tank liquid chamber (14) minus the pressure of the tank air chamber (12). The starting pressure difference of the metal diaphragm tank (1) is greater than 0.07 MPa, the reverse pressure difference when the metal diaphragm (13) flips is greater than 0.2 MPa, and the metal diaphragm (13) moves downward and pushes the propellant in the tank liquid chamber (14) to flow downstream. When the starting pressure difference of the metal diaphragm tank (1) is less than or equal to 0.07 MPa and the reverse pressure difference of the metal diaphragm (13) is less than or equal to 0.2 MPa, the metal diaphragm (13) will not move. The starting pressure difference of the compensation diaphragm (2) is not greater than 0.02 MPa, and the starting pressure difference of the compensation diaphragm (2) is less than that of the metal diaphragm (13) by 0.07 MPa; The starting pressure difference of the compensation diaphragm (2) is the pressure of the air chamber (22) of the diaphragm and the pressure of the liquid chamber (24) of the diaphragm.

2. The spacecraft propellant safety management device adapted to temperature alternation according to claim 1, characterized in that, The metal diaphragm tank (1) includes a gas interface (11), a tank gas chamber (12), a metal diaphragm (13), a tank liquid chamber (14), and a liquid interface (15). The gas interface (11) is located on the tank gas chamber (12). The tank gas chamber (12) is separated from the tank liquid chamber (14) by the metal diaphragm (13). The tank liquid chamber (14) is provided with a liquid interface (15). The gas interface (11) is connected to the gas pipeline (3), the gas chamber (12) of the storage tank is used to carry pressurized gas, the liquid chamber (14) of the storage tank is used to carry propellant, and the pressurized gas and propellant are separated by the metal diaphragm (13), and the liquid interface (15) is connected to the liquid pipeline (4).

3. The spacecraft propellant safety management device adapted to temperature alternation according to claim 2, characterized in that, The compensation diaphragm (2) includes a gas path end cap (21), a diaphragm gas chamber (22), a diaphragm assembly (23), a diaphragm liquid chamber (24), and a liquid path end cap (25). The gas path end cap (21) is provided on the diaphragm gas chamber (22). The diaphragm gas chamber (22) is separated from the diaphragm liquid chamber (24) by the diaphragm assembly (23). The liquid path end cap (25) is provided on the diaphragm liquid chamber (24). The gas passage end cap (21) is connected to the gas passage pipeline (3). The diaphragm gas chamber (22) is used to carry pressurized gas. The diaphragm liquid chamber (24) is used to carry propellant. The diaphragm assembly (23) is used to separate pressurized gas and propellant. The diaphragm assembly (23) adopts a stretchable design. The diaphragm assembly (23) dynamically adjusts the volume ratio of the diaphragm gas chamber (22) and the diaphragm liquid chamber (24). The liquid passage end cap (25) is connected to the liquid passage pipeline (4).

4. The spacecraft propellant safety management device adapted to temperature alternation according to claim 3, characterized in that, The gas pipeline (3) connects the gas interface (11) to the gas end cap (21), thereby realizing the connection between the storage tank gas chamber (12) and the membrane box gas chamber (22); The liquid pipeline (4) connects the liquid interface (15) to the liquid end cap (25), thereby realizing the connection between the storage tank liquid chamber (14) and the membrane box liquid chamber (24).

5. The spacecraft propellant safety management device adapted to temperature alternation according to claim 3, characterized in that, When the temperature of the spacecraft rises, the propellant in the tank liquid chamber (14) enters the diaphragm liquid chamber (24) through the liquid pipeline (4) and drives the diaphragm assembly (23) to move, thereby increasing the volume of the diaphragm liquid chamber (24) and decreasing the volume of the diaphragm gas chamber (22). The excess gas in the diaphragm gas chamber (22) after compression enters the tank gas chamber (12) through the gas end cap (21), the gas pipeline (3), and the gas interface (11) and makes the system reach pressure balance. When the temperature of the spacecraft drops, the propellant flows back from the membrane liquid chamber (24) through the liquid pipeline (4) into the storage tank liquid chamber (14).

6. The spacecraft propellant safety management device adapted to temperature alternation according to claim 5, characterized in that, The compensation diaphragm (2) utilizes the reciprocating motion of the diaphragm assembly (23) to achieve dynamic changes in the volume of the diaphragm liquid chamber (24), compensating for the volume changes of the propellant in the metal diaphragm tank (1), thereby avoiding fatigue failure that may occur due to the reciprocating displacement of the metal diaphragm (13) in the metal diaphragm tank (1), and realizing safe propellant management of the spacecraft under periodic temperature changes.

7. A method of using the spacecraft propellant safety management device adapted to temperature alternation as described in any one of claims 1-6, characterized in that, The specific operating steps are as follows: S1. First, evacuate the gas path, then evacuate the liquid path. S2. Fill the gas according to the principle that "the compensation diaphragm (2) can withstand a negative pressure difference of up to 0.3 MPa" and maintain "the compensation diaphragm (2) can withstand a negative pressure difference of up to 0.3 MPa" during the ground preparation stage; S3. At the same time, the metal diaphragm (13) is in the initial position, and the diaphragm assembly (23) of the compensation diaphragm box (2) is in the maximum stroke stretching state. S4. Before launch, pressurize and fill the metal diaphragm tank (1).

8. The method of using the spacecraft propellant safety management device adapted to temperature alternation according to claim 7, characterized in that, In step S4, since the pressure difference of the compensation diaphragm (2) is small when it starts, the compensation diaphragm (2) moves first after pressurization. The metal diaphragm (13) only starts working when the positive pressure difference of the compensation diaphragm (2) after being pressurized is greater than or equal to the pressure difference of the metal diaphragm (13). After pressurization is completed, the pressure of the gas and liquid chambers reaches equilibrium. At this time, the metal diaphragm (13) remains in the corresponding position, while the diaphragm assembly (23) is in the compressed position.

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