Integrated absolute pressure control mechanism capable of automatically switching double pressure systems

Abstract

The invention relates to the technical field of aviation aircraft cabin pressure regulators, in particular to an integrated absolute pressure control mechanism capable of automatically switching double pressure systems. Comprising a lower shell, a diaphragm assembly, a clamping ring A, a gasket A, a clamping ring B, a gasket B, an electromagnet, a socket, a rubber gasket A, an upper shell, a rubber gasket B, an adjusting stud, a corrugated pipe assembly, an upper cover, a sliding sleeve, a spring A, a spring B, a valve rod, a spring C, a suction piece, a valve seat and a sealing piece. The diaphragm assembly comprises a metal sheet, a diaphragm and a sleeve; when an electromagnet in the integrated absolute pressure control mechanism is not attracted, two springs and a diaphragm assembly control the opening and closing position of a valve at the same time, a cabin pressure system is determined, and the function of the integrated absolute pressure control mechanism is equivalent to that of a set of absolute pressure control mechanism in a traditional split type absolute pressure control mechanism.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft cabin pressure regulators, in particular to an integrated absolute pressure control mechanism capable of automatically switching dual pressure systems. Background Art

[0002] The cabin pressure regulation subsystem belongs to the aircraft environmental control system, and is mainly composed of a cabin pressure controller, a cabin exhaust valve, and a cabin safety valve. The cabin pressure controller and the cabin exhaust valve are used together, and the cabin exhaust valve control chamber is connected to the cabin. The pressure change trend is consistent, with only a slight difference in the value. The cabin pressure controller adjusts the control chamber pressure of the cabin exhaust valve, and the cabin exhaust valve lifts the valve according to the control chamber pressure signal adjusted by the cabin pressure controller, thereby controlling the cabin pressure and keeping the cabin pressure within the required range to meet the expected cabin pressure system. In the aircraft cabin pressure system, it is generally divided into three stages: free ventilation stage, absolute pressure control stage, and residual pressure control stage.

[0003] For the cabin pressure controller, the structure of the prior art is as follows Figure 1 As shown, it consists of a shell assembly, a valve seat, a diaphragm assembly, an upper cover, a valve assembly, a bellows assembly, an upper cover, a spring, a cap, a switch, a handle, a lower cover, a nut, and a screw. In order to meet the needs of using a dual pressure system for takeoff and landing at airports at different altitudes, this type of cabin pressure controller is equipped with two independent absolute pressure control mechanisms I and II. Before takeoff, the staff needs to manually switch the three-way switch assembly II to determine which absolute pressure control mechanism to use for this flight and which pressure system to adopt. The change cannot be made in the middle, resulting in the takeoff airport altitude limiting the landing airport altitude flight, especially when taking off from a plain airport and landing at a plateau airport. Since the cabin pressure is much greater than the atmospheric pressure during landing, if the pressure is not discharged in a standardized manner, it is easy to cause ear pressure problems for personnel, and serious problems will also affect the aircraft structure.

[0004] The existing technology has the following problems: 1. In order to meet the demand of using a dual pressure system, two independent absolute pressure control mechanisms are set up, which have a complex structure; 2. Before each takeoff, the staff needs to manually switch the three-way switch assembly according to the use requirements to decide which absolute pressure control mechanism to use for this flight and which pressure system to adopt. The operation process is cumbersome and prone to errors; 3. After the aircraft takes off, the aircraft pressure system is determined and cannot be changed. The take-off airport altitude limits the landing airport altitude, and the flight is restricted. Summary of the invention

[0005] Purpose of the Invention

[0006] An integrated absolute pressure control mechanism with dual pressure systems that can be automatically switched is proposed. The focus is on solving the problems of the current cabin pressure controller, which has a complex mechanism, requires manual pressure system conversion, and cannot switch pressure systems during flight.

[0007] Technical Solution

[0008] An integrated absolute pressure control mechanism with dual pressure systems that can be automatically switched includes a lower shell, a diaphragm assembly, a clamp ring A, a gasket A, a clamp ring B, a gasket B, an electromagnet, a socket, a rubber gasket A, an upper shell, a rubber gasket B, an adjustment stud, a bellows assembly, an upper cover, a sliding sleeve, a spring A, a spring B, a valve rod, a spring C, a suction piece, a valve seat, and a sealing piece. The diaphragm assembly includes a metal sheet, a diaphragm, and a sleeve;

[0009] The outer wall of the sleeve in the diaphragm assembly is connected to the groove of the bellows assembly by threads, one end of the spring B is fixed on the inner step of the metal sheet in the diaphragm assembly, and the other end is fixed on the step on the bellows assembly; the gasket B, the suction sheet, and the spring A are fixedly stacked and installed in sequence at the outer step of the metal sheet in the diaphragm assembly, one end of the spring A falls on the suction sheet, and the suction sheet can drive the spring A to move when power is turned on; the guide rod of the bellows assembly passes through the guide hole of the sliding sleeve and the internal threaded hole of the adjusting stud in sequence, the other end of the spring A is fixed on the step of the sliding sleeve, and the lower end of the adjusting stud is in contact with the groove plane of the sliding sleeve, The upper end is tightened by a nut; the electromagnet is installed on the step on the upper shell, the electromagnet is connected to the socket by a wire, the socket is connected to the upper shell by a screw, and a rubber gasket A is installed in the middle; the clamping ring A is installed in the groove of the upper shell; the clamping ring B and the gasket A are stacked and installed between the electromagnet and the clamping ring A in sequence; the adjusting stud is connected to the upper shell by a thread and tightened by a nut; the valve seat is connected to the lower shell by a thread, and a sealing sheet is installed between the two; the valve rod and the spring C are installed in sequence between the inner groove of the sleeve and the valve seat in the diaphragm assembly; the lower shell and the diaphragm assembly 、 The upper shell is connected by screws; the upper shell and the upper cover are connected by screws, and a rubber gasket B is installed between the two.

[0010] Furthermore, the diaphragm material is specifically a composite of silicone rubber compound GX2-50 and brocade twill silk 511;

[0011] Furthermore, the spring C is used for resetting, and the elastic force of the spring C has a preload and a stiffness that are as small as possible while satisfying the resetting condition.

[0012] Furthermore, the common preload force of the spring A and the spring B cooperates with the bellows assembly to meet the pressure regulation requirements.

[0013] Furthermore, the preload force of the spring B cooperates with the bellows assembly to meet the pressure regulation requirements.

[0014] Furthermore, the number of gaskets B should ensure that the suction piece can be normally attracted when the electromagnet is energized.

[0015] Furthermore, the number of sealing sheets should meet the pressure regulation requirements.

[0016] Furthermore, the material of the bellows in the bellows assembly should be beryllium bronze QBe2, which has high strength, high hardness and good processing performance.

[0017] The beneficial effects of this application are:

[0018] The present invention provides an integrated absolute pressure control mechanism with dual pressure systems that can be automatically switched. When the electromagnet in the integrated absolute pressure control mechanism is not attracted, two springs and a diaphragm assembly simultaneously control the valve switch position to determine a cabin pressure system, and its function is equivalent to a set of absolute pressure control mechanisms in a traditional split absolute pressure control mechanism.

[0019] When the electromagnet in the integrated absolute pressure control mechanism is attracted, one of the springs is shielded, so that the other spring and the diaphragm assembly simultaneously control the valve switch position, which determines a cabin pressure system, and its function is equivalent to a set of absolute pressure control mechanisms in the traditional split absolute pressure control mechanism;

[0020] Whether the electromagnet in the integrated absolute pressure control mechanism is energized determines which cabin pressure system is used. Compared with the traditional split absolute pressure control mechanism, the two sets of absolute pressure control mechanisms are characterized by manually turning the switch to determine which set is effective. It has the characteristics of simple structure, automatic switching of pressure systems, and unrestricted switching timing, avoiding damage to the aircraft due to the selection of a pressure system that does not meet the airport altitude. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural diagram of the prior art;

[0022] Figure 2 It is a schematic diagram of an integrated absolute pressure control mechanism with automatic switching of dual pressure systems according to an embodiment of the present invention.

[0023] The invention comprises a lower shell (1), a diaphragm assembly (2), a clamping ring A (3), a gasket A (4), a clamping ring B (5), a gasket B (6), an electromagnet (7), a socket (8), a rubber gasket A (9), an upper shell (10), a rubber gasket B (11), an adjusting stud (12), a bellows assembly (13), an upper cover (14), a sliding sleeve (15), a spring A (16), a spring B (17), a valve rod (18), a spring C (19), a suction plate (20), a valve seat (21), and a sealing plate (22). DETAILED DESCRIPTION

[0024] In order to make the purpose, technical scheme and advantages of the implementation of the present invention clearer, the technical scheme in the embodiment of the present invention will be described in more detail in combination with the embodiment of the present invention. In the example, the same or similar reference numerals throughout represent the same or similar originals or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, not all of them. The embodiments described below by reference are exemplary and intended to be used to explain the present invention, and should not be construed as limitations on the present invention. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present invention. The following is a detailed description in combination with the embodiments of the present invention.

[0025] Invention point 1: An integrated absolute pressure control mechanism with dual pressure systems that can be automatically switched, characterized in that it comprises a lower shell (1), a diaphragm assembly (2), a collar A (3), a gasket A (4), a collar B (5), a gasket B (6), an electromagnet (7), a socket (8), a rubber gasket A (9), an upper shell (10), a rubber gasket B (11), an adjusting stud (12), a bellows assembly (13), an upper cover (14), a sliding sleeve (15), a spring A (16), a spring B (17), a valve rod (18), a spring C (19), a suction piece (20), a valve seat (21), and a sealing piece (22). The lower shell (1), the diaphragm assembly (2), and the upper shell (10) are connected together by screws; the socket (8) and the upper shell (10) are connected together by screws; the upper shell (10) and the upper cover (14) are connected together by threads; and the electromagnet (7) and the socket (8) are connected together by wires.

[0026] Invention point 2: The absolute pressure control mechanism according to claim 1 is characterized in that a groove is processed on the upper shell (10) to have an interference fit with the clamping ring A (3), and a step is processed on the upper shell (10) to have a clearance fit with the electromagnet (7);

[0027] Invention point 3: The absolute pressure control mechanism according to claim 1 is characterized in that a gasket A (4) is installed between the clamp ring A (3) and the clamp ring B (5), the clamp ring B (5) is in contact with the electromagnet (7), and the electromagnet (7) can be fixed by adjusting the number of gaskets A (4);

[0028] Invention point 4: The absolute pressure control mechanism according to claim 1 is characterized in that the electromagnet (7) and the socket (8) are connected by a wire for transmitting the electromagnet power-on and power-off signal, and a gasket B (6) is installed between the diaphragm assembly (2) and the suction plate (20), and the distance between the suction plate (20) and the electromagnet (7) can be adjusted by adjusting the number of gaskets B (6) to ensure the suction effect of the two when power is turned on;

[0029] Invention point 5: The absolute pressure control mechanism according to claim 1 is characterized in that the upper housing (10) is threadedly matched with the adjusting stud (12), and the adjusting stud (12) is threadedly matched with the bellows assembly (13), and the adjusting stud (12) and the bellows assembly (13) can be rotated to make the two move axially up and down;

[0030] Invention point 6: The absolute pressure control mechanism according to claim 1 is characterized in that a hole is machined on the sleeve (15) to be clearance-matched with the bellows assembly (13), and a concave platform is machined on the sleeve (15) to be contact-matched with the adjustment stud (12), so that the adjustment sleeve (15) can be adjusted by rotating the adjustment stud (12) to move axially up and down;

[0031] Invention point 7: The absolute pressure control mechanism according to claim 1 is characterized in that a boss is provided on the diaphragm assembly (2), which is clearance-matched with the spring A (16) and the spring B (17); a boss is provided on the bellows assembly (13) and the sliding sleeve (15), which is clearance-matched with the spring A (16) and the spring B (17), so as to ensure that the expansion and contraction movement of the spring A (16) and the spring B (17) is along the axial direction;

[0032] Invention point 8: The absolute pressure control mechanism according to claim 1 is characterized in that the diaphragm assembly (2) and the bellows assembly (13) are connected by threads to ensure that the movement trends of the two are consistent;

[0033] Invention point 9: The absolute pressure control mechanism according to claim 1 is characterized in that the diaphragm assembly (2) and the spring A (16) are in contact and fit, and a suction piece (20) is installed between the diaphragm assembly (2) and the spring B (17), and the three are in contact and fit;

[0034] Invention point 10: The absolute pressure control mechanism according to claims 1, 4 and 10 is characterized in that before the suction piece (20) and the electromagnet (7) are attracted, the diaphragm assembly (2) is controlled by the force of the bellows assembly (13), the spring A (16) and the spring B (17); after the suction piece (20) and the electromagnet (7) are attracted, the diaphragm assembly (2) is controlled by the force of the bellows assembly (13) and the spring B (17);

[0035] Invention point 11: The absolute pressure control mechanism according to claims 1, 8 and 9 is characterized in that a spring C (19) is installed between the valve rod (18) and the valve seat (21) to ensure that the valve rod (18) and the diaphragm assembly (2) are in contact and cooperate with each other and have consistent movement trends. The position of the diaphragm assembly (2) determines the position of the valve rod (18), determines the distance between the valve rod (18) and the valve seat (21), and determines the exhaust volume passing therethrough.

[0036] Figure 2 It is a schematic diagram of an integrated absolute pressure control mechanism with automatic switching of dual pressure systems according to an embodiment of the present invention.

[0037] Working principle:

[0038] The lower shell (1), the diaphragm assembly (2), and the upper shell (10) are connected together by screws; the upper shell (10) and the upper cover (14) are connected together by threads; the interior of the mechanism is a closed cavity, the lower shell (1) is processed with an air intake pipeline for receiving the pressure of the cabin exhaust valve control cavity, and the lower shell (1) is processed with an exhaust pipeline for discharging the cabin exhaust valve control cavity pressure after adjustment according to the flight altitude and the selected flight pressure system, so as to achieve the purpose of controlling the control cavity pressure, and then control the valve opening amount of the cabin exhaust valve, so as to achieve the effect of regulating the aircraft cabin pressure.

[0039] In the absolute pressure control mechanism, the diaphragm assembly (2) is controlled by the bellows assembly (13), spring A (16) and spring B (17). After the aircraft takes off, in the free ventilation stage, the sum of the preload forces of spring A (16) and spring B (17) is insufficient to expand the bellows assembly (13), and the distance between the valve rod (18) and the valve seat (21) has no infinite flow effect. The absolute pressure control mechanism does not limit the pressure intake and exhaust of the cabin exhaust valve control chamber. The cabin exhaust valve has the maximum valve opening amount under the action of the pressure difference between the cabin and the control chamber. The aircraft is in a free ventilation state, and the pressure system trend is the same as that of the atmosphere.

[0040] As the flight altitude increases, the atmospheric pressure gradually decreases, and the cabin pressure and cabin exhaust valve control chamber pressure also gradually decrease. The sum of the preload forces of spring A (16) and spring B (17) expands the bellows assembly (13), and the distance between the valve rod (18) and the valve seat (21) decreases, resulting in flow restriction. The absolute pressure control mechanism limits the exhaust of the cabin exhaust valve control chamber, and the cabin exhaust valve control chamber pressure increases. The cabin exhaust valve valve opening amount decreases under the action of the pressure difference between the cabin and the control chamber, and the aircraft cabin pressure begins to be higher than the atmospheric pressure, and the first absolute pressure system begins to be implemented.

[0041] If the second absolute pressure system is to be implemented, the aircraft energizes the socket (8), and after the suction piece (20) and the electromagnet (7) are attracted, the diaphragm assembly (2) is controlled by the force of the bellows assembly (13) and the spring B (17). The preload force of the spring B (17) is determined by the position of the guide rod of the bellows assembly (13) in the adjusting stud (12) and the position of the adjusting stud (12) in the upper shell (10);

[0042] After the aircraft takes off, in the free ventilation stage, the preload force of the spring B (17) is insufficient to expand the bellows assembly (13), and the distance between the valve rod (18) and the valve seat (21) has no infinite flow effect. The absolute pressure control mechanism does not restrict the pressure intake and exhaust of the cabin exhaust valve control chamber. The cabin exhaust valve opens to the maximum amount under the pressure difference between the cabin and the control chamber. The aircraft is in a free ventilation state, and the pressure system trend is the same as that of the atmosphere.

[0043] As the flight altitude increases, the atmospheric pressure gradually decreases, and the cabin pressure and the cabin exhaust valve control chamber pressure also gradually decrease. The preload force of the spring B (17) causes the bellows assembly (13) to expand, and the distance between the valve rod (18) and the valve seat (21) decreases, resulting in flow restriction. The absolute pressure control mechanism limits the exhaust of the cabin exhaust valve control chamber, and the cabin exhaust valve control chamber pressure increases. The cabin exhaust valve valve opening amount decreases under the action of the pressure difference between the cabin and the control chamber, and the aircraft cabin pressure begins to be higher than the atmospheric pressure, and the second absolute pressure system begins to be implemented.

[0044] Since the aircraft uses the first or second pressure system when the socket (8) is powered on, the pressure system switching is not limited by time, place, or scene, and can be switched at will before or during flight. In addition, the mechanism integrates the control elements of the two pressure systems, which greatly reduces the weight and volume.

[0045] Example

[0046] An integrated absolute pressure control mechanism capable of automatically switching between dual pressure systems comprises a lower housing (1), a diaphragm assembly (2), a clamping ring A (3), a gasket A (4), a clamping ring B (5), a gasket B (6), an electromagnet (7), a socket (8), a rubber gasket A (9), an upper housing (10), a rubber gasket B (11), an adjusting stud (12), a bellows assembly (13), an upper cover (14), a sliding sleeve (15), a spring A (16), a spring B (17), a valve rod (18), a spring C (19), a suction plate (20), a valve seat (21), and a sealing plate (22). The diaphragm assembly (2) comprises a metal sheet, a diaphragm, and a sleeve;

[0047] The outer wall of the sleeve in the diaphragm assembly (2) is connected to the groove of the bellows assembly (13) by threads; one end of the spring B (17) is fixed on the inner step of the metal sheet in the diaphragm assembly (2), and the other end is fixed on the step on the bellows assembly (13); the gasket B (6), the suction sheet (20), and the spring A (16) are fixedly mounted and stacked in sequence at the outer step of the metal sheet in the diaphragm assembly (2); one end of the spring A (16) falls on the suction sheet (20), and the suction sheet (20) can drive the spring A (16) to move when power is turned on; the guide rod of the bellows assembly (13) passes through the guide hole of the sliding sleeve (15) and the internal threaded hole of the adjusting stud (12) in sequence; the other end of the spring A (16) is fixed on the step of the sliding sleeve (15); the lower end of the adjusting stud (12) contacts the groove plane of the sliding sleeve (15), and the upper end is fixed by The nut is tightened; the electromagnet (7) is installed on the step on the upper shell (10), the electromagnet (7) and the socket (8) are connected by a wire, the socket (8) and the upper shell (10) are connected by a screw, and a rubber gasket A (9) is installed in the middle; the clamping ring A (3) is installed in the groove of the upper shell (10); the clamping ring B (5) and the gasket A (4) are stacked and installed between the electromagnet (7) and the clamping ring A (3); the adjusting stud (12) and the upper shell (10) are connected by threads and tightened by a nut; the valve seat (21) and the lower shell (1) are connected by threads, and a sealing plate (22) is installed between the two; the valve rod (18) and the spring C (19) are installed in sequence between the inner groove of the sleeve in the diaphragm assembly (2) and the valve seat (21); the lower shell (1) and the diaphragm assembly (2) 、 The upper shell (10) is connected by screws; the upper shell (10) and the upper cover (14) are connected by screws, and a rubber gasket B (11) is installed between the two.

[0048] In a certain embodiment of the present invention, the diaphragm material is specifically a composite of silicone rubber compound GX2-50 and brocade twill silk 511;

[0049] In a certain embodiment of the present invention, the spring C (19) is used for resetting. When the elastic force of the spring C (19) satisfies the resetting condition, the smaller the preload force and stiffness are, the better.

[0050] In a certain embodiment of the present invention, the common preload force of the spring A (16) and the spring B (17) cooperates with the bellows assembly (13) to meet the pressure regulation requirements.

[0051] In a certain embodiment of the present invention, the preload force of the spring B (17) cooperates with the bellows assembly (13) to meet the pressure regulation requirements.

[0052] In a certain embodiment of the present invention, the number of gaskets B (6) should ensure that the suction plate (20) can be normally attracted when the electromagnet (7) is energized.

[0053] In a certain implementation case of the present invention, the number of sealing sheets (22) should meet the pressure regulation requirements.

[0054] In a certain embodiment of the present invention, the material of the bellows in the bellows assembly (13) should be beryllium bronze QBe2, which has high strength, high hardness and good processing performance.

[0055] It is understood by those skilled in the art that, unless otherwise defined, all terms (including technical terms and scientific terms) used herein have the same meaning as the general understanding of ordinary technicians in the field to which the present invention belongs. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and unless defined as here, will not be interpreted with idealized or overly formal meanings. The specific implementation methods described above further describe the purpose, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the present invention. Within the spirit and principle of the present invention, any technician familiar with the profession may use the above disclosed technical content to change or modify it into an equivalent embodiment of equivalent changes for application in other fields, but any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the technical solution content of the present invention, any modification, equivalent replacement, improvement, etc., made according to the technical essence of the present invention, should be included in the protection scope of the present invention.

Claims

1. An integrated absolute pressure control mechanism with dual pressure systems that can automatically switch, characterized in that: It includes a lower shell, a diaphragm assembly, a clamp ring A, a gasket A, a clamp ring B, a gasket B, an electromagnet, a socket, a rubber gasket A, an upper shell, a rubber gasket B, an adjusting stud, a bellows assembly, an upper cover, a sliding sleeve, a spring A, a spring B, a valve rod, a spring C, a suction piece, a valve seat, and a sealing piece; the diaphragm assembly includes a metal sheet, a diaphragm, and a sleeve; The outer wall of the sleeve in the diaphragm assembly is connected to the groove of the bellows assembly by threads, one end of the spring B is fixed on the inner step of the metal sheet in the diaphragm assembly, and the other end is fixed on the step on the bellows assembly; the gasket B, the suction sheet, and the spring A are fixedly stacked and installed in sequence at the outer step of the metal sheet in the diaphragm assembly, one end of the spring A falls on the suction sheet, and the suction sheet can drive the spring A to move when power is turned on; the guide rod of the bellows assembly passes through the guide hole of the sliding sleeve and the internal threaded hole of the adjusting stud in sequence, the other end of the spring A is fixed on the step of the sliding sleeve, and the lower end of the adjusting stud is in contact with the groove plane of the sliding sleeve, The upper end is tightened by a nut; the electromagnet is installed on the step on the upper shell, the electromagnet is connected to the socket by a wire, the socket is connected to the upper shell by a screw, and a rubber gasket A is installed in the middle; the clamping ring A is installed in the groove of the upper shell; the clamping ring B and the gasket A are stacked and installed between the electromagnet and the clamping ring A in sequence; the adjusting stud is connected to the upper shell by a thread and tightened by a nut; the valve seat is connected to the lower shell by a thread, and a sealing sheet is installed between the two; the valve rod and the spring C are installed in sequence between the inner groove of the sleeve and the valve seat in the diaphragm assembly; the lower shell and the diaphragm assembly 、 The upper shell is connected by screws; the upper shell and the upper cover are connected by screws, and a rubber gasket B is installed between the two.

2. The mechanism according to claim 1, characterized in that: The diaphragm material is specifically a composite of silicone rubber compound GX2-50 and brocade twill silk 511.

3. The mechanism according to claim 2, characterized in that: The spring C is used for resetting. When the elastic force of the spring C satisfies the resetting condition, the smaller the preload force and the stiffness are, the better.

4. The mechanism according to claim 3, characterized in that: The common preload force of the spring A and the spring B cooperates with the bellows assembly to meet the pressure regulation requirements.

5. The mechanism according to claim 4, characterized in that: The preload force of the spring B cooperates with the bellows assembly to meet the pressure regulation requirements.

6. The mechanism according to claim 5, characterized in that The number of gaskets B should ensure that the suction piece can be normally attracted when the electromagnet is energized.

7. The mechanism according to claim 6, characterized in that The number of sealing pieces should meet the pressure regulation requirements.

8. The mechanism according to claim 7, characterized in that The material of the bellows in the bellows assembly should be beryllium bronze QBe2, which has high strength, high hardness and good processing performance.

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