Pressure relief valve for airplane

Abstract

The utility model discloses a pressure relief valve for an airplane, which comprises a cylindrical valve body, a valve core, a pressure relief valve core and a pressure relief valve core, the two valve seats are oppositely arranged at the two ends of the valve body; the valve core is fixedly arranged in the valve body; the valve plate is slidably connected to the valve element; wherein the valve body, the valve core, the valve seat and the valve plate are coaxially arranged; the valve element comprises a valve rod and an elastic piece, the valve rod is sleeved with the elastic piece, one end of the elastic piece is fixedly connected to one of the two valve seats, and the other end of the elastic piece is connected to the valve plate. When gas flows through the valve element, the pressure of the gas acts on the valve plate, and the valve plate is restrained to do axial movement on the valve rod through the acting force of the elastic piece. The pressure relief valve can replace an existing valve plate and an existing ground valve, the pressure relief valve can give consideration to the pressure relief function of an airplane in various states, the occupied space of the valve plate and the ground valve on the airplane can be reduced, and therefore the overall weight of the airplane is reduced.

Description

Technical Field

[0001] The present application relates to the technical field of flight control systems, and in particular to a pressure relief valve used on an aircraft. Background Art

[0002] The pressure relief valve is the main equipment of the civil aircraft pressure regulation system to realize the positive and negative pressure relief protection function of the aircraft cabin. Modern civil aircraft use the pressure relief valve to connect the gas inside and outside the cabin through a pipeline to monitor the pressure inside and outside the cabin. When the pressure difference between the inside and outside of the cabin reaches a certain value, it opens to maintain the positive and negative pressure difference of the aircraft cabin within a certain range, thereby protecting the cabin personnel and the aircraft structure.

[0003] The pressure relief valve is generally installed on a spherical frame, and is generally composed of a pressure differential chamber, a control chamber, a diaphragm, a valve plate, an actuating chamber, a filter, a spring assembly, and an external pressure-leading pipe. The inside of the diaphragm box in the pressure differential chamber is connected to the inside of the cabin through a filter, and the external pressure-leading pipe is connected to the outside of the cabin. When the positive pressure difference between the inside and outside of the cabin exceeds the set value, the diaphragm box extends, the ejector pin opens, and the pressure decreases after the control chamber and the pressure differential chamber are connected. The pressure in the actuating chamber is greater than that in the control chamber. The valve is actuated upward by the spring to drive the valve plate to open, and the inside and outside of the cabin are connected, and the pressure difference between the inside and outside of the cabin is controlled. When the negative positive pressure difference between the inside and outside of the cabin exceeds the set value, the negative pressure difference pushes the valve plate upward to open, and the inside and outside of the cabin are connected, and the pressure difference between the inside and outside of the cabin is controlled. A micro switch is built into the pressure relief valve to monitor its switch state and send the switch state to the environmental control controller. The pressure relief valve is a mechanical valve, which is driven by sensing the pressure inside and outside the cabin and is not affected by the environmental control controller.

[0004] The ground valve is the main equipment for the pressure regulating system of civil aircraft to achieve ground pressure relief. The valve is mainly opened when the aircraft lands so that the residual pressure in the cabin can be reduced in time and the cabin door can be opened in time to prevent the cabin door from being unable to open during extreme failure conditions such as emergency evacuation, causing catastrophic consequences.

[0005] The ground valve is usually installed on a spherical frame and is generally composed of a motor, an actuator, a valve plate and sealing materials. When the aircraft lands on the ground, the ground valve receives an opening command from the controller and actuates the valve plate through the motor to open the valve plate, reducing the residual pressure in the cabin. When the aircraft takes off, the ground valve receives a closing command from the controller, the valve closes, and the aircraft is pressurized. The ground valve is an electric valve that is actuated by receiving instructions from the environmental control controller.

[0006] At present, since the pressure relief valve and the ground valve are generally installed on the spherical frame at the same time, the two take up a large space on the aircraft and increase the overall weight of the aircraft. In addition, the ground valve is only used when on the ground and has few usage scenarios. The functions of the pressure relief valve and the ground valve are both to release pressure, so how to integrate the pressure relief valve and the ground valve into a pressure relief valve is a technical problem that needs to be solved urgently. Utility Model Content

[0007] The utility model aims to provide a pressure relief valve for an aircraft, so as to solve the technical problems that the existing pressure relief valves and ground valves on the aircraft occupy a large space, the overall weight of the aircraft is heavy, and the ground valve has few usage scenarios.

[0008] To achieve the above-mentioned purpose, the utility model provides a pressure relief valve for an aircraft, comprising: a valve body, which is cylindrical; two valve seats, which are relatively arranged at the two ends of the valve body; a valve core, which is fixedly arranged in the valve body; and a valve plate, which can be slidably connected to the valve core; wherein the valve body is coaxially arranged with the valve core, the valve seat, and the valve plate; the valve core comprises a valve stem and an elastic member, the elastic member is sleeved on the valve stem, one end of the elastic member is fixedly connected to one of the two valve seats, and the other end is connected to the valve plate; when gas flows through the valve core, the pressure of the gas acts on the valve plate, and the valve plate is constrained to make axial movement on the valve stem through the force of the elastic member.

[0009] Furthermore, the valve body has a first air port and a second air port for gas circulation, the first air port is connected to the inside of the aircraft cabin, and the second air port is connected to the outside of the aircraft cabin; when the air pressure inside the aircraft cabin is greater than the air pressure outside the aircraft cabin, the valve plate moves axially on the valve stem from the inside of the aircraft cabin to the outside of the aircraft cabin, and the elastic member is gradually compressed.

[0010] Furthermore, the pressure of the gas inside the aircraft cabin acting on the valve plate is defined as F1, and the pressure of the gas outside the aircraft cabin acting on the valve plate is defined as F2; ​​when F1>F2, and the pressure difference between F1 and F2 is maintained at a set value, and the set value is not zero, a sealed closed state is formed between the valve plate and the valve body, and the elastic member is in a compressed state.

[0011] Furthermore, the pressure of the gas inside the aircraft cabin acting on the valve plate is defined as F1, and the pressure of the gas outside the aircraft cabin acting on the valve plate is defined as F2; ​​when F1>F2, and the pressure difference between F1 and F2 is greater than a set value, and the set value is not zero, the valve plate is opened, and the elastic member is in a compressed state.

[0012] Furthermore, the valve body has a first air port and a second air port for gas circulation, the first air port is connected to the inside of the aircraft cabin, and the second air port is connected to the outside of the aircraft cabin; when the air pressure inside the aircraft cabin is lower than the air pressure outside the aircraft cabin, the valve plate moves axially on the valve stem from the outside of the aircraft cabin to the inside of the aircraft cabin, and the elastic member is gradually stretched.

[0013] Furthermore, the pressure of the gas inside the aircraft cabin acting on the valve plate is defined as F1, and the pressure of the gas outside the aircraft cabin acting on the valve plate is defined as F2; ​​when F1<F2, and the pressure difference between F1 and F2 is maintained at a set value, and the set value is not zero, a sealed closed state is formed between the valve plate and the valve body, and the elastic member is in a compressed state.

[0014] Furthermore, the pressure of the gas inside the aircraft cabin acting on the valve plate is defined as F1, and the pressure of the gas outside the aircraft cabin acting on the valve plate is defined as F2; ​​when F1<F2, and the pressure difference between F1 and F2 is less than a set value, and the set value is not zero, the valve plate is opened, and the elastic member is in a stretched state.

[0015] Furthermore, the pressure of the gas inside the aircraft cabin acting on the valve plate is defined as F1, and the pressure of the gas outside the aircraft cabin acting on the valve plate is defined as F2; ​​when F1=F2, and the pressure difference between F1 and F2 is zero, the valve plate is opened, and the elastic member remains unchanged.

[0016] Furthermore, the aperture of the first air guide port and / or the second air guide port is smaller than the aperture of the valve body.

[0017] Furthermore, the valve plate is provided with a through hole, the aperture of which matches the diameter of the valve stem; and the outer diameter of the valve plate is equal to the inner diameter of the valve body.

[0018] The technical effect of the utility model is to provide a pressure relief valve for an aircraft, comprising a coaxially arranged valve body, a valve core and a valve plate; wherein the valve core comprises a valve stem and an elastic member, and when gas flows through the valve core, the pressure of the gas acts on the valve plate, and the force of the elastic member constrains the valve plate to make axial movement on the valve stem. The pressure relief valve of the present application can replace the existing pressure relief valve and ground valve, and the pressure relief valve can take into account the pressure relief function of the aircraft in various states, and can reduce the space occupied by the pressure relief valve and the ground valve on the aircraft, thereby reducing the overall weight of the aircraft.

[0019] When the aircraft is on the ground, when the pressure difference between the inside and outside of the cabin reaches the pressure difference during ground pressure relief, the valve plate opens under the action of the elastic part, the inside of the cabin is connected with the outside of the cabin, the pressure difference between the inside and outside of the cabin is reduced, and the ground pressure relief function is completed.

[0020] When the aircraft takes off, as the pressure difference between the inside and outside of the cabin increases, the valve plate compresses the elastic part to move in the valve body, the inside and outside of the cabin cannot be connected, and the pressure regulating system is pressurized normally.

[0021] When the pressure difference between the inside and outside of the aircraft cabin exceeds the positive pressure relief setting value, the valve plate opens under the action of the pressure difference, the inside of the cabin is connected with the outside of the cabin, the pressure difference between the inside and outside of the cabin is reduced, and the positive pressure relief protection function is completed.

[0022] When the aircraft makes an emergency descent and the pressure difference between the inside and outside of the cabin exceeds the negative pressure relief setting value, the valve plate opens under the action of the pressure difference, the inside of the cabin is connected with the outside of the cabin, the pressure difference between the inside and outside of the cabin is reduced, and the positive pressure relief protection function is completed. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The technical solution and other beneficial effects of the present application will be made apparent by describing in detail the specific implementation methods of the present application in conjunction with the accompanying drawings.

[0024] Figure 1 A schematic diagram of the structure of the pressure relief valve provided in an embodiment of the present application in a normal state.

[0025] Figure 2 A schematic diagram of the structure of the pressure relief valve in the pre-pressurization state provided in an embodiment of the present application.

[0026] Figure 3 A schematic diagram of the structure of the pressure relief valve provided in an embodiment of the present application in a normal state in the air.

[0027] Figure 4 A schematic diagram of the structure of the pressure relief valve provided in an embodiment of the present application under the maximum pressure difference state in the air.

[0028] Figure 5 A schematic diagram of the structure of the pressure relief valve provided in an embodiment of the present application in a positive pressure relief state.

[0029] Figure 6 A schematic diagram of the structure of the pressure relief valve provided in an embodiment of the present application in a negative pressure relief state.

[0030] The components of the attached drawings are identified as follows:

[0031] 1. Valve body; 2. Valve seat; 3. Valve core; 4. Valve plate; 5. Fixed seat; 61. First air guide port; 62. Second air guide port; 31. Valve stem; 32. Elastic member. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0033] In some embodiments, Figure 1 As shown, a pressure relief valve for an aircraft is provided, which includes a coaxially arranged valve body 1, a valve seat 2, a valve core 3, a valve plate 4 and a fixed seat 5.

[0034] The valve body 1 is cylindrical and has a first air guide port 61 and a second air guide port 62 for gas circulation. The first air guide port 61 is connected to the inside of the aircraft cabin, and the second air guide port 62 is connected to the outside of the aircraft cabin.

[0035] In some embodiments, when in use, the pressure relief valve is installed on the aircraft so that the first air guide port 61 on the left side faces the inside of the aircraft cabin and the second air guide port 62 on the right side faces the outside of the aircraft cabin.

[0036] Two valve seats 2 are arranged opposite to each other at two ends of the valve body 1 .

[0037] The valve core 3 is fixedly arranged in the valve body 1, and the valve core 3 includes a valve stem 31 and an elastic member 32. The left end of the valve stem 31 can be fixedly connected to the valve seat 2 on the same side as the first air guide port 61, and the right end of the valve stem 31 can be fixedly connected to the valve seat 2 on the same side as the second air guide port 62. In other embodiments, the connection between the valve stem 31 and the valve stem 31 can be a detachable connection, such as a threaded connection. The elastic member 32 is sleeved on the valve stem 31, one end of the elastic member 32 is fixedly connected to one of the two valve seats 2, and the other end is connected to the valve plate 4. In the embodiment of the present application, the left end of the valve stem 31 is fixedly connected to the valve plate 4, and the right end of the valve stem 31 is connected to the right valve seat 2. The elastic member 32 includes but is not limited to a spring.

[0038] In some embodiments, the elastic member 32 mainly plays the role of driving the valve plate 4. When the pressure difference between the cabin interior and the cabin exterior is too large, the elastic member 32 is compressed to open the valve plate 4; when the pressure difference between the cabin interior and the cabin exterior is too small, the elastic member 32 is stretched to open the valve plate 4; when the cabin interior is normally pressurized, the pressure difference between the cabin interior and the cabin exterior and the elastic member 32 work together to close the valve. The spring mainly plays the role of driving the valve plate to move. When the pressure difference is too large, the spring is compressed to open the valve. When the pressure difference is too small, the spring is stretched to open the valve. When the pressure difference is normally pressurized, the pressure difference and the spring work together to close the valve.

[0039] The valve plate 4 is slidably connected to the valve core 3, and the valve plate 4 is provided with a through hole, through which the valve plate 4 is sleeved on the valve stem 31, and the aperture of the through hole matches the diameter of the valve stem 31, and the valve plate 4 is guided by the valve stem 31 so that the valve plate 4 can make axial movements back and forth on the valve stem 31. A sealing ring (not shown) may be provided between the valve plate 4 and the valve stem 31, and the valve stem 31 may also be provided with a guide sleeve (not shown).

[0040] In some embodiments, the outer diameter of the valve plate 4 is equal to the inner diameter of the valve body 1. The apertures of the first air guide port 61 and the second air guide port 62 are both smaller than the aperture of the valve body 1. The aperture of the first air guide port 61 may be equal to or different from the aperture of the second air guide port 62, and no special limitation is made here.

[0041] The fixing seat 5 is arranged outside the valve body 1 . For example, the fixing seat 5 can be sleeved on the valve body 1 . There is no special limitation here.

[0042] In some embodiments, when gas flows through the valve core 3 , the pressure of the gas acts on the valve plate 4 , and the force of the elastic member 32 constrains the valve plate 4 to make axial movement on the valve stem 31 .

[0043] In some embodiments, when the air pressure inside the aircraft cabin is greater than the air pressure outside the aircraft cabin, the valve plate 4 moves axially from the inside of the aircraft cabin to the outside of the aircraft cabin on the valve stem 31, and the elastic member 32 is gradually compressed. That is, the valve plate 4 moves from the left end to the right end of the valve stem 31 under the action of the air pressure, and the elastic member 32 is also compressed from left to right.

[0044] In some embodiments, when the air pressure inside the aircraft cabin is lower than the air pressure outside the aircraft cabin, the valve plate 4 moves axially on the valve stem 31 from outside the aircraft cabin to inside the aircraft cabin, and the elastic member 32 is gradually stretched, that is, the valve plate 4 moves from the right end to the left end of the valve stem 31 under the action of air pressure, and the elastic member 32 is also stretched from right to left.

[0045] During the operation of an aircraft, there are generally divided into normal state, pre-pressurization state, normal state in the air, maximum pressure difference state in the air, positive decompression state and negative decompression state. The various states will be explained below.

[0046] In some embodiments, Figure 1 As shown, the normal state is a static state when the aircraft is on the ground and the pressure inside the cabin is equal to the pressure outside the cabin. At this time, the valve plate 4 is stationary at the first air guide port 61, and the elastic member 32 remains unchanged, that is, in the normal state, the inside of the cabin is connected with the outside of the cabin.

[0047] It is defined that the pressure of the gas inside the aircraft cabin acting on the valve plate 4 is F1, the pressure of the gas outside the aircraft cabin acting on the valve plate 4 is F2, and the pressure of the elastic member 32 acting on the valve plate 4 is F3.

[0048] When F1=F2, and the pressure difference between F1 and F2 is zero, the pressure relief valve is in a normal state, the valve plate 4 is opened, and the elastic member 32 remains unchanged.

[0049] In some embodiments, Figure 2As shown, the pre-pressurization state is that the pressure inside the cabin is pre-pressurized to a certain value on the ground, the valve plate 4 is closed to seal the valve body 1, and the cabin can be pressurized normally.

[0050] When F1>F2, and the pressure difference between F1 and F2 is maintained at a set value, and the set value is not zero, a sealed closed state is formed between the valve plate 4 and the valve body 1, and the elastic member 32 is in a compressed state. At this time, F1=F2+F3. It should be noted that the set value in the embodiment of the present application can be set according to the actual state of the aircraft, and is not particularly limited here.

[0051] As the aircraft's altitude rises, the aircraft will transition from its normal state in the air to the maximum pressure difference state and the positive pressure relief state in sequence, allowing the pressure relief valve to perform the pressure relief function in various states.

[0052] In some embodiments, Figure 3 As shown, the normal state of an aircraft in the air is that the aircraft gradually rises and the pressure difference between the inside and outside of the cabin gradually increases.

[0053] When F1>F2, and the pressure difference between F1 and F2 is maintained at a set value, and the set value is not zero, a sealed closed state is formed between the valve plate 4 and the valve body 1, and the elastic member 32 is in a compressed state. At this time, F1>F2+F3, and the valve plate 4 gradually moves from left to right on the valve stem 31. Alternatively, in other embodiments, when F1<F2, and the pressure difference between F1 and F2 is maintained at a set value, and the set value is not zero, a sealed closed state is formed between the valve plate 4 and the valve body 1, and the elastic member 32 is gradually stretched and in a compressed state. At this time, F1<F2+F3, and the valve plate 4 gradually moves from right to left on the valve stem 31.

[0054] In some embodiments, Figure 4 As shown, the maximum pressure difference state of the aircraft in the air is that as the aircraft altitude increases, the pressure difference between the inside and outside of the cabin gradually increases to the maximum value of normal pressurization.

[0055] When F1>F2, and the pressure difference between F1 and F2 is maintained at a set value, and the set value is not zero, a sealed closed state is formed between the valve plate 4 and the valve body 1, and the elastic member 32 is in a compressed state. At this time, F1=F2+F3, the valve plate 4 is at the right end of the valve body 1, and the inner cavity of the valve body 1 is connected to the interior of the cabin.

[0056] In some embodiments, Figure 5 As shown, the positive decompression state of the aircraft is that abnormal pressurization occurs inside the cabin, resulting in excessive pressure difference between the inside and outside of the cabin.

[0057] When F1>F2, and the pressure difference between F1 and F2 is greater than a set value, and the set value is not zero, the valve plate 4 is opened, and the elastic member 32 is in a compressed state. At this time, F1>F2+F3, the valve plate 4 is located at the second air guide port 62, and the interior of the cabin is connected to the outside of the cabin.

[0058] As the aircraft makes an emergency descent, it will switch from the maximum pressure difference state in the air to the negative pressure relief state, allowing the pressure relief valve to perform the pressure relief function under various conditions.

[0059] Specifically, in some embodiments, the maximum pressure difference state of the aircraft in the air can also be that as the aircraft altitude decreases, the pressure difference between the inside and outside of the cabin gradually decreases to a normal value. The negative pressure relief state of the aircraft is when the aircraft performs an emergency descent, resulting in an excessive pressure difference between the inside and outside of the cabin.

[0060] When F1<F2, and the pressure difference between F1 and F2 is maintained at a set value, and the set value is not zero, the valve plate 4 is opened, and the elastic member 32 is in a stretched state. At this time, F1=F2-F3, the valve plate 4 is at the left end of the valve body 1, and the inner cavity of the valve body 1 is connected to the outside of the cabin.

[0061] like Figure 6 As shown, when F1<F2, and the pressure difference between F1 and F2 is less than a set value, and the set value is not zero, the valve plate 4 is opened, and the elastic member 32 is in a stretched state. At this time, F1+F3<F2, the valve plate 4 is located at the first air guide port 61, and the interior of the cabin is connected to the outside of the cabin.

[0062] Therefore, an embodiment of the present application provides a pressure relief valve for use on an aircraft to replace the existing valve plate 4 and ground valve. The pressure relief valve can take into account the pressure relief function of the aircraft in various states, and can reduce the space occupied by the valve plate 4 and the ground valve on the aircraft, thereby reducing the overall weight of the aircraft.

[0063] When the aircraft is on the ground, when the pressure difference between the inside and outside of the cabin reaches the pressure difference during ground pressure relief, the valve plate 4 opens under the action of the elastic member 32, the inside of the cabin is connected with the outside of the cabin, the pressure difference between the inside and outside of the cabin is reduced, and the ground pressure relief function is completed.

[0064] When the aircraft takes off, as the pressure difference between the cabin interior and the cabin exterior increases, the valve plate 4 compresses the elastic member 32 to move in the valve body 1, the cabin interior and the cabin exterior are disconnected, and the pressure regulating system is pressurized normally.

[0065] When the pressure difference between the inside and outside of the aircraft cabin exceeds the positive pressure relief setting value, the valve plate 4 opens under the action of the pressure difference, the inside of the cabin is connected with the outside of the cabin, the pressure difference between the inside and outside of the cabin is reduced, and the positive pressure relief protection function is completed.

[0066] When the aircraft makes an emergency descent and the pressure difference between the inside and outside of the cabin exceeds the negative pressure relief setting value, the valve plate 4 opens under the action of the pressure difference, the inside of the cabin is connected with the outside of the cabin, the pressure difference between the inside and outside of the cabin is reduced, and the positive pressure relief protection function is completed.

[0067] The above is a detailed introduction to a pressure relief valve for an aircraft provided in an embodiment of the present application. Specific examples are used herein to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the technical solution and its core idea of ​​the present application. Ordinary technicians in this field should understand that they can still modify the technical solutions recorded in the aforementioned embodiments, or replace some of the technical features therein with equivalents; and these modifications or replacements do not make the essence of the corresponding technical solution deviate from the scope of the technical solution of the embodiments of the present application.

Claims

1. A pressure relief valve for an aircraft, characterized in that: include: A valve body (1) which is cylindrical; Two valve seats (2) are arranged opposite to each other at two ends of the valve body (1); A valve core (3) is fixedly arranged in the valve body (1); and A valve plate (4) slidably connected to the valve core (3); Wherein, the valve body (1) is coaxially arranged with the valve core (3), the valve seat (2) and the valve plate (4); The valve core (3) comprises a valve stem (31) and an elastic member (32), wherein the elastic member (32) is sleeved on the valve stem (31), one end of the elastic member (32) is fixedly connected to one of the two valve seats (2), and the other end is connected to the valve plate (4); When gas flows through the valve core (3), the pressure of the gas acts on the valve plate (4), and through the action force of the elastic member (32), the valve plate (4) is constrained to move axially on the valve stem (31).

2. The pressure relief valve according to claim 1, characterized in that: The valve body (1) has a first air guide port (61) and a second air guide port (62) for gas circulation, wherein the first air guide port (61) is connected to the interior of the aircraft cabin, and the second air guide port (62) is connected to the exterior of the aircraft cabin; When the air pressure inside the aircraft cabin is greater than the air pressure outside the aircraft cabin, the valve plate (4) moves axially on the valve stem (31) from the inside of the aircraft cabin to the outside of the aircraft cabin, and the elastic member (32) is gradually compressed.

3. The pressure relief valve according to claim 2, characterized in that: The pressure of the gas inside the aircraft cabin acting on the valve plate (4) is defined as F1, and the pressure of the gas outside the aircraft cabin acting on the valve plate (4) is defined as F2; When F1>F2, and the pressure difference between F1 and F2 is maintained at a set value, and the set value is not zero, a sealed closed state is formed between the valve plate (4) and the valve body (1), and the elastic member (32) is in a compressed state.

4. The pressure relief valve according to claim 2, characterized in that: The pressure of the gas inside the aircraft cabin acting on the valve plate (4) is defined as F1, and the pressure of the gas outside the aircraft cabin acting on the valve plate (4) is defined as F2; When F1>F2, and the pressure difference between F1 and F2 is greater than a set value, and the set value is not zero, the valve plate (4) is opened, and the elastic member (32) is in a compressed state.

5. The pressure relief valve according to claim 1, characterized in that: The valve body (1) has a first air guide port (61) and a second air guide port (62) for gas circulation, wherein the first air guide port (61) is connected to the interior of the aircraft cabin, and the second air guide port (62) is connected to the exterior of the aircraft cabin; When the air pressure inside the aircraft cabin is lower than the air pressure outside the aircraft cabin, the valve plate (4) moves axially on the valve stem (31) from outside the aircraft cabin to inside the aircraft cabin, and the elastic member (32) is gradually stretched.

6. The pressure relief valve according to claim 5, characterized in that: The pressure of the gas inside the aircraft cabin acting on the valve plate (4) is defined as F1, and the pressure of the gas outside the aircraft cabin acting on the valve plate (4) is defined as F2; When F1<F2, and the pressure difference between F1 and F2 is maintained at a set value, and the set value is not zero, a sealed closed state is formed between the valve plate (4) and the valve body (1), and the elastic member (32) is in a compressed state.

7. The pressure relief valve according to claim 6, characterized in that: The pressure of the gas inside the aircraft cabin acting on the valve plate (4) is defined as F1, and the pressure of the gas outside the aircraft cabin acting on the valve plate (4) is defined as F2; When F1<F2, and the pressure difference between F1 and F2 is less than a set value, and the set value is not zero, the valve plate (4) is opened, and the elastic member (32) is in a stretched state.

8. The pressure relief valve according to claim 1, characterized in that: The pressure of the gas inside the aircraft cabin acting on the valve plate (4) is defined as F1, and the pressure of the gas outside the aircraft cabin acting on the valve plate (4) is defined as F2; When F1=F2, and the pressure difference between F1 and F2 is zero, the valve plate (4) is opened, and the elastic member (32) remains unchanged.

9. The pressure relief valve according to claim 2 or 5, characterized in that: The aperture of the first air guide port (61) and / or the second air guide port (62) is smaller than the aperture of the valve body (1).

10. The pressure relief valve according to claim 1, characterized in that: The valve plate (4) is provided with a through hole, the diameter of which matches the diameter of the valve stem (31); The outer diameter of the valve plate (4) is equal to the inner diameter of the valve body (1).

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