Dual pressure regime automatically switchable integrated absolute pressure control mechanism

Abstract

The present application relates to the technical field of aircraft cabin pressure regulator, and relates to an integrated absolute pressure control mechanism capable of automatically switching between two pressure systems. The integrated absolute pressure control mechanism comprises a lower shell, a diaphragm assembly, a ring A, a gasket A, a 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 the electromagnet of the integrated absolute pressure control mechanism is not attracted, the two springs and the diaphragm assembly simultaneously control the opening and closing position of the valve, and determine a cabin pressure system, and the function is equivalent to a set of absolute pressure control mechanism in a traditional split type absolute pressure control mechanism.

Description

Technical Field

[0001] This invention relates to the field of aircraft cabin pressure regulator technology, and to an integrated absolute pressure control mechanism with automatic switching between dual pressure systems. Background Technology

[0002] The cabin pressure regulation subsystem, belonging to the aircraft environmental control system, mainly consists of a cabin pressure controller, cabin exhaust valves, and cabin safety valves. The cabin pressure controller and cabin exhaust valves work together; the control chamber of the cabin exhaust valve is connected to the cabin, and their pressure changes follow the same trend, differing only slightly in numerical values. The cabin pressure controller regulates the pressure in the control chamber of the cabin exhaust valve, and the cabin exhaust valve, based on the regulated pressure signal, lifts its valve to control the cabin pressure, keeping it within the required range and meeting the expected cabin pressure regime. The aircraft cabin pressure regime generally consists of three phases: free ventilation, absolute pressure control, and overpressure control.

[0003] For cabin pressure controllers, the existing technology structure is as follows: Figure 1 As shown, it consists of a housing assembly, valve seat, diaphragm assembly, top cover, valve assembly, bellows assembly, top cover, spring, cap, switch, handle, bottom cover, nut, and screws. This type of cabin pressure controller is designed to meet the dual-pressure system requirements for takeoff and landing at airports at different altitudes. It features two independent absolute pressure control mechanisms, I and II. Before takeoff, operators must manually switch the three-way switch assembly II to determine which absolute pressure control mechanism and pressure system to use for the flight, based on the aircraft's requirements. This inability to change the control mechanism mid-flight restricts the takeoff and landing altitudes, especially when taking off from plains airports and landing at high-altitude airports. Because the cabin pressure is significantly higher than atmospheric pressure during landing, improper depressurization can lead to pressure sore ears and, in severe cases, damage to the aircraft structure.

[0004] The existing technology has the following problems: 1. In order to meet the requirement of using a dual pressure system, two independent absolute pressure control mechanisms are set up, which is complex in structure; 2. Before each takeoff, the staff needs to manually switch the three-way switch assembly to determine which absolute pressure control mechanism and pressure system to use for this flight according to the usage requirements. 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 altitude of the takeoff airport restricts the altitude of the landing airport, thus limiting flight. Summary of the Invention

[0005] Purpose of the invention An integrated absolute pressure control mechanism with automatic switching between dual pressure regimes is proposed. This addresses the problems of current cockpit pressure controllers being complex, requiring manual switching of pressure regimes, and being unable to switch pressure regimes during flight.

[0006] Technical solution An integrated absolute pressure control mechanism with automatic switching between dual pressure systems includes a lower housing, a diaphragm assembly, a retaining ring A, a gasket A, a retaining ring B, a gasket B, an electromagnet, a socket, a rubber gasket A, an upper housing, a rubber gasket B, an adjusting stud, a bellows assembly, a top cover, a sliding sleeve, springs A and B, a valve rod, a spring C, a suction plate, a valve seat, and a sealing plate. The diaphragm assembly includes a metal sheet, a diaphragm, and a sleeve. The outer wall of the sleeve in the diaphragm assembly is threadedly connected to the groove of the bellows assembly. One end of spring B is fixed to the inner step of the metal sheet in the diaphragm assembly, and the other end is fixed to the step on the bellows assembly. A gasket B, a suction plate, and spring A are sequentially stacked and fixed at the outer step of the metal sheet in the diaphragm assembly. One end of spring A rests on the suction plate, and when energized, the suction plate can move spring A. The guide rod of the bellows assembly passes sequentially through the guide hole of the sliding sleeve and the internal threaded hole of the adjusting stud. The other end of spring A is fixed to the step of the sliding sleeve. The lower end of the adjusting stud contacts the groove plane of the sliding sleeve, and the upper end is tightened by a nut. The electromagnet is installed on the upper shell. At the step on the body, the electromagnet is connected to the socket via a wire, and the socket is connected to the upper housing via screws, with a rubber gasket A installed in between; the retaining ring A is installed in the groove of the upper housing; the retaining ring B and the gasket A are stacked sequentially between the electromagnet and the retaining ring A; the adjusting stud is connected to the upper housing via a thread and tightened by a nut; the valve seat is connected to the lower housing via a thread, with a sealing plate installed between them; a valve rod and a spring C are sequentially installed between the inner groove of the sleeve and the valve seat in the diaphragm assembly; the lower housing, the diaphragm assembly, and the upper housing are connected by screws; the upper housing and the upper cover are connected by screws, with a rubber gasket B installed between them.

[0007] Furthermore, the diaphragm material is specifically a composite of silicone rubber compound GX2-50 and brocade twill fabric 511; Furthermore, the spring C is used for reset, and the spring force of the spring C should be as small as possible in terms of preload and stiffness while satisfying the reset conditions.

[0008] Furthermore, the combined preload of springs A and B, in conjunction with the bellows assembly, should meet the pressure regulation requirements.

[0009] Furthermore, the preload of the spring B, in conjunction with the bellows assembly, should meet the pressure adjustment requirements.

[0010] Furthermore, the number of gaskets B should ensure that the attracting plate can be properly attracted when the electromagnet is energized.

[0011] Furthermore, the number of sealing plates should meet the pressure regulation requirements.

[0012] Furthermore, the material of the bellows in the bellows assembly should be beryllium bronze QBe2, which has high strength, high hardness, and good machinability.

[0013] The beneficial effects of this application are as follows: This invention provides an integrated absolute pressure control mechanism with automatic switching between dual pressure systems. In the integrated absolute pressure control mechanism, when the electromagnet is not engaged, two spring and diaphragm assemblies simultaneously control the valve opening and closing position, determining a cabin pressure system. Its function is equivalent to one absolute pressure control mechanism in a traditional split absolute pressure control mechanism. The integrated absolute pressure control mechanism features an electromagnet that, when engaged, shields one of the springs, allowing the other spring and diaphragm assembly to simultaneously control the valve's opening and closing position. This structure defines a cabin pressure regime, functionally equivalent to a single absolute pressure control mechanism in a traditional split-type absolute pressure control system. The integrated absolute pressure control mechanism determines which cabin pressure regime is used based on whether the electromagnet is engaged. Compared to the traditional split absolute pressure control mechanism, the two absolute pressure control mechanisms are controlled by a manual toggle switch, which makes the system simple in structure, automatically switch pressure regimes, and have no restrictions on the timing of the switch. This avoids damage to the aircraft due to the selection of a pressure regime that is not suitable for the airport altitude. Attached Figure Description

[0014] Figure 1 This is a structural diagram of the existing technology; Figure 2 This is a schematic diagram of an integrated absolute pressure control mechanism with automatic switching between dual pressure systems, according to an embodiment of the present invention.

[0015] The components include: lower housing-1, diaphragm assembly-2, retaining ring A-3, gasket A-4, retaining ring B-5, gasket B-6, electromagnet-7, socket-8, rubber gasket A-9, upper housing-10, rubber gasket B-11, adjusting stud-12, bellows assembly-13, upper cover-14, sliding sleeve-15, spring A-16, spring B-17, valve rod-18, spring C-19, suction plate-20, valve seat-21, and sealing plate-22. Detailed Implementation

[0016] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below. In the examples, the same or similar reference numerals denote the same or similar components or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of this invention. The embodiments described below with reference to reference are exemplary and intended to explain this invention, and should not be construed as limiting the invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention. The embodiments of this invention will be described in detail below.

[0017] Invention Point 1: An integrated absolute pressure control mechanism with automatic switching between dual pressure systems, comprising a lower housing 1, a diaphragm assembly 2, a retaining ring A3, a gasket A4, a retaining ring B5, a gasket B6, an electromagnet 7, a socket 8, a rubber gasket A9, an upper housing 10, a rubber gasket B11, an adjusting stud 12, a bellows assembly 13, a top cover 14, a sliding sleeve 15, a spring A16, a spring B17, a valve rod 18, a spring C19, a suction plate 20, a valve seat 21, and a sealing plate 22. The lower housing 1, the diaphragm assembly 2, and the upper housing 10 are connected together by screws; the socket 8 and the upper housing 10 are connected together by screws; the upper housing 10 and the top cover 14 are connected together by threads; and the electromagnet 7 and the socket 8 are connected together by wires.

[0018] Invention Point 2: The upper housing 10 has a groove machined on it to make an interference fit with the retaining ring A3, and the upper housing 10 has a stepped platform machined on it to make a clearance fit with the electromagnet 7; Invention Point 3: A shim A4 is installed between the retaining ring A3 and the retaining ring B5. The retaining ring B5 is in contact with the electromagnet 7. The electromagnet 7 can be fixed by adjusting the number of shims A4. Invention Point 4: The electromagnet 7 and the socket 8 are connected by a wire to transmit the on / off signal of the electromagnet. A shim B6 is installed between the diaphragm assembly 2 and the suction plate 20. The distance between the suction plate 20 and the electromagnet 7 can be adjusted by adjusting the number of shims B6 to ensure the attraction effect when energized. Invention Point 5: The upper housing 10 is threadedly engaged with the adjusting stud 12, and the adjusting stud 12 is threadedly engaged with the bellows assembly 13. The upper housing 10 and the bellows assembly 13 can be rotated to make them move axially up and down. Invention Point 6: The sliding sleeve 15 has a hole that fits with the bellows assembly 13 with clearance, and the sliding sleeve 15 has a recess that fits with the adjusting stud 12. The sliding sleeve 15 can be adjusted to move up and down axially by rotating the adjusting stud 12. Invention Point 7: The diaphragm assembly 2 is provided with a boss, which is in clearance fit with spring A16 and spring B17. The bellows assembly 13 and the sliding sleeve 15 are provided with a boss, which is in clearance fit with spring A16 and spring B17, to ensure that the extension and retraction movement of spring A16 and spring B17 is axial. Invention Point 8: The diaphragm assembly 2 and the bellows assembly 13 are connected by threads to ensure that their movement trends are consistent; Invention Point 9: The diaphragm assembly 2 is in contact with the spring A16, and a suction plate 20 is installed between the diaphragm assembly 2 and the spring B17, and the three are in contact with each other; Invention Point 10: Before the suction plate 20 is attracted to the electromagnet 7, the diaphragm assembly 2 is controlled by the forces of the bellows assembly 13, spring A16, and spring B17. After the suction plate 20 is attracted to the electromagnet 7, the diaphragm assembly 2 is controlled by the forces of the bellows assembly 13 and spring B17. Invention Point 11: A spring C19 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 have the same movement trend. The position of the diaphragm assembly 2 determines the position of the valve rod 18, the distance between the valve rod 18 and the valve seat 21, and the exhaust volume passing through it.

[0019] Figure 2 This is a schematic diagram of an integrated absolute pressure control mechanism with automatic switching between dual pressure systems, according to an embodiment of the present invention.

[0020] Working principle: The lower housing 1, diaphragm assembly 2, and upper housing 10 are connected together by screws; the upper housing 10 and upper cover 14 are connected together by threads; the interior of the mechanism is a sealed cavity. The lower housing 1 is machined with an air intake pipe to receive the pressure of the cabin exhaust valve control chamber. The lower housing 1 is also machined with an exhaust pipe to release the pressure of the cabin exhaust valve control chamber after adjustment according to the flight altitude and the selected flight pressure regime, so as to achieve the purpose of controlling the pressure of the control chamber, thereby controlling the opening amount of the cabin exhaust valve and achieving the effect of regulating the cabin pressure of the aircraft.

[0021] In this absolute pressure control mechanism, the diaphragm assembly 2 is controlled by the forces of the bellows assembly 13, spring A16, and spring B17. After takeoff, during the free ventilation phase, the combined preload of springs A16 and B17 is insufficient to cause the bellows assembly 13 to expand, resulting in an unlimited flow effect between the valve stem 18 and the valve seat 21. This absolute pressure control mechanism does not restrict the pressure intake or exhaust of the cabin exhaust valve control chamber. Under the pressure difference between the cabin and the control chamber, the cabin exhaust valve opens to its maximum extent, and the aircraft is in a free ventilation state, with the pressure regime trend being the same as that of the atmosphere.

[0022] As the flight altitude increases, atmospheric pressure gradually decreases, and so does the cabin pressure and the pressure in the cabin exhaust valve control chamber. The combined preload of springs A16 and B17 causes the bellows assembly 13 to expand, reducing the distance between the valve stem 18 and the valve seat 21, resulting in flow restriction. This absolute pressure control mechanism restricts the exhaust from the cabin exhaust valve control chamber, causing the pressure in the control chamber to rise. Under the pressure difference between the cabin and the control chamber, the valve opening decreases, and the aircraft cabin pressure begins to exceed atmospheric pressure, initiating the first absolute pressure regime.

[0023] To execute the second absolute pressure system, the aircraft energizes the socket 8. After the suction plate 20 is attracted to the electromagnet 7, the diaphragm assembly 2 is controlled by the forces of the bellows assembly 13 and the spring B17. The preload of the spring B17 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 housing 10. After takeoff, during the free ventilation phase, the preload of spring B17 is insufficient to expand the bellows assembly 13, and the distance between valve stem 18 and valve seat 21 is unlimited. This absolute pressure control mechanism does not restrict the pressure intake or exhaust of the cabin exhaust valve control chamber. Under the pressure difference between the cabin and control chamber, the cabin exhaust valve opens to its maximum extent, and the aircraft is in a free ventilation state, with the pressure regime trending in the same direction as the atmosphere.

[0024] As the flight altitude increases, atmospheric pressure gradually decreases, and so does the cabin pressure and the pressure in the cabin exhaust valve control chamber. The preload of spring B17 causes the bellows assembly 13 to expand, reducing the distance between the valve stem 18 and the valve seat 21, resulting in flow restriction. This absolute pressure control mechanism restricts the exhaust from the cabin exhaust valve control chamber, causing the pressure in the control chamber to rise. Under the pressure difference between the cabin and the control chamber, the valve opening decreases, and the aircraft cabin pressure begins to exceed atmospheric pressure, initiating the second absolute pressure regime.

[0025] Because the aircraft's power supply to socket 8 determines whether it uses the first or second pressure regime, the switching of pressure regimes is not limited by time, location, or scenario, and can be freely switched before or during flight. Furthermore, the mechanism integrates the control elements for both pressure regimes, significantly reducing weight and size.

[0026] Example An integrated absolute pressure control mechanism with automatic switching between dual pressure systems includes a lower housing 1, a diaphragm assembly 2, a retaining ring A3, a gasket A4, a retaining ring B5, a gasket B6, an electromagnet 7, a socket 8, a rubber gasket A9, an upper housing 10, a rubber gasket B11, an adjusting stud 12, a bellows assembly 13, a top cover 14, a sliding sleeve 15, a spring A16, a spring B17, a valve rod 18, a spring C19, a suction plate 20, a valve seat 21, and a sealing plate 22. The diaphragm assembly 2 includes a metal sheet, a diaphragm, and a sleeve. The outer wall of the sleeve in the diaphragm assembly 2 is threadedly connected to the groove of the bellows assembly 13. One end of the spring B17 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. A gasket B6, a suction plate 20, and a spring A16 are sequentially stacked and fixed at the outer step of the metal sheet in the diaphragm assembly 2. One end of the spring A16 rests on the suction plate 20, and when energized, the suction plate 20 can move the spring A16. The guide rod of the bellows assembly 13 passes sequentially through the guide hole of the sliding sleeve 15 and the internal threaded hole of the adjusting stud 12. The other end of the spring A16 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 tightened by a nut. The electromagnet 7 is installed on the upper housing 1. At the step on the 0, electromagnet 7 and socket 8 are connected by wires, socket 8 is connected to upper housing 10 by screws, and rubber gasket A9 is installed in the middle; the retaining ring A3 is installed in the groove of upper housing 10; retaining ring B5 and gasket A4 are stacked between electromagnet 7 and retaining ring A3; adjusting stud 12 is threaded to upper housing 10 and tightened by nut; valve seat 21 is threaded to lower housing 1, and sealing plate 22 is installed between them; valve rod 18 and spring C19 are installed between the inner groove of sleeve in diaphragm assembly 2 and valve seat 21; lower housing 1, diaphragm assembly 2, and upper housing 10 are connected by screws; upper housing 10 and upper cover 14 are connected by screws, and rubber gasket B11 is installed between them.

[0027] In one embodiment of the present invention, the diaphragm material is specifically a composite of silicone rubber compound GX2-50 and brocade twill 511; In one embodiment of the present invention, the spring C19 is used for resetting, and the spring force of the spring C19 should be as small as possible in terms of preload and stiffness while satisfying the resetting conditions.

[0028] In one embodiment of the present invention, the combined preload of springs A16 and B17, in conjunction with the bellows assembly 13, should meet the pressure adjustment requirements.

[0029] In one embodiment of the present invention, the preload of the spring B17, in conjunction with the bellows assembly 13, should meet the pressure adjustment requirements.

[0030] In one embodiment of the present invention, the number of gaskets B6 should ensure that the suction plate 20 can be normally attracted when the electromagnet 7 is energized.

[0031] In one embodiment of the present invention, the number of sealing sheets 22 should meet the pressure regulation requirements.

[0032] In one 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 machinability.

[0033] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. 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 should not be interpreted in an idealized or overly formal sense unless defined as herein. The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the present invention. Within the spirit and principles of the present invention, any person skilled in the art may use the disclosed technical content to make changes or modifications to create equivalent embodiments applicable to other fields. However, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention, any modifications, equivalent substitutions, improvements, etc., should be included within the protection scope of the present invention.

Claims

1. An integrated absolute pressure control mechanism with automatic switching between dual pressure systems, characterized in that, Includes a lower housing, diaphragm assembly, retaining ring A, gasket A, retaining ring B, gasket B, electromagnet, socket, rubber gasket A, upper housing, rubber gasket B, adjusting stud, bellows assembly, top cover, sliding sleeve, spring A, spring B, valve rod, spring C, suction plate, valve seat, and sealing plate; the diaphragm assembly includes a metal sheet, diaphragm, and sleeve; In the diaphragm assembly, the outer wall of the sleeve is threadedly connected to the groove of the bellows assembly. One end of spring B is fixed to the inner step of the metal sheet in the diaphragm assembly, and the other end is fixed to the step on the bellows assembly. A gasket B, a suction plate, and spring A are sequentially stacked and fixed at the outer step of the metal sheet in the diaphragm assembly. One end of spring A rests on the suction plate, and when energized, the suction plate can move spring A. The guide rod of the bellows assembly passes sequentially through the guide hole of the sliding sleeve and the internal threaded hole of the adjusting stud. The other end of spring A is fixed to the step of the sliding sleeve, and the lower end of the adjusting stud contacts 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 housing, the electromagnet is connected to the socket by a wire, the socket is connected to the upper housing by a screw, and a rubber gasket A is installed in the middle; the retaining ring A is installed in the groove of the upper housing; retaining ring B and gasket A are stacked and installed in sequence between the electromagnet and retaining ring A; the adjusting stud is connected to the upper housing by a thread and tightened by a nut; the valve seat is connected to the lower housing by a thread, and a sealing plate is installed between the two; a valve rod and spring C are installed in sequence between the inner groove of the sleeve and the valve seat in the diaphragm assembly; the lower housing and diaphragm assembly 、 The upper housing is connected by screws; the upper housing and the upper cover are connected by screws, and a rubber gasket B is installed between them.

2. The mechanism as described in claim 1, characterized in that, The diaphragm material is specifically a composite of silicone rubber compound GX2-50 and brocade twill fabric 511.

3. The mechanism as described in claim 2, characterized in that, The spring C is used for reset. Under the condition that the reset condition is met, the smaller the preload and stiffness of the spring C, the better.

4. The mechanism as described in claim 3, characterized in that, The combined preload of springs A and B, in conjunction with the bellows assembly, should meet the pressure regulation requirements.

5. The mechanism as described in claim 4, characterized in that, The preload of spring B, in conjunction with the bellows assembly, should meet the pressure regulation requirements.

6. The mechanism as described in claim 5, characterized in that, The number of shims B should be sufficient to ensure that the attracting plate can be properly attracted when the electromagnet is energized.

7. The mechanism as described in claim 6, characterized in that, The number of sealing plates should meet the pressure regulation requirements.

8. The mechanism as described in 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 machinability.

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