Double-flap check valve for aircraft, double-flap check valve opening and closing system, and opening and closing method

Abstract

This invention discloses a double-disc one-way valve for aircraft, a double-disc one-way valve opening and closing system, and an opening and closing method, including a valve ring, a crossbeam, a first movable valve disc, and a second movable valve disc; the first movable valve disc, the second movable valve disc, and the first side of the crossbeam together form a complete and smoothly transitioning first action surface; the second side of the crossbeam is provided with an opening and closing compensation device, which includes an electromagnetic action part, which is hinged to the first movable valve disc and the second movable valve disc via a connecting rod; the electromagnetic action part adjusts its axial movement stroke according to the pressure difference and pressure drop between the two sides of the valve disc to assist the first movable valve disc and the second movable valve disc in opening and closing according to a set tilt angle and response time; this invention can improve the impact load and vibration of the valve body caused by airflow, ensure the valve body to operate normally and safely for a long time, and assist the valve disc to act quickly and accurately when the pressure difference between the two sides of the valve body exceeds the standard, ensuring that the double-disc one-way valve can open and close with a preset position accuracy within a preset response time.

Description

Technical Field

[0001] This invention belongs to the technical field of aviation one-way valves, specifically relating to aircraft double-disc one-way valves, double-disc one-way valve opening and closing systems, and opening and closing methods. Background Technology

[0002] The dual-disc check valve is a crucial control component installed inside the airborne ventilation system to regulate airflow and control the flow rate. Existing airborne dual-disc check valves require a separate mounting bracket on a crossbeam spanning the center of the valve body to accommodate the rotating shaft that powers the valve disc. Bolts are then used to secure the bracket at the airflow-facing end of the crossbeam. This results in an uneven surface on the airflow-facing side of the crossbeam, causing greater impact loads on the valve body. Furthermore, prolonged exposure to airflow vibrations can lead to loosening and detachment of bolts and other connecting parts. Loose bolts can impair the valve's opening mechanism, and could even fall into the piping, posing a serious safety hazard to the aircraft.

[0003] Meanwhile, existing double-disc check valves control their opening and closing through the pressure difference across the valve disc. However, in actual use, the airflow pressure fluctuates, and pressure drops occur during airflow. Therefore, the actual pressure difference acting on both sides of the double-disc check valve will deviate from the theoretical pressure difference. When the deviation is large, it will affect the valve disc's response speed and opening / closing position accuracy, thus causing the double-disc check valve to fail to perform fast and accurate actions within the required response time range and opening / closing position.

[0004] Therefore, in view of the above-mentioned problems of existing airborne double-lobe check valves, the present invention discloses an aircraft double-lobe check valve, a double-lobe check valve opening and closing system, and an opening and closing method. Summary of the Invention

[0005] This invention discloses a double-disc check valve for aircraft, a double-disc check valve opening and closing system, and an opening and closing method. It can effectively improve the impact load and vibration of the valve body caused by airflow, thereby ensuring the normal and safe operation of the valve body for a long time. Furthermore, when the pressure difference on both sides of the valve body exceeds the standard, it assists the valve disc to perform rapid and accurate action, ensuring that the double-disc check valve can open and close with a preset position accuracy within a preset response time.

[0006] This invention is achieved through the following technical solution:

[0007] A dual-disc one-way valve for aircraft includes a valve ring. A crossbeam is integrally formed at the center of the valve ring along the diametrical direction. A first movable valve disc and a second movable valve disc are symmetrically rotatably arranged on both sides of the crossbeam. The first side of the first movable valve disc, the first side of the second movable valve disc, and the first side of the crossbeam form a complete and smoothly transitioning first action surface. An opening and closing compensation device is provided at the center of the second side of the crossbeam. The opening and closing compensation device includes at least one set of electromagnetic action parts that move along the central axis of the valve ring. The electromagnetic action parts are hinged to the second side of the first movable valve disc and the second movable valve disc through at least one set of connecting rods. The electromagnetic action parts adjust their axial movement stroke according to the pressure difference and pressure drop between the two sides of the first and second movable valve discs to assist the first and second movable valve discs in opening and closing according to a set tilt angle and a set response time.

[0008] The dual-disc check valve is installed in the airborne ventilation line. When the air pressure on the first side of the crossbeam is greater than that on the second side, the pressure difference causes the first and second movable valve discs to rotate towards the second side, thus opening the entire valve body. When the air pressure on the second side is greater than that on the first side, the reverse pressure difference causes the first and second movable valve discs to rotate towards the first side, thus closing the valve body. By controlling the air pressure on the first and second sides, the one-way opening and closing of the first and second movable valve discs, as well as their opening degree, can be controlled.

[0009] In actual use, the airflow in the ventilation pipeline inevitably generates pressure drop and pressure fluctuations. This causes the first and second movable valve discs to not experience the theoretically preset pressure difference, resulting in them not opening and closing according to the theoretically set opening and closing angles and response times. At this point, the electromagnetic actuator in the opening and closing compensation device adjusts its axial movement stroke according to the pressure difference and pressure drop to assist the first and second movable valve discs in opening and closing according to the set tilt angle and response time. This ensures that the entire double-disc check valve can respond quickly to opening and closing within 0.2 seconds. Simultaneously, the angle difference between the fully opened tilt angle of the first and second movable valve discs and the set tilt angle is less than or equal to 0.5°, thus guaranteeing the high precision and rapid response of the entire double-disc check valve in the ventilation pipeline. Meanwhile, the first side of the crossbeam, the first side of the first movable valve disc, and the first side of the second movable valve disc together form a smooth transition first working surface. The crossbeam at the center of the valve ring is integrated, eliminating the structure of fixing the crossbeam to the valve ring with bolts in the traditional double-disc check valve, as well as the structure of fixing the valve disc with bolts through the first side of the crossbeam. This allows the first side of the valve ring to receive the airflow with a complete and smooth transition first working surface, thereby effectively guiding the airflow and significantly reducing the vibration of the entire valve body. This effectively avoids the problem of bolts loosening and falling off in the traditional double-disc check valve under long-term vibration.

[0010] To better realize the present invention, the opening and closing compensation device further includes a first electromagnetic part, a second electromagnetic part, a permanent magnet slider, a ceramic central shaft, and a connecting rod. The ceramic central shaft is coaxial with the central axis of the valve ring and is disposed on the second side of the crossbeam. The permanent magnet slider is slidably sleeved on the ceramic central shaft. The two sides of the permanent magnet slider are respectively hinged to the second side of the first movable valve disc and the second side of the second movable valve disc through the connecting rod. The first electromagnetic part and the second electromagnetic part are respectively disposed on both sides of the permanent magnet slider along the central axis. The first electromagnetic part and the second electromagnetic part are connected to the control device.

[0011] To better realize the present invention, further, damping and vibration reduction devices are provided on both the side of the permanent magnet slider near the first electromagnetic part and the side near the second electromagnetic part. The damping and vibration reduction devices include at least one set of circumferential damping and vibration reduction parts and at least one set of axial damping and vibration reduction parts.

[0012] To better realize the present invention, the permanent magnet slider is further provided with circumferential grooves and axial grooves symmetrically arranged on both sides. The damping and vibration reduction device includes a slip ring. The side of the slip ring near the circumferential groove is slidably connected to the circumferential groove. A circumferential damping spring connected to the slip ring is provided inside the circumferential groove. An axial slider is provided on the side of the slip ring near the axial cavity. The axial slider is axially slidably connected to the axial cavity. An axial damping spring is provided on both sides of the axial slider inside the axial cavity. The axial cavities on both sides of the axial slider are filled with damping fluid.

[0013] To better realize the present invention, at least one side of the crossbeam is provided with a noise-absorbing component, and the noise-absorbing component is provided with a fluid passage corresponding to the first movable valve and the second movable valve. The shape and distribution position of the fluid passage are adapted to the fluid distribution in the pipeline after the fluid passes through the first movable valve and the second movable valve.

[0014] To better realize the present invention, the first movable valve disc and the second movable valve disc have unequal weights, and the offset between the valve disc center of mass of the first movable valve disc and the second movable valve disc relative to the valve ring center of mass is less than or equal to 2mm.

[0015] To better realize the present invention, the limiting deflection angle of the first movable valve disc and the second movable valve disc relative to the crossbeam is 75±2°; the surface roughness of the first movable valve disc and the second movable valve disc is less than or equal to 0.2μm.

[0016] To better realize the present invention, a U-shaped bracket is integrally formed on the second side of the crossbeam, and a rotating shaft is rotatably provided on the U-shaped bracket. The first movable valve flap and the second movable valve flap are symmetrically rotated and sleeved on the rotating shaft through a damping bushing. A pre-tightening member is provided at one end of the rotating shaft to adjust the pre-tightening force of the rotating shaft.

[0017] An aircraft-grade double-disc check valve opening and closing system, based on an aircraft-grade double-disc check valve, includes a first pressure sensing system disposed on a first side of the double-disc check valve, a second pressure sensing system disposed on a second side of the double-disc check valve, and a control module. The first pressure sensing system is used to detect the pressure and pressure drop on the first side of the double-disc check valve, and the second pressure sensing system is used to detect the pressure and pressure drop on the second side of the double-disc check valve. The control module is used to calculate the pressure difference across the double-disc check valve and control the direction and magnitude of the electromagnetic force in the electromagnetic actuator according to the pressure difference, thereby controlling the movement direction and axial stroke of the electromagnetic actuator. The axial movement of the electromagnetic actuator assists the first and second movable valve discs to open and close according to a set tilt angle and a set response time.

[0018] A method for opening and closing a dual-lobe check valve for aircraft, based on a dual-lobe check valve opening and closing system, includes the following steps:

[0019] Step 1: Detect the linear pressure drop on the first side of the double-disc check valve using the first pressure sensing system, and calculate the first pressure acting on the first side of the double-disc check valve using the calibrated pressure and linear pressure drop on the first side; Detect the linear pressure drop on the second side of the double-disc check valve using the second pressure sensing system, and calculate the second pressure acting on the second side of the double-disc check valve using the calibrated pressure and linear pressure drop on the second side.

[0020] Step 2: Calculate the actual pressure difference between the first pressure and the second pressure using the control module to determine the opening direction of the double-disc check valve, and calculate the difference between the actual pressure difference and the calibrated control pressure difference; if the difference is less than or equal to the calibrated pressure difference error, proceed to step 2; if the difference is greater than the calibrated pressure difference error, proceed to step 3.

[0021] Step 3: The control module de-energizes the electromagnetic actuator in the opening and closing compensation device, so that the first and second movable valve discs open and close autonomously under the action of the actual pressure difference.

[0022] Step 4: The control module controls the electromagnetic actuator in the opening and closing compensation device to be energized, and calculates the electromagnetic force and axial travel of the electromagnetic actuator based on the difference value. The electromagnetic force is used to compensate for the pressure difference caused by the difference value, and the axial travel assists the first and second movable valve discs to open and close with a set tilt angle and a set response time.

[0023] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0024] (1) The present invention integrates the valve ring, crossbeam and U-shaped bracket into a single form, which not only improves the overall strength of the valve body, but also avoids the need to insert bolts through the first section of the crossbeam, thereby ensuring that the first side of the crossbeam is a smooth transition guide surface. The guide surface guides and diverts the airflow on the first side smoothly, which not only reduces the impact load of the airflow on the valve body, but also ensures that the impact load and torque on the first and second movable flaps are within a suitable range, thereby ensuring that the first and second movable flaps can open and close smoothly and in a timely manner. Since bolts and other connecting parts are eliminated, the situation of bolts loosening and falling off in the vibration environment is also avoided.

[0025] (2) The present invention provides an opening and closing compensation device coaxially on one side of the double-lobe one-way valve. By monitoring the difference between the actual pressure difference and pressure drop on both sides of the valve lobe and the theoretical pressure difference and pressure drop, the electromagnetic action part in the opening and closing compensation device applies a magnetic force according to the difference value to assist in driving the first movable valve lobe and the second movable valve lobe to rotate quickly and accurately to the preset opening and closing position within a preset response time. Thus, the rapid and accurate opening and closing operation of the double-lobe one-way valve is guaranteed without the need for a large adjustment of the control air pressure. Attached Figure Description

[0026] Figure 1 A schematic diagram of a double-disc check valve for aircraft.

[0027] Figure 2 This is a schematic diagram of the opening and closing compensation device;

[0028] Figure 3 This is a schematic diagram of the structure of a damping vibration reduction device;

[0029] Figure 4 This is a schematic diagram showing the connection between the U-shaped bracket and the crossbeam;

[0030] Figure 5 This is a schematic diagram of the beam installation.

[0031] Figure 6 This is a schematic diagram of the shaft installation.

[0032] Figure 7 This is a schematic diagram of an existing double-lobe check valve.

[0033] Wherein: 1-valve ring; 2-crossbeam; 3-first movable valve disc; 4-second movable valve disc; 5-opening and closing compensation device; 6-silencing component; 7-U-shaped bracket; 8-rotating shaft; 51-first electromagnetic part; 52-second electromagnetic part; 53-permanent magnet slider; 54-ceramic central shaft; 55-connecting rod; 56-damping vibration reduction device; 561-slip ring; 562-circumferential damping spring; 563-axial slider; 564-axial damping spring. Detailed Implementation

[0034] Example 1:

[0035] This embodiment provides a dual-disc check valve for aircraft, such as... Figures 1-6 As shown, the device includes a valve ring 1, with a crossbeam 2 integrally formed at the center of the valve ring 1 along the diameter direction. A first movable valve disc 3 and a second movable valve disc 4 are symmetrically rotated on both sides of the crossbeam 2. The first side of the first movable valve disc 3, the first side of the second movable valve disc 4, and the first side of the crossbeam 2 form a complete and smoothly transitioning first action surface. An opening / closing compensation device 5 is provided at the center of the second side of the crossbeam 2. The opening / closing compensation device 5 includes at least one set of electromagnetic action parts that move along the central axis of the valve ring 1. The electromagnetic action parts are hinged to the second side of the first movable valve disc 3 and the second movable valve disc 4 via at least one set of connecting rods. The electromagnetic action parts adjust their axial movement stroke according to the pressure difference and pressure drop between the two sides of the first movable valve disc 3 and the second movable valve disc 4 to assist the first movable valve disc 3 and the second movable valve disc 4 in opening and closing according to a set tilt angle and a set response time.

[0036] like Figure 7 As shown, in a traditional double-disc check valve, a mounting bracket is separately installed on the second side of the crossbeam 2 to install the rotating shaft 8, and several bolts are inserted through the first side of the crossbeam 2. The mounting bracket is fixed by the bolts, thereby achieving the installation of the rotating shaft 8. This leads to two problems. First, the bolts and other connecting parts are in direct contact with the airflow and are subjected to vibration for a long time, causing the bolts to loosen and fall into the airflow pipeline, posing a significant safety hazard to aircraft flight. Second, because the bolts are inserted through the first side of the crossbeam 2, the first side of the crossbeam 2 has an uneven frontal surface, which will disrupt the airflow on the first side of the valve body, thus affecting the opening of the valve disc. After prolonged use, this will lead to obstructed valve opening and a longer response time.

[0037] In this embodiment, when the pressure on the second side is greater than the pressure on the first side, the first movable valve disc 3 and the second movable valve disc 4 rotate toward the first side to a fully closed state under the action of the pressure difference. At this time, the first side of the first movable valve disc 3, the first side of the second movable valve disc 4, and the first side of the crossbeam 2 form a smoothly transitioning first working surface. This smoothly transitioning first working surface replaces the bolt holes and bolts on the middle beam of the traditional double-disc check valve, effectively reducing the vibration of the double-disc check valve under the action of airflow on the first side. Furthermore, because there are no bolts or other connecting parts on the first side, the loosening and falling off of bolts under vibration is avoided. Moreover, the first working surface guides and diverts the airflow from the first side, allowing the airflow from the first side to act more evenly on the first movable valve disc 3 and the second movable valve disc 4, ensuring that the double-disc check valve can open smoothly and quickly.

[0038] like Figure 5 , Figure 6 As shown, the crossbeam 2 and valve ring 1 are integrally formed, ensuring the strength of the main valve body structure. Secondly, a rotating shaft 8 is directly rotatably mounted on the second side of the crossbeam 2, eliminating the bolts on the first side of the crossbeam 2 used to fix the rotating shaft 8. Instead, a fully transitional guide surface is provided on the first side of the crossbeam 2. This guide surface smoothly guides the airflow from the first side to the first movable valve disc 3 and the second movable valve disc 4, improving the overall stress distribution of the valve body and effectively reducing vibration. Furthermore, when the first movable valve disc 3 and the second movable valve disc 4 are fully closed, the first side of the first movable valve disc 3, the first side of the second movable valve disc 4, and the first side of the crossbeam 2 (i.e., the guide surface) form a smoothly transitional first working surface. Because the connecting bolts are directly eliminated, the problem of bolts loosening and falling off due to vibration is completely avoided. Furthermore, the airflow on the first side is guided and diverted by the guide surface, so that the airflow is smoothly and evenly diverted and flows to the first movable valve 3 and the second movable valve 4 respectively, thereby ensuring that the first movable valve 3 and the second movable valve 4 will not experience any problems such as obstruction, jamming, or delayed opening during long-term operation.

[0039] Furthermore, an opening / closing compensation device 5 is installed on the second side of the double-disc check valve, coaxially with the central axis of the valve ring 1. The function of the opening / closing compensation device 5 is to assist the first movable valve disc 3 and the second movable valve disc 4 in accurately and quickly opening and closing at a predetermined angle and with a predetermined response time when the pressure difference across the double-disc check valve exceeds the limit or pressure drop occurs. The magnetic force generated by the electromagnetic actuator in the opening / closing compensation device 5 compensates for the pressure difference, thereby assisting the first movable valve disc 3 and the second movable valve disc 4 in moving to a predetermined position within a predetermined response time. By setting up the opening / closing compensation device 5 to compensate for the opening and closing positions of the first movable valve disc 3 and the second movable valve disc 4 caused by pressure difference fluctuations and pressure drop, the double-disc check valve can be opened and closed efficiently and accurately without requiring significant adjustment of the pressure on both sides.

[0040] Example 2:

[0041] This embodiment discloses a dual-disc check valve for aircraft, which is an optimization based on Embodiment 1, such as... Figure 2As shown, the opening and closing compensation device 5 includes a first electromagnetic part 51, a second electromagnetic part 52, a permanent magnet slider 53, a ceramic central shaft 54, and a connecting rod 55. The ceramic central shaft 54 ​​is coaxial with the central axis of the valve ring 1 and is disposed on the second side of the crossbeam 2. The permanent magnet slider 53 is slidably sleeved on the ceramic central shaft 54. The two sides of the permanent magnet slider 53 are respectively hinged to the second side of the first movable valve disc 3 and the second side of the second movable valve disc 4 through the connecting rod 55. The first electromagnetic part 51 and the second electromagnetic part 52 are respectively disposed on both sides of the permanent magnet slider 53 along the central axis. The first electromagnetic part 51 and the second electromagnetic part 52 are connected to the control device.

[0042] The inner hole of the permanent magnet slider 53 is slidably fitted with the ceramic central shaft 54, and the roughness of the inner hole of the permanent magnet slider 53 is less than or equal to 0.05 mm, which significantly reduces its friction when the permanent magnet slider 53 slides smoothly along the ceramic central shaft 54. By controlling the direction and magnitude of the current passing through the coils of the first electromagnetic part 51 and the second electromagnetic part 52, the magnetism and magnetic force of the first electromagnetic part 51 and the second electromagnetic part 52 are controlled, and a magnetic force is applied to the permanent magnet slider 53 through the cooperation of the first electromagnetic part 51 and the second electromagnetic part 52. When it is necessary to assist the opening of the first movable valve disc 3 and the second movable valve disc 4, the magnetic force points from the first side to the second side, and the magnitude of the magnetic force is calculated based on the pressure drop loss and the difference between the actual pressure difference and the calibrated pressure difference on both sides of the valve body; when it is necessary to assist the closing of the first movable valve disc 3 and the second movable valve disc 4, the magnetic force points from the second side to the first side, and the magnitude of the magnetic force is calculated based on the pressure drop loss and the difference between the actual pressure difference and the calibrated pressure difference on both sides of the valve body. When the permanent magnet slider 53 slides under the action of magnetic force, it drives the first movable valve disc 3 and the second movable valve disc 4 to rotate and open or close through the connecting rod 55.

[0043] Furthermore, damping and vibration reduction devices 56 are provided on both the side of the permanent magnet slider 53 closest to the first electromagnetic part 51 and the side closest to the second electromagnetic part 52. Each damping and vibration reduction device 56 includes at least one set of circumferential damping and vibration reduction parts and at least one set of axial damping and vibration reduction parts. The damping and vibration reduction devices 56 are used to reduce vibrations during the sliding process of the permanent magnet slider 53 and during the rotation of the first movable valve disc 3 and the second movable valve disc 4. Under the action of airflow, the permanent magnet slider 53, the first movable valve disc 3, and the second movable valve disc 4 are subjected to both axial and circumferential vibrations. The circumferential damping and vibration reduction parts buffer the circumferential vibrations, and the axial damping and vibration reduction parts buffer the axial vibrations.

[0044] Furthermore, such as Figure 3As shown, the permanent magnet slider 53 has symmetrical circumferential and axial grooves on both sides. The damping and vibration reduction device 56 includes a slip ring 561. The side of the slip ring 561 near the circumferential groove is slidably connected to the circumferential groove. A circumferential damping spring 562 connected to the slip ring 561 is provided inside the circumferential groove. An axial slider 563 is provided on the side of the slip ring 561 near the axial cavity. The axial slider 563 is axially slidably connected to the axial cavity. An axial damping spring 564 is provided on both sides of the axial slider 563 inside the axial cavity. The axial cavities on both sides of the axial slider 563 are filled with damping fluid.

[0045] Under circumferential vibration load, the slip ring 561 slides circumferentially relative to the circumferential groove. At this time, the circumferential damping spring 562 located inside the circumferential groove is compressed, and the elastic deformation of the circumferential damping spring 562 buffers the circumferential vibration load. Under axial vibration load, the axial slider 563 slides axially inside the axial cavity, which in turn causes the axial damping springs 564 on both sides of the axial slider 563 to undergo elastic deformation and squeeze the damping fluid, causing the damping fluid to flow in the cavities on both sides of the axial slider 563. Through the cooperation of the elastic deformation of the axial damping springs 564 and the flow of the damping fluid, the axial vibration load is buffered.

[0046] The rest of this embodiment is the same as that of Embodiment 1, so it will not be described again.

[0047] Example 3:

[0048] This embodiment discloses a dual-disc one-way valve for aircraft, which is an optimization based on Embodiment 1 or 2, such as... Figure 1 As shown, at least one side of the crossbeam 2 is provided with a noise-absorbing component 6. The noise-absorbing component 6 is provided with a fluid passage corresponding to the first movable valve 3 and the second movable valve 4. The shape and distribution position of the fluid passage are adapted to the fluid distribution in the pipeline after the fluid passes through the first movable valve 3 and the second movable valve 4.

[0049] Since the thickness of the silencing component 6 is much smaller than the length of the pipe and the thickness of the valve ring 1, the pressure drop of the fluid passing through the fluid passage on the silencing component 6 can be ignored. Corresponding to the first movable valve disc 3 and the second movable valve disc 4, two fluid passages are centrally symmetrically arranged on the silencing component 6. After the airflow passes through the fluid passages, it enters the pipe with a larger diameter to complete the pulsation reduction.

[0050] The rest of this embodiment is the same as that of embodiment 1 or 2, so it will not be described again.

[0051] Example 4:

[0052] This embodiment discloses a dual-disc one-way valve for aircraft, optimized based on any one of embodiments 1-3. The first movable valve disc 3 and the second movable valve disc 4 have unequal weights, and the offset between the center of mass of the first movable valve disc 3 and the second movable valve disc 4 relative to the center of mass of the valve ring 1 is less than or equal to 2 mm. The limiting deflection angle of the first movable valve disc 3 and the second movable valve disc 4 relative to the crossbeam 2 is 75±2°; the surface roughness of the first movable valve disc 3 and the second movable valve disc 4 is less than or equal to 0.2 μm.

[0053] Due to the centroid shift between the first movable valve disc 3 and the second movable valve disc 4, the positions of the two fluid passages on the silencing component 6 also shift accordingly, so that the shape and distribution of the fluid passages are adapted to the fluid distribution in the pipeline after the fluid passes through the first movable valve disc 3 and the second movable valve disc 4.

[0054] Based on the torque balance equation, an unequal weight model of the first movable valve disc 3 and the second movable valve disc 4 is established. The preferred weight of the first movable valve disc 3 is 30g, and the weight of the second movable valve disc 4 is 25g. Furthermore, the offset between the center of mass of the first movable valve disc 3 and the center of mass of the second movable valve disc 4 relative to the center of mass of the valve ring 1 is less than or equal to 2mm. This ensures that during the opening process of the first movable valve disc 3 and the second movable valve disc 4 at a preset angle, their torque remains within a preset torque range. Ultimately, this ensures that the first movable valve disc 3 and the second movable valve disc 4 can respond and open rapidly within 0.1s, and reduces the impact load of the airflow on the first movable valve disc 3 and the second movable valve disc 4.

[0055] Furthermore, the limit deflection angle of the first movable valve disc 3 and the second movable valve disc 4 relative to the crossbeam 2 is 75±2°, which can ensure the airflow through the valve ring 1, while also reducing the impact load on the first movable valve disc 3 and the second movable valve disc 4.

[0056] Furthermore, the surface roughness of the first movable valve disc 3 and the second movable valve disc 4 is less than or equal to 0.2 μm. In the closed state, this ensures the airtightness of the contact between the first movable valve disc 3, the second movable valve disc 4 and the inner side of the valve ring 1, preventing airflow leakage. During the opening process, this ensures that the first movable valve disc 3 and the second movable valve disc 4 can open smoothly, avoiding obstruction and jamming during the opening process.

[0057] The rest of this embodiment is the same as any one of embodiments 1-3, so it will not be described again.

[0058] Example 5:

[0059] This embodiment discloses a dual-disc check valve for aircraft, which is optimized based on any one of embodiments 1-4, such as... Figures 4-6As shown, a U-shaped bracket 7 is integrally formed on the second side of the crossbeam 2, and a rotating shaft 8 is rotatably mounted on the U-shaped bracket 7. The first movable valve disc 3 and the second movable valve disc 4 are symmetrically mounted on the rotating shaft 8 through damping bushings. A pre-tightening member is provided at one end of the rotating shaft 8 to adjust the pre-tightening force of the rotating shaft 8.

[0060] like Figure 6 As shown, a U-shaped bracket 7 is integrally formed on the second side of the crossbeam 2, and the rotating shaft 8 is rotatably mounted on the U-shaped bracket 7. The U-shaped bracket 7 is integrally formed on the second side of the crossbeam 2, thus eliminating the need for bolts used to fix the U-shaped bracket 7 in traditional structures, ensuring that the first side of the crossbeam 2 can form a smooth transition guide surface, and improving the overall strength of the crossbeam 2 and the U-shaped bracket 7.

[0061] Furthermore, a preload is provided at one end of the rotating shaft 8, and an external thread is provided at one end of the rotating shaft 8. The preload includes a locking nut that engages with the external thread. By adjusting the tightness of the locking nut, the preload force on the rotating shaft 8 is made to be approximately 5 N·m.

[0062] The rest of the content of this embodiment is the same as any one of embodiments 1-4, so it will not be repeated here.

[0063] Example 6:

[0064] This embodiment discloses an aircraft double-disc check valve opening and closing system, based on an aircraft double-disc check valve. It includes a first pressure sensing system disposed on the first side of the double-disc check valve, a second pressure sensing system disposed on the second side of the double-disc check valve, and a control module. The first pressure sensing system is used to detect the pressure and pressure drop on the first side of the double-disc check valve, and the second pressure sensing system is used to detect the pressure and pressure drop on the second side of the double-disc check valve. The control module is used to calculate the pressure difference across the double-disc check valve and control the direction and magnitude of the electromagnetic force in the electromagnetic actuator based on the pressure difference, thereby controlling the movement direction and axial stroke of the electromagnetic actuator. The axial movement of the electromagnetic actuator assists the first movable valve disc 3 and the second movable valve disc 4 to open and close according to a set tilt angle and a set response time.

[0065] A method for opening and closing a dual-lobe check valve for aircraft, based on a dual-lobe check valve opening and closing system, includes the following steps:

[0066] Step 1: Detect the linear pressure drop on the first side of the double-disc check valve using the first pressure sensing system, and calculate the first pressure acting on the first side of the double-disc check valve using the calibrated pressure and linear pressure drop on the first side; Detect the linear pressure drop on the second side of the double-disc check valve using the second pressure sensing system, and calculate the second pressure acting on the second side of the double-disc check valve using the calibrated pressure and linear pressure drop on the second side.

[0067] Step 2: Calculate the actual pressure difference between the first pressure and the second pressure through the control module to determine the opening direction of the double-disc check valve, and calculate the difference between the actual pressure difference and the calibrated control pressure difference; if the difference is less than or equal to the calibrated pressure difference error, proceed to step 3; if the difference is greater than the calibrated pressure difference error, proceed to step 4.

[0068] Step 3: The control module de-energizes the electromagnetic actuator in the opening and closing compensation device 5, so that the first movable valve disc 3 and the second movable valve disc 4 open and close autonomously under the action of the actual pressure difference.

[0069] Step 4: The control module controls the electromagnetic actuator in the opening and closing compensation device 5 to be energized, and calculates the electromagnetic force and axial travel of the electromagnetic actuator based on the difference value. The electromagnetic force compensates for the pressure difference caused by the difference value, and the axial travel assists the first movable valve disc 3 and the second movable valve disc 4 to open and close with a set tilt angle and a set response time.

[0070] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A dual-disc check valve for aircraft, comprising a valve ring (1), characterized in that, A crossbeam (2) is integrally provided at the center of the valve ring (1) along the diameter direction. A first movable valve disc (3) and a second movable valve disc (4) are symmetrically rotated on both sides of the crossbeam (2). The first side of the first movable valve disc (3), the first side of the second movable valve disc (4), and the first side of the crossbeam (2) form a complete and smooth transition first working surface. An opening and closing compensation device (5) is provided at the center of the second side of the crossbeam (2). The opening and closing compensation device (5) includes at least one set of electromagnetic action parts that move along the central axis of the valve ring (1). The electromagnetic action parts are hinged to the second side of the first movable valve disc (3) and the second side of the second movable valve disc (4) through at least one set of connecting rods. The electromagnetic action parts adjust their axial movement stroke according to the pressure difference and pressure drop between the two sides of the first movable valve disc (3) and the second movable valve disc (4) to assist in the adjustment of the valve ring (1). The first movable valve disc (3) and the second movable valve disc (4) open and close according to the set tilt angle and the set response time. The opening and closing compensation device (5) includes a first electromagnetic part (51), a second electromagnetic part (52), a permanent magnet slider (53), a ceramic central shaft (54), and a connecting rod (55). The ceramic central shaft (54) is coaxial with the central axis of the valve ring (1) and is set on the second side of the crossbeam (2). The permanent magnet slider (53) is slidably sleeved on the ceramic central shaft (54). The two sides of the permanent magnet slider (53) are hinged to the second side of the first movable valve disc (3) and the second side of the second movable valve disc (4) respectively through the connecting rod (55). The permanent magnet slider (53) is provided with a first electromagnetic part (51) and a second electromagnetic part (52) on both sides along the central axis. The first electromagnetic part (51) and the second electromagnetic part (52) are connected to the control device.

2. The dual-disc check valve for aircraft according to claim 1, characterized in that, The permanent magnet slider (53) is provided with damping and vibration reduction devices (56) on both the side near the first electromagnetic part (51) and the side near the second electromagnetic part (52). The damping and vibration reduction devices (56) include at least one set of circumferential damping and vibration reduction parts and at least one set of axial damping and vibration reduction parts.

3. The dual-disc check valve for aircraft according to claim 2, characterized in that, The permanent magnet slider (53) is symmetrically provided with circumferential grooves and axial grooves on both sides. The damping and vibration reduction device (56) includes a slip ring (561). The slip ring (561) is slidably connected to the circumferential groove on the side near the circumferential groove. A circumferential damping spring (562) connected to the slip ring (561) is provided inside the circumferential groove. An axial slider (563) is provided on the side of the slip ring (561) near the axial cavity. The axial slider (563) is axially slidably connected to the axial cavity. An axial damping spring (564) is provided on both sides of the axial slider (563) inside the axial cavity. The axial cavities on both sides of the axial slider (563) are filled with damping fluid.

4. A dual-disc check valve for aircraft according to any one of claims 1-3, characterized in that, At least one side of the crossbeam (2) is provided with a noise-absorbing component (6), and the noise-absorbing component (6) is provided with a fluid passage corresponding to the first movable valve disc (3) and the second movable valve disc (4). The shape and distribution position of the fluid passage are adapted to the fluid distribution in the pipeline after the fluid passes through the first movable valve disc (3) and the second movable valve disc (4).

5. A dual-disc check valve for aircraft according to any one of claims 1-3, characterized in that, The first movable valve disc (3) and the second movable valve disc (4) have different weights. The offset between the center of mass of the first movable valve disc (3) and the center of mass of the second movable valve disc (4) relative to the center of mass of the valve ring (1) is less than or equal to 2 mm.

6. A dual-disc check valve for aircraft according to claim 5, characterized in that, The limit deflection angle of the first movable valve disc (3) and the second movable valve disc (4) relative to the crossbeam (2) is 75±2°; the surface roughness of the first movable valve disc (3) and the second movable valve disc (4) is less than or equal to 0.2μm.

7. A dual-disc check valve for aircraft according to any one of claims 1-3, characterized in that, A U-shaped bracket (7) is integrally formed on the second side of the crossbeam (2). A rotating shaft (8) is rotatably mounted on the U-shaped bracket (7). The first movable valve disc (3) and the second movable valve disc (4) are symmetrically mounted on the rotating shaft (8) through a damping bushing. A pre-tightening member is provided at one end of the rotating shaft (8) to adjust the pre-tightening force of the rotating shaft (8).

8. An aircraft dual-disc check valve opening and closing system, implemented based on the aircraft dual-disc check valve according to any one of claims 1-7, characterized in that, The system includes a first pressure sensing system installed on the first side of the double-disc check valve, a second pressure sensing system installed on the second side of the double-disc check valve, and a control module. The first pressure sensing system is used to detect the pressure and pressure drop on the first side of the double-disc check valve, and the second pressure sensing system is used to detect the pressure and pressure drop on the second side of the double-disc check valve. The control module is used to calculate the pressure difference between the two sides of the double-disc check valve and control the direction and magnitude of the electromagnetic force in the electromagnetic actuator according to the pressure difference, thereby controlling the moving direction and axial stroke of the electromagnetic actuator. The axial movement of the electromagnetic actuator assists the first movable valve disc (3) and the second movable valve disc (4) to open and close according to the set tilt angle and the set response time.

9. A method for opening and closing a double-lobe one-way valve for aircraft, implemented based on the double-lobe one-way valve opening and closing system of claim 8, characterized in that, Includes the following steps: Step 1: Detect the linear pressure drop on the first side of the double-disc check valve using the first pressure sensing system, and calculate the first pressure acting on the first side of the double-disc check valve using the calibrated pressure on the first side and the linear pressure drop; Detect the linear pressure drop on the second side of the double-disc check valve using the second pressure sensing system, and calculate the second pressure acting on the second side of the double-disc check valve using the calibrated pressure on the second side and the linear pressure drop. Step 2: Calculate the actual pressure difference between the first pressure and the second pressure through the control module to determine the opening direction of the double-disc check valve, and calculate the difference between the actual pressure difference and the calibrated control pressure difference; if the difference is less than or equal to the calibrated pressure difference error, proceed to step 3; if the difference is greater than the calibrated pressure difference error, proceed to step 4. Step 3: The control module de-energizes the electromagnetic part in the opening and closing compensation device (5), so that the first movable valve disc (3) and the second movable valve disc (4) open and close autonomously under the action of the actual pressure difference. Step 4: The control module controls the electromagnetic action part in the opening and closing compensation device (5) to be energized, and calculates the electromagnetic force and axial stroke of the electromagnetic action part based on the difference value. The electromagnetic force is used to compensate for the pressure difference caused by the difference value, and the axial stroke assists the first movable valve disc (3) and the second movable valve disc (4) to open and close with a set tilt angle and a set response time.

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