Bivalve check valve for airplane, opening and closing system of bivalve check valve and opening and closing method of bivalve check valve

Abstract

The invention discloses a bivalve one-way valve for an airplane, an opening and closing system of the bivalve one-way valve and an opening and closing method of the bivalve one-way valve. The bivalve one-way valve comprises a valve ring, a cross beam, a first movable valve clack and a second movable valve clack. The first movable valve clack, the second movable valve clack and the first side of the cross beam jointly form a first acting surface in complete smooth transition; an opening and closing compensation device is arranged on the second side face of the cross beam and comprises an electromagnetic acting part, and the electromagnetic acting part is hinged to the first movable valve clack and the second movable valve clack through connecting rods; the electromagnetic action part adjusts the axial movement stroke of the electromagnetic action part according to the pressure difference and pressure drop between the two sides of the valve clack so as to assist the first movable valve clack and the second movable valve clack to be opened and closed according to the set inclination angle and response time. According to the double-clack check valve, the impact load and vibration of airflow borne by the valve body can be improved, long-time normal and safe operation of the valve body is guaranteed, the valve clack is assisted to act rapidly and accurately when the pressure difference of the two sides of the valve body exceeds the standard, and it is guaranteed that the double-clack check valve can be opened and closed with preset position precision within preset response time.

Description

Technical Field

[0001] The present invention belongs to the technical field of one-way valves for aviation, and in particular relates to a double-flap one-way valve for aircraft, a double-flap one-way valve opening and closing system, and an opening and closing method. Background Art

[0002] The double-flap one-way valve is one of the important control components installed inside the airborne ventilation duct to control the airflow interruption and airflow rate. In order to install the rotating shaft for the valve disc to rotate, the existing airborne double-flap one-way valve needs to install a split mounting frame on the crossbeam across the center of the valve body, and penetrate the flow-facing end of the crossbeam to fix the mounting frame. This causes the flow-facing surface of the crossbeam to be uneven, causing the airflow to exert a greater impact load on the valve body. In addition, since the valve body is under the influence of airflow vibration for a long time, the bolts and other connecting parts will loosen and fall off. Once the bolts are loose, it will affect the opening effect of the valve disc, and even the bolts will fall off and fall into the pipeline, posing a serious safety hazard to the aircraft.

[0003] Meanwhile, existing dual-flap check valves control their opening and closing via a pressure differential across their discs. However, in actual use, the airflow pressure fluctuates, and pressure drops occur during flow. Consequently, the actual pressure differential across the dual-flap check valve can deviate from the theoretical pressure differential. Large deviations can affect the valve's response speed and opening and closing position accuracy, ultimately preventing the valve from operating quickly and accurately within the required response time and opening and closing positions.

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

[0005] The present invention discloses a double-flap one-way valve for aircraft, a double-flap one-way valve opening and closing system, and an opening and closing method, which can effectively improve the impact load and vibration of the valve body subjected to the airflow, thereby ensuring the long-term normal and safe operation of the valve body, and when the pressure difference on both sides of the valve body exceeds the standard, the auxiliary valve flap can quickly and accurately move, ensuring that the double-flap one-way valve can be opened and closed with a preset position accuracy within a preset response time.

[0006] The present invention is achieved through the following technical solutions: A double-flap one-way valve for aircraft, comprising a valve ring, a crossbeam integrally provided at the center of the valve ring along the diameter direction, a first movable valve flap and a second movable valve flap symmetrically provided on both sides of the crossbeam; the first side surface of the first movable valve flap, the first side surface of the second movable valve flap, and the first side surface of the crossbeam constitute a first action surface with a complete and smooth transition; an opening and closing compensation device is provided at the center of the second side surface of the crossbeam, the opening and closing compensation device comprises at least one group of electromagnetic action parts that move along the central axis of the valve ring, the electromagnetic action parts are hinged to the second side surface of the first movable valve flap and the second side surface of the second movable valve flap through at least one group of connecting rods; the electromagnetic action parts adjust their own axial movement stroke according to the pressure difference and pressure drop between the two sides of the first movable valve flap and the second movable valve flap, so as to assist the first movable valve flap and the second movable valve flap to open and close according to the set inclination angle and the set response time.

[0007] The dual-flap one-way valve is installed in the aircraft's ventilation system. When the air pressure on the first side of the crossbar is greater than that on the second side, the pressure differential causes the first and second movable valve flaps to rotate toward the second side, opening the entire valve. When the air pressure on the second side is greater than that on the first side, the reverse pressure differential causes the first and second movable valve flaps to rotate toward the first side, closing the valve. By controlling the pressure on the first and second sides, the one-way opening and closing, as well as the degree of opening, of the first and second movable valve flaps can be controlled.

[0008] During actual use, the flow of air in the ventilation line inevitably generates pressure drops and pressure fluctuations, which results in the first and second movable valve flaps not being subjected to the theoretically preset pressure differential. This results in the first and second movable valve flaps not opening and closing according to the theoretically set opening and closing angles and response times. At this time, the electromagnetic action unit in the opening and closing compensation device adjusts its own axial movement stroke according to the pressure differential and pressure drop to assist the first and second movable valve flaps in opening and closing according to the set inclination angle and set response time, thereby ensuring that the entire double-flap one-way valve can respond to opening and closing quickly within 0.2 seconds. At the same time, the angle difference between the inclination angle of the first and second movable valve flaps after they are fully opened and the set inclination angle is less than or equal to 0.5°, thereby ensuring the high precision and rapid response of the entire double-flap one-way valve in the ventilation line. At the same time, the first side of the beam, the first side of the first movable valve disc, and the first side of the second movable valve disc jointly form a first active surface with a smooth transition, and the beam in the center of the valve ring is integrated, eliminating the structure of fixing the beam to the valve ring with bolts in the traditional double-flap one-way valve, and also eliminating the structure of passing bolts on the first side of the beam to fix the valve disc, so that the first side of the valve ring meets the airflow with a complete and smoothly transitioned first active surface, thereby effectively guiding the airflow and significantly reducing the vibration of the entire valve body, effectively avoiding the problem of loosening and falling off of bolts in the traditional double-flap one-way valve in a long-term vibration environment.

[0009] In order to better realize the present invention, further, the opening and closing compensation device includes a first electromagnetic part, a second electromagnetic part, a permanent magnetic slider, a ceramic center shaft, and a connecting rod. The ceramic center shaft is coaxial with the central axis of the valve ring and is arranged on the second side of the crossbeam. A permanent magnetic slider is slidably sleeved on the ceramic center shaft. The two sides of the permanent magnetic slider are respectively hinged to the second side of the first movable valve flap and the second side of the second movable valve flap through a connecting rod; the permanent magnetic slider is respectively provided with a first electromagnetic part and a second electromagnetic part on both sides along the central axis, and the first electromagnetic part and the second electromagnetic part are connected to the control device.

[0010] In order to better implement the present invention, further, a damping vibration reduction device is provided on the side of the permanent magnet slider close to the first electromagnetic part and the side close to the second electromagnetic part, and the damping vibration reduction device includes at least one group of circumferential damping vibration reduction parts and at least one group of axial damping vibration reduction parts.

[0011] In order to better realize the present invention, further, circumferential grooves and axial grooves are symmetrically arranged on both sides of the permanent magnet slider, and the damping vibration reduction device includes a slip ring, and the side of the slip ring close to the circumferential groove is slidingly connected to the circumferential groove, and a circumferential damping spring connected to the slip ring is arranged inside the circumferential groove; an axial slider is provided on the side of the slip ring close to the axial cavity, and the axial slider is axially slidingly connected to the axial cavity, and axial damping springs are arranged on both sides of the axial slider in the axial cavity, and the axial cavities on both sides of the axial slider are filled with damping fluid.

[0012] In order to better implement the present invention, further, a silencer component is provided on at least one side of the beam, and a fluid passage is provided on the silencer component corresponding to the first movable valve flap and the second movable valve flap. 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 flap and the second movable valve flap.

[0013] In order to better implement the present invention, further, the first movable valve flap and the second movable valve flap have different weights, and the offset between the valve flap mass center of the first movable valve flap and the second movable valve flap relative to the valve ring mass center of the valve ring is less than or equal to 2 mm.

[0014] In order to better implement the present invention, further, the limit deflection angle of the first movable valve flap and the second movable valve flap relative to the crossbeam is 75±2°; the surface roughness of the first movable valve flap and the second movable valve flap is less than or equal to 0.2 μm.

[0015] In order to better realize the present invention, further, a U-shaped bracket is integrally formed on the second side surface of the beam, a rotating shaft is rotatably provided on the U-shaped bracket, the first movable valve flap and the second movable valve flap are symmetrically rotatably sleeved on the rotating shaft through a damping bushing, and a pre-tightening member is provided at one end of the rotating shaft to adjust the pre-tightening force of the rotating shaft.

[0016] A double-flap one-way valve opening and closing system for aircraft is implemented based on the double-flap one-way valve for aircraft, including a first pressure sensing system arranged on a first side of the double-flap one-way valve, a second pressure sensing system arranged on a second side of the double-flap one-way 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-flap one-way valve, and the second pressure sensing system is used to detect the pressure and pressure drop on the second side of the double-flap one-way valve. The control module is used to resolve the pressure difference on both sides of the double-flap one-way valve, and control the direction and magnitude of the electromagnetic force in the electromagnetic action part according to the pressure difference, thereby controlling the movement direction and axial stroke of the electromagnetic action part, and assisting the first movable valve flap and the second movable valve flap to open and close according to the set inclination angle and set response time through the axial movement of the electromagnetic action part.

[0017] A method for opening and closing a double-flap check valve for an aircraft is implemented based on a double-flap check valve opening and closing system, comprising the following steps: Step 1: Detecting a linear pressure drop on a first side of the double-flap check valve using a first pressure sensing system, and calculating a first pressure acting on the first side of the double-flap check valve using a calibrated pressure on the first side and the linear pressure drop; detecting a linear pressure drop on a second side of the double-flap check valve using a second pressure sensing system, and calculating a second pressure acting on the second side of the double-flap 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 by the control module to determine the opening direction of the double-flap 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; Step 3: The control module controls the electromagnetic action part in the opening and closing compensation device to be powered off, so that the first movable valve flap and the second movable valve flap can 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 to be energized, and calculates the electromagnetic force and axial stroke of the electromagnetic action part based on the difference value, compensates for the pressure difference caused by the difference value through the electromagnetic force, and assists the first movable valve flap and the second movable valve flap to open and close with the set inclination angle and set response time through the axial stroke.

[0018] Compared with the prior art, the present invention has the following advantages and beneficial effects: (1) The present invention integrates the valve ring, the crossbeam, and the U-shaped bracket into an integrated structure, which not only improves the overall strength of the valve body, but also avoids the need to install bolts in the first section of the crossbeam, thereby ensuring that the first side of the crossbeam is a guide surface with a smooth transition. The guide surface smoothly guides and diverts the airflow on the first side, thereby reducing the impact load of the airflow on the valve body and ensuring that the impact load and torque on the first movable flap and the second movable flap are within an appropriate range, thereby ensuring that the first movable flap and the second movable flap can be opened and closed smoothly and in a timely manner. Since the bolts and other connecting parts are eliminated, the loosening and falling of the bolts under vibration conditions can also be avoided. (2) The present invention coaxially arranges an opening and closing compensation device on one side of the double-flap one-way valve, monitors the difference between the actual pressure difference and pressure drop on both sides of the valve disc and the theoretical pressure difference and pressure drop, and applies a magnetic force through the electromagnetic action part in the opening and closing compensation device according to the difference to assist in driving the first movable valve disc and the second movable valve disc to rotate quickly and accurately to the preset opening and closing position within the preset response time, thereby ensuring the rapid and accurate opening and closing operation of the double-flap one-way valve without the need to significantly adjust the control air pressure. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of the structure of a double-flap one-way valve for aircraft; Figure 2 It is a structural diagram of the opening and closing compensation device; Figure 3 It is a structural diagram of the damping vibration reduction device; Figure 4 It is a schematic diagram of the connection between the U-shaped bracket and the beam; Figure 5 This is a schematic diagram of the installation of the beam; Figure 6 Schematic diagram of the installation of the shaft; Figure 7 It is a structural diagram of an existing double-flap one-way valve.

[0020] Among them: 1-valve ring; 2-crossbeam; 3-first movable valve disc; 4-second movable valve disc; 5-opening and closing compensation device; 6-silencer component; 7-U-shaped bracket; 8-rotating shaft; 51-first electromagnetic part; 52-second electromagnetic part; 53-permanent magnet slider; 54-ceramic center shaft; 55-connecting rod; 56-damping vibration reduction device; 561-slip ring; 562-circumferential damping spring; 563-axial slider; 564-axial damping spring. DETAILED DESCRIPTION

[0021] Example 1: A double-flap one-way valve for aircraft of this embodiment, such as Figures 1-6As shown, it includes a valve ring 1, a crossbeam 2 is integrally provided at the center of the valve ring 1 along the diameter direction, and a first movable valve flap 3 and a second movable valve flap 4 are symmetrically rotated on both sides of the crossbeam 2; the first side surface of the first movable valve flap 3, the first side surface of the second movable valve flap 4, and the first side surface of the crossbeam 2 constitute a first action surface with a complete and smooth transition; an opening and closing compensation device 5 is provided at the center of the second side surface of the crossbeam 2, and the opening and closing compensation device 5 includes at least one group of electromagnetic action parts that move along the central axis of the valve ring 1, and the electromagnetic action parts are hinged to the second side surface of the first movable valve flap 3 and the second side surface of the second movable valve flap 4 through at least one group of connecting rods; the electromagnetic action parts adjust their own axial movement stroke according to the pressure difference and pressure drop between the two sides of the first movable valve flap 3 and the second movable valve flap 4, so as to assist the first movable valve flap 3 and the second movable valve flap 4 to open and close according to the set inclination angle and the set response time.

[0022] like Figure 7 As shown, in order to install the rotating shaft 8, a traditional double-flap one-way valve will have a split mounting bracket installed on the second side of the crossbeam 2, and a number of 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 will lead to two problems. First, the bolts and other connecting parts are in direct contact with the airflow and are exposed to a vibrating environment for a long time, causing the bolts to loosen and fall into the airflow pipeline, posing a huge safety hazard to the aircraft flight. Second, because the bolts are inserted through the first side of the crossbeam 2, the first side of the crossbeam 2 presents an uneven flow-facing surface, which in turn disrupts the airflow on the first side of the valve body, affecting the opening of the valve disc. After long-term use, the valve disc will be blocked from opening and the response time will be prolonged.

[0023] In this embodiment, when the pressure on the second side is greater than the pressure on the first side, the first and second movable valve flaps 3 and 4 rotate toward the first side to a fully closed state under the influence of the pressure differential. At this point, the first side of the first movable valve flap 3, the first side of the second movable valve flap 4, and the first side of the crossbeam 2 form a smoothly transitioned first operating surface. This smoothly transitioned first operating surface replaces the bolt holes, bolts, and other connecting components on the center beam of a conventional double-flap check valve, effectively reducing vibration of the double-flap check valve under the influence of airflow on the first side. Furthermore, because there are no bolts or other connecting components on the first side, the bolts are prevented from loosening and falling out under vibration. Furthermore, the first operating surface guides and diverts the airflow on the first side, allowing the airflow from the first side to more evenly act on the first and second movable valve flaps 3 and 4, ensuring smooth and rapid opening of the double-flap check valve.

[0024] like Figure 5 、 Figure 6As shown, the crossbeam 2 and valve ring 1 are integrally formed, firstly ensuring the strength of the valve body's main structure. Secondly, a rotating shaft 8 is directly pivoted on the second side of the crossbeam 2. The bolts securing the rotating shaft 8 on the first side of the crossbeam 2 are eliminated. Instead, a fully transitional guide surface is provided on the first side of the crossbeam 2. This fully transitional guide surface smoothly guides airflow from the first side to the first and second movable valve flaps 3 and 4, improving the overall force distribution of the valve body while effectively reducing vibration. Furthermore, when the first and second movable valve flaps 3 and 4 are fully closed, the first side surface of the first movable valve flap 3, the first side surface of the second movable valve flap 4, and the first side surface of the crossbeam 2 (i.e., the guide surface) form a smoothly transitioned first operating surface. By eliminating the connecting bolts, the risk of bolts loosening and falling due to vibration is completely eliminated. In addition, the guide surface guides and diverts the airflow on the first side, so that the airflow is smoothly and evenly diverted and flows to the first movable valve flap 3 and the second movable valve flap 4 respectively, thereby ensuring that the first movable valve flap 3 and the second movable valve flap 4 will not have problems of blockage, jamming, and delayed opening during long-term operation.

[0025] Furthermore, an opening and closing compensation device 5 is provided on the second side of the double-flap one-way valve, coaxially with the central axis of the valve ring 1. The function of the opening and closing compensation device 5 is to assist the first movable valve flap 3 and the second movable valve flap 4 in accurately and quickly opening and closing at a predetermined angle and within a predetermined response time when the pressure differential across the double-flap one-way valve exceeds the standard or is affected by a pressure drop. The magnetic force generated by the electromagnetic action portion of the opening and closing compensation device 5 compensates for the pressure differential, and the electromagnetic action portion then assists in driving the first movable valve flap 3 and the second movable valve flap 4 to a predetermined position within a predetermined response time. By providing the opening and closing compensation device 5 to compensate for the opening and closing positions of the first movable valve flap 3 and the second movable valve flap 4 caused by pressure differential fluctuations and pressure drops, the double-flap one-way valve can be opened and closed efficiently and accurately without requiring significant adjustments to the pressure across the valve.

[0026] Example 2: This embodiment discloses a double-flap one-way valve for aircraft, which is optimized based on the embodiment 1. Figure 2 As shown, the opening and closing compensation device 5 includes a first electromagnetic part 51, a second electromagnetic part 52, a permanent magnetic slider 53, a ceramic center shaft 54, and a connecting rod 55. The ceramic center shaft 54 ​​is coaxial with the central axis of the valve ring 1 and is arranged on the second side of the crossbeam 2. A permanent magnetic slider 53 is slidably sleeved on the ceramic center shaft 54. The two sides of the permanent magnetic slider 53 are hinged to the second side of the first movable valve flap 3 and the second side of the second movable valve flap 4 through a connecting rod 55; the permanent magnetic slider 53 is respectively provided with a first electromagnetic part 51 and a second electromagnetic part 52 on both sides along the central axis, and the first electromagnetic part 51 and the second electromagnetic part 52 are connected to the control device.

[0027] The inner bore of the permanent magnet slider 53 slides in conjunction with the ceramic center axis 54, and the inner bore roughness of the permanent magnet slider 53 is less than or equal to 0.05 mm, ensuring that the friction force of the permanent magnet slider 53 is significantly reduced when it slides smoothly along the ceramic center axis 54. By controlling the direction and magnitude of the current flowing through the coils of the first and second electromagnetic parts 51, 52, and thereby controlling the magnetism and magnitude of the magnetic force of the first and second electromagnetic parts 51, 52, the first and second electromagnetic parts 51, 52 cooperate to apply a combined magnetic force to the permanent magnet slider 53. When assisting the opening of the first and second movable valve flaps 3, 4, the combined magnetic force is directed from the first side to the second side, and the magnitude of the combined magnetic force is calculated based on the pressure drop loss and the difference between the actual pressure difference between the two sides of the valve body and the calibrated pressure difference. When assisting the closing of the first and second movable valve flaps 3, 4, the combined magnetic force is directed from the second side to the first side, and the magnitude of the combined magnetic force is calculated based on the pressure drop loss and the difference between the actual pressure difference between the two sides of the valve body and the calibrated pressure difference. When the permanent magnetic slider 53 slides under the action of the magnetic combined force, the first movable valve flap 3 and the second movable valve flap 4 are driven to rotate to open or close through the connecting rod 55 .

[0028] Furthermore, the permanent magnet slider 53 is provided with a damping vibration reduction device 56 on both the side near the first electromagnetic portion 51 and the side near the second electromagnetic portion 52. The damping vibration reduction device 56 includes at least one set of circumferential damping vibration reduction components and at least one set of axial damping vibration reduction components. The damping vibration reduction device 56 is used to reduce vibration during the sliding of the permanent magnet slider 53 and the rotation of the first and second movable valve flaps 3 and 4. Under the action of airflow, the permanent magnet slider 53, the first and second movable valve flaps 3 and 4 are subjected to not only axial vibration but also circumferential vibration. The circumferential damping vibration is buffered by the circumferential damping vibration reduction component, while the axial damping vibration is buffered by the axial damping vibration reduction component.

[0029] Further, such as Figure 3 As shown, circumferential grooves and axial grooves are symmetrically provided on both sides of the permanent magnet slider 53, and the damping vibration reduction device 56 includes a slip ring 561, and the side of the slip ring 561 close to the circumferential groove is slidably connected to the circumferential groove, and 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 close to the axial cavity, and the axial slider 563 is axially slidably connected to the axial cavity, and axial damping springs 564 are provided on both sides of the axial slider 563 in the axial cavity, and the axial cavities on both sides of the axial slider 563 are filled with damping fluid.

[0030] Under the action of circumferential vibration loads, the slip ring 561 slides circumferentially relative to the circumferential groove. At this time, the circumferential damping spring 562 located within the circumferential groove is compressed, and the circumferential vibration load is buffered by the elastic deformation of the circumferential damping spring 562. Under the action of axial vibration loads, the axial slider 563 slides axially within the axial cavity, thereby causing the axial damping springs 564 on both sides of the axial slider 563 to elastically deform and squeeze the damping fluid, causing the damping fluid to flow in the cavities on both sides of the axial slider 563. The elastic deformation of the axial damping spring 564 and the flow of the damping fluid cooperate to buffer the axial vibration load.

[0031] The rest of this embodiment is the same as that of Embodiment 1, and therefore will not be described again.

[0032] Example 3: This embodiment discloses a double-flap one-way valve for aircraft, which is optimized based on the embodiment 1 or 2, such as Figure 1 As shown, a silencer component 6 is provided on at least one side of the crossbeam 2, and a fluid passage is provided on the silencer component 6 corresponding to the first movable valve flap 3 and the second movable valve flap 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 flap 3 and the second movable valve flap 4.

[0033] Because the thickness of the silencer 6 is much smaller than the length of the pipeline and the thickness of the valve ring 1, the pressure drop of the fluid passing through the fluid passage of the silencer 6 is negligible. Two fluid passages are centrally symmetrically arranged on the silencer 6, corresponding to the first movable valve flap 3 and the second movable valve flap 4. After passing through the fluid passages, the airflow enters the larger-diameter pipeline to achieve pulsation reduction.

[0034] The rest of this embodiment is the same as that of Embodiment 1 or 2, and thus will not be described again.

[0035] Example 4: This embodiment discloses a dual-flap check valve for aircraft, optimized based on any one of Embodiments 1-3. The first movable valve flap 3 and the second movable valve flap 4 have different weights, and the offset between the valve center of mass of the first movable valve flap 3 and the second movable valve flap 4 relative to the valve ring center of mass of the valve ring 1 is less than or equal to 2 mm. The maximum deflection angle of the first movable valve flap 3 and the second movable valve flap 4 relative to the crossbeam 2 is 75±2°. The surface roughness of the first movable valve flap 3 and the second movable valve flap 4 is less than or equal to 0.2 μm.

[0036] Due to the offset of the center of mass of the first movable valve flap 3 and the second movable valve flap 4, the positions of the two fluid passages on the silencer component 6 also move accordingly so that the shape and distribution position of the fluid passages are adapted to the fluid distribution in the pipeline after the fluid passes through the first movable valve flap 3 and the second movable valve flap 4.

[0037] Based on the torque balance equation, an unequal weight model for the first movable valve flap 3 and the second movable valve flap 4 is established. Preferably, the weight of the first movable valve flap 3 is 30g, the weight of the second movable valve flap 4 is 25g, and the offset between the valve center of mass of the first movable valve flap 3 and the second movable valve flap 4 relative to the valve center of mass of the valve ring 1 is less than or equal to 2mm. This ensures that when the first movable valve flap 3 and the second movable valve flap 4 rotate to open at a preset angle, their torque is within a preset torque range. Ultimately, this ensures that the first movable valve flap 3 and the second movable valve flap 4 can quickly respond to opening within 0.1s, and reduces the impact load of the airflow on the first movable valve flap 3 and the second movable valve flap 4.

[0038] Furthermore, the maximum deflection angle of the first movable valve flap 3 and the second movable valve flap 4 relative to the crossbeam 2 is 75±2°, which can ensure the air flow through the valve ring 1 and also reduce the impact load on the first movable valve flap 3 and the second movable valve flap 4.

[0039] Furthermore, the surface roughness of the first movable valve flap 3 and the second movable valve flap 4 is less than or equal to 0.2 μm, which ensures the air tightness of the contact between the first movable valve flap 3, the second movable valve flap 4 and the inner surface of the valve ring 1 in the closed state to avoid airflow leakage; during the opening process, it ensures that the first movable valve flap 3 and the second movable valve flap 4 can be opened smoothly to avoid blockage and jamming during the opening of the first movable valve flap 3 and the second movable valve flap 4.

[0040] The rest of this embodiment is the same as any one of Embodiments 1-3, so it will not be repeated here.

[0041] Example 5: This embodiment discloses a double-flap one-way valve for aircraft, which is optimized based on any one of the embodiments 1-4, such as Figure 4-Figure 6 As shown, a U-shaped bracket 7 is integrally formed on the second side surface of the crossbeam 2, and a rotating shaft 8 is rotatably provided on the U-shaped bracket 7. The first movable valve flap 3 and the second movable valve flap 4 are symmetrically rotatably sleeved on the rotating shaft 8 through a damping bushing, and 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.

[0042] 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, thereby eliminating the bolts used to secure the U-shaped bracket 7 in traditional structures, ensuring that the first side of the crossbeam 2 can form a smoothly transitioned guide surface, while also improving the overall strength of the crossbeam 2 and the U-shaped bracket 7.

[0043] Furthermore, a pre-tightening member is provided at one end of the rotating shaft 8. The rotating shaft 8 is provided with an external thread at one end. The pre-tightening member includes a locking nut that screws into the external thread. By adjusting the tightening degree of the locking nut, the pre-tightening force on the rotating shaft 8 is set to about 5N.m.

[0044] The rest of the contents of this embodiment are the same as any one of Embodiments 1-4, and therefore will not be repeated here.

[0045] Example 6: The present embodiment discloses an opening and closing system for a double-flap one-way valve for an aircraft, which is implemented based on a double-flap one-way valve for an aircraft, and includes a first pressure sensing system arranged on a first side of the double-flap one-way valve, a second pressure sensing system arranged on a second side of the double-flap one-way 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-flap one-way valve, and the second pressure sensing system is used to detect the pressure and pressure drop on the second side of the double-flap one-way valve. The control module is used to resolve the pressure difference on both sides of the double-flap one-way valve, and control the direction and magnitude of the electromagnetic force in the electromagnetic action part according to the pressure difference, thereby controlling the movement direction and axial stroke of the electromagnetic action part, and assisting the first active valve flap 3 and the second active valve flap 4 to open and close according to the set inclination angle and the set response time through the axial movement of the electromagnetic action part.

[0046] A method for opening and closing a double-flap check valve for an aircraft is implemented based on a double-flap check valve opening and closing system, comprising the following steps: Step 1: Detecting a linear pressure drop on a first side of the double-flap check valve using a first pressure sensing system, and calculating a first pressure acting on the first side of the double-flap check valve using a calibrated pressure on the first side and the linear pressure drop; detecting a linear pressure drop on a second side of the double-flap check valve using a second pressure sensing system, and calculating a second pressure acting on the second side of the double-flap 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 by the control module to determine the opening direction of the double-flap 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 controls the electromagnetic action part in the opening and closing compensation device 5 to be powered off, so that the first movable valve flap 3 and the second movable valve flap 4 can 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, compensates for the pressure difference caused by the difference value through the electromagnetic force, and assists the first movable valve flap 3 and the second movable valve flap 4 to open and close with the set inclination angle and set response time through the axial stroke.

[0047] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent change made to the above embodiment based on the technical essence of the present invention shall fall within the scope of protection of the present invention.

Claims

1. A double-flap one-way 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, and a first movable valve flap (3) and a second movable valve flap (4) are symmetrically provided on both sides of the crossbeam (2); the first side surface of the first movable valve flap (3), the first side surface of the second movable valve flap (4), and the first side surface of the crossbeam (2) constitute a first action surface with a complete and smooth transition; an opening and closing compensation device (5) is provided at the center of the second side surface of the crossbeam (2), and the opening and closing compensation device (5) includes at least one group of electromagnetic action parts that move along the central axis of the valve ring (1), and the electromagnetic action parts are hinged to the second side surface of the first movable valve flap (3) and the second side surface of the second movable valve flap (4) through at least one group of connecting rods; the electromagnetic action parts adjust their own axial movement stroke according to the pressure difference and pressure drop between the two sides of the first movable valve flap (3) and the second movable valve flap (4), so as to assist the first movable valve flap (3) and the second movable valve flap (4) to open and close according to the set inclination angle and the set response time.

2. The double-flap one-way valve for aircraft according to claim 1, characterized in that: The opening and closing compensation device (5) comprises a first electromagnetic part (51), a second electromagnetic part (52), a permanent magnetic slider (53), a ceramic center shaft (54), and a connecting rod (55). The ceramic center shaft (54) is coaxial with the center axis of the valve ring (1) and is arranged on the second side of the crossbeam (2). The permanent magnetic slider (53) is slidably sleeved on the ceramic center shaft (54). The two sides of the permanent magnetic slider (53) are respectively hinged to the second side of the first movable valve flap (3) and the second side of the second movable valve flap (4) through the connecting rod (55). The first electromagnetic part (51) and the second electromagnetic part (52) are respectively arranged on both sides of the center axis of the permanent magnetic slider (53). The first electromagnetic part (51) and the second electromagnetic part (52) are connected to the control device.

3. The double-flap one-way valve for aircraft according to claim 2, characterized in that: A damping vibration reduction device (56) is provided on both the side of the permanent magnet slider (53) close to the first electromagnetic part (51) and the side close to the second electromagnetic part (52). The damping vibration reduction device (56) includes at least one group of circumferential damping vibration reduction parts and at least one group of axial damping vibration reduction parts.

4. The double-flap one-way valve for aircraft according to claim 3, characterized in that: Circumferential grooves and axial grooves are symmetrically arranged on both sides of the permanent magnet slider (53); the damping vibration reduction device (56) includes a slip ring (561); the side of the slip ring (561) close to the circumferential groove is slidably connected to the circumferential groove; a circumferential damping spring (562) connected to the slip ring (561) is arranged inside the circumferential groove; an axial slider (563) is arranged on the side of the slip ring (561) close to the axial cavity; the axial slider (563) is axially slidably connected to the axial cavity; axial damping springs (564) are arranged on both sides of the axial slider (563) in the axial cavity; the axial cavities on both sides of the axial slider (563) are filled with damping fluid.

5. A double-flap one-way valve for aircraft according to any one of claims 1 to 4, characterized in that: At least one side of the crossbeam (2) is provided with a silencer component (6), and a fluid passage is provided on the silencer component (6) corresponding to the first movable valve flap (3) and the second movable valve flap (4), and 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 flap (3) and the second movable valve flap (4).

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

7. The double-flap one-way valve for aircraft according to claim 6, characterized in that: The limit deflection angle of the first movable valve flap (3) and the second movable valve flap (4) relative to the crossbeam (2) is 75±2°; and the surface roughness of the first movable valve flap (3) and the second movable valve flap (4) is less than or equal to 0.2 μm.

8. A double-flap one-way valve for aircraft according to any one of claims 1 to 4, characterized in that: A U-shaped bracket (7) is integrally formed on the second side surface of the crossbeam (2), a rotating shaft (8) is rotatably provided on the U-shaped bracket (7), the first movable valve flap (3) and the second movable valve flap (4) are symmetrically rotatably sleeved on the rotating shaft (8) via a damping bushing, and 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).

9. An aircraft double-flap check valve opening and closing system, implemented based on the aircraft double-flap check valve according to any one of claims 1 to 8, characterized in that: The invention comprises a first pressure sensing system arranged on the first side of the double-flap one-way valve, a second pressure sensing system arranged on the second side of the double-flap one-way valve, and a control module, wherein the first pressure sensing system is used to detect the pressure and pressure drop on the first side of the double-flap one-way valve, and the second pressure sensing system is used to detect the pressure and pressure drop on the second side of the double-flap one-way valve. The control module is used to calculate the pressure difference between the two sides of the double-flap one-way valve, and control the direction and magnitude of the electromagnetic force in the electromagnetic action part according to the pressure difference, thereby controlling the movement direction and axial stroke of the electromagnetic action part, and assisting the first movable valve flap (3) and the second movable valve flap (4) to open and close according to the set inclination angle and the set response time through the axial movement of the electromagnetic action part.

10. A method for opening and closing a double-flap check valve for an aircraft, implemented based on the double-flap check valve opening and closing system according to claim 9, characterized in that: The following steps are involved: Step 1: Detecting a linear pressure drop on a first side of the double-flap check valve using a first pressure sensing system, and calculating a first pressure acting on the first side of the double-flap check valve using a calibrated pressure on the first side and the linear pressure drop; detecting a linear pressure drop on a second side of the double-flap check valve using a second pressure sensing system, and calculating a second pressure acting on the second side of the double-flap 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 by the control module to determine the opening direction of the double-flap 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 controls the electromagnetic action part in the opening and closing compensation device (5) to be powered off, so that the first movable valve flap (3) and the second movable valve flap (4) are opened and closed 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, compensates for the pressure difference caused by the difference value through the electromagnetic force, and assists the first movable valve flap (3) and the second movable valve flap (4) to open and close at the set inclination angle and the set response time through the axial stroke.

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