An oxygen supply system for an aircraft

Abstract

The application belongs to the technical field of oxygen supply, and particularly discloses an oxygen supply system of an airplane, which comprises an oxygen cylinder, one end of the oxygen cylinder is fixedly connected with an oxygen cut-off valve, the outer wall of the oxygen cut-off valve is fixedly connected with an oxygen connection valve, the outer wall of the oxygen connection valve is fixedly connected with a connecting air pipe, one end of the connecting air pipe away from the oxygen connection valve is fixedly connected with a filter sleeve, the inside of the filter sleeve is provided with a replacement assembly, and one end of the filter sleeve away from the connecting air pipe is fixedly connected with an oxygen supply pipe; the adjusting assembly is used for automatically adjusting the oxygen supply amount according to the demand of the airplane passengers, and the adjusting assembly is connected with the oxygen connection valve and the oxygen supply pipe; the adjusting assembly comprises an adjusting ring fixedly installed in the inside of the oxygen connection valve. Through the setting of the adjusting assembly, the oxygen supply speed of the oxygen cylinder can be automatically adjusted according to the oxygen consumed by the passengers on the airplane after the oxygen supply system is started, the oxygen supply effect is improved, and the passengers are not affected by too much or too little oxygen supply amount.

Description

Technical Field

[0001] This invention belongs to the field of oxygen supply technology, and specifically relates to an oxygen supply system for an aircraft. Background Technology

[0002] An aircraft oxygen supply system is a personal protective equipment (PPE) designed to prevent hypoxia in aircraft occupants during high-altitude flight or emergency situations. It comes in various forms depending on the number of occupants, flight range, service ceiling, and mission nature. The system typically consists of an oxygen source, control valves, regulators, indicating instruments, an oxygen supply unit, a disconnector, and oxygen masks. It can also be divided into three parts: an oxygen generation system, an oxygen supply system, and oxygen-supplying PPE.

[0003] Existing aircraft oxygen supply systems cannot adjust the oxygen supply in real time according to the number of passengers and their oxygen intake to avoid oxygen waste and insufficient supply. Furthermore, they cannot automatically replace the filters in the oxygen supply system during oxygen supply, affecting the oxygen filtration effect. To address these issues, designing an aircraft oxygen supply system has become a problem that we need to solve. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings of existing technologies by proposing an oxygen supply system for aircraft.

[0005] To achieve the above objectives, the present invention provides an oxygen supply system for an aircraft, including an oxygen cylinder, an oxygen shut-off valve fixedly connected to one end of the oxygen cylinder, an oxygen connection valve fixedly connected to the outer wall of the oxygen shut-off valve, a connecting air pipe fixedly connected to the outer wall of the oxygen connection valve, a filter sleeve fixedly connected to the end of the connecting air pipe away from the oxygen connection valve, a replacement component provided inside the filter sleeve, and an oxygen supply pipe fixedly connected to the end of the filter sleeve away from the connecting air pipe. An adjustment component is used to automatically and dynamically adjust the oxygen supply according to the needs of the aircraft occupants. The adjustment component is connected to the oxygen connection valve and the oxygen supply pipe. The regulating assembly includes an regulating ring fixedly installed inside the oxygen connecting valve. A bidirectional threaded sleeve is rotatably connected inside the oxygen connecting valve. Two threaded rods are threadedly connected inside the bidirectional threaded sleeve. The two threaded rods are arranged in a mirror symmetrical manner. An regulating block is fixedly connected to the end of each threaded rod away from the bidirectional threaded sleeve.

[0006] The regulating component can automatically adjust the oxygen supply rate of the oxygen cylinders according to the oxygen consumption of the passengers after the oxygen supply system is started, thereby improving the oxygen supply effect and avoiding excessive or insufficient oxygen supply, which could have adverse effects on the passengers.

[0007] In the above technical solution, a sealing block is slidably connected inside the first diverter tube, a pressure spring is fixedly installed on one side of the sealing block, the end of the pressure spring away from the sealing block is fixedly installed inside the first diverter tube, a connecting rod is fixedly connected to the side of the sealing block near the pressure spring, the end of the connecting rod away from the sealing block passes through the first diverter tube, and a hinge is fixedly connected to the protective shell.

[0008] In the above technical solution, the adjusting block is slidably connected inside the oxygen connecting valve, the outer wall of the bidirectional threaded sleeve is fixedly connected to a hinge block, the hinge is hinged to the outer wall of the hinge block, the outer wall of the hinge is slidably connected to a connecting pipe, the connecting pipe is sleeved on the outer wall of the connecting rod, and the connecting pipe is fixedly connected to one side of the oxygen connecting valve.

[0009] In the above technical solution, the replacement component further includes a sliding sleeve slidably connected inside the filter sleeve, a compression spring fixedly installed between the sliding sleeve and the filter sleeve, a first filter element inserted inside the sliding sleeve, a second diverter fixedly connected to the outer wall of the oxygen supply pipe, and a placement sleeve fixedly connected to the end of the second diverter away from the oxygen supply pipe.

[0010] In the above technical solution, a push plate is slidably connected inside the placement sleeve. A plurality of second filter sheets are provided on the side of the push plate away from the second diversion pipe. A storage cavity is provided on the side of the filter sleeve of the second filter sheet away from the placement sleeve. The placement sleeve and the storage cavity are both locked between two protective shells.

[0011] In the above technical solution, one of the second filter elements is provided with a pusher on one side, and an inner telescopic rod is fixedly connected to the outer wall of the pusher. The outer telescopic rod is slidably connected to the inside of the protective shell, and a storage spring is fixedly installed between the inner and outer telescopic rods.

[0012] In the above technical solution, a first rack is fixedly installed on one side of the telescopic rod outer rod. A double-layer gear large gear meshes with the outer wall of the first rack. The double-layer gear is rotatably connected to the inside of the protective shell and the inside of the filter sleeve. A second rack is provided inside the sliding sleeve. The second rack meshes with the double-layer gear small gear. A replacement groove is provided on the outer wall of the filter sleeve.

[0013] Compared with the prior art, the present invention has the following beneficial effects: By adjusting the settings of the components, the oxygen supply rate of the oxygen cylinder can be automatically adjusted according to the oxygen consumed by the passengers after the oxygen supply system is started, thereby improving the oxygen supply effect and avoiding excessive or insufficient oxygen supply, which could affect the passengers. By setting the replacement component, the first filter inside the filter sleeve can be monitored in real time. When the first filter fails, the replacement component is automatically triggered to replace the first filter, thus preventing the failed first filter from filtering oxygen and affecting the filtration efficiency and effect. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the overall structure proposed in this invention; Figure 2 This is a cross-sectional view of the unfolded structure of the replacement component proposed in this invention; Figure 3 This is a cross-sectional view of the structure of the replacement component in its contracted state as proposed in this invention. Figure 4 The present invention proposes Figure 3 Enlarged view of the A-section structure; Figure 5 This is a partial structural diagram of the replacement component in its contracted state as proposed in this invention; Figure 6 This is a partial structural cross-sectional view of the adjustment component proposed in this invention.

[0015] In the diagram: 1. Oxygen cylinder; 2. Oxygen shut-off valve; 3. Oxygen connection valve; 4. Connecting pipe; 5. Filter sleeve; 6. Oxygen supply pipe; 7. First diverter pipe; 8. Exhaust pipe; 9. Protective shell; 10. Sealing block; 11. Pressure spring; 12. Connecting rod; 13. Connecting pipe; 15. Hinge; 16. Hinge block; 17. Bidirectional threaded sleeve; 18. Threaded rod; 19. Adjusting block; 20. Adjusting ring; 21. Compression spring; 22. Sliding sleeve; 23. First filter; 24. Second diverter pipe; 25. Placement sleeve; 26. Push plate; 27. Second filter; 28. Storage cavity; 29. ​​Pushing component; 30. Telescopic rod; 31. Storage spring; 32. First rack; 33. Double-layer gear; 34. Second rack; 35. Replacement slot. Detailed Implementation

[0016] To better understand the above-mentioned objectives, features, and advantages of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0017] like Figures 1 to 6 An oxygen supply system for an aircraft is shown, including an oxygen cylinder 1. An oxygen shut-off valve 2 is fixedly connected to one end of the oxygen cylinder 1. An oxygen connecting valve 3 is fixedly connected to the outer wall of the oxygen shut-off valve 2. A connecting pipe 4 is fixedly connected to the outer wall of the oxygen connecting valve 3. A filter sleeve 5 is fixedly connected to the end of the connecting pipe 4 away from the oxygen connecting valve 3. A replacement component is provided inside the filter sleeve 5. An oxygen supply pipe 6 is fixedly connected to the end of the filter sleeve 5 away from the connecting pipe 4. The regulating component is used to automatically and dynamically adjust the oxygen supply according to the needs of the aircraft crew. The regulating component is connected to the oxygen connection valve 3 and the oxygen supply pipe 6. The regulating assembly includes an regulating ring 20 fixedly installed inside the oxygen connection valve 3. A bidirectional threaded sleeve 17 is rotatably connected inside the oxygen connection valve 3. Two threaded rods 18 are threadedly connected inside the bidirectional threaded sleeve 17, arranged in a mirror-symmetrical configuration. An regulating block 19 is fixedly connected to the end of each threaded rod 18 away from the bidirectional threaded sleeve 17. The regulating block 19 is slidably connected inside the oxygen connection valve 3. A hinge block 16 is fixedly connected to the outer wall of the bidirectional threaded sleeve 17. The regulating assembly also includes a first diversion pipe 7 fixedly installed on the outer wall of the oxygen supply pipe 6. An exhaust pipe 8 is fixedly connected to the outer wall of the first diversion pipe 7. Protective shells are fitted around the outer walls of the filter sleeve 5, oxygen supply pipe 6, first diversion pipe 7, and exhaust pipe 8. 9. The number of protective shells 9 is set to two, and the two protective shells 9 are fixedly connected by threads. A sealing block 10 is slidably connected inside the first diversion pipe 7. A pressure spring 11 is fixedly installed on one side of the sealing block 10. The end of the pressure spring 11 away from the sealing block 10 is fixedly installed inside the first diversion pipe 7. A connecting rod 12 is fixedly connected to the side of the sealing block 10 near the pressure spring 11. The end of the connecting rod 12 away from the sealing block 10 passes through the first diversion pipe 7 and is fixedly connected to the protective shell 9. The hinge 15 is hinged to the outer wall of the hinge block 16. A connecting pipe 13 is slidably connected to the outer wall of the hinge 15. The connecting pipe 13 is sleeved on the outer wall of the connecting rod 12. The connecting pipe 13 is fixedly connected to one side of the oxygen connecting valve 3. The regulating component can automatically adjust the oxygen supply speed of oxygen cylinder 1 according to the oxygen consumed by the passengers after the oxygen supply system is started, thereby improving the oxygen supply effect and avoiding excessive or insufficient oxygen supply, which could have adverse effects on the passengers. When the oxygen supply system is activated, the oxygen shut-off valve 2 is first opened, allowing oxygen from the oxygen cylinder 1 to flow through the oxygen shut-off valve 2, oxygen connection valve 3, and connecting pipe 4 into the filter sleeve 5. The oxygen then passes through the first filter 23 inside the filter sleeve 5 and flows into the oxygen supply pipe 6, which transmits oxygen to the oxygen masks (not shown) to supply oxygen to the aircraft occupants. As the oxygen level inside the oxygen supply pipe 6 gradually increases, the internal pressure rises. The oxygen in the supply pipe 6 begins to push the sealing block 10 inside the first diversion pipe 7, causing the sealing block 10 to slide along the inside of the first diversion pipe 7. This causes the sealing block 10 to compress the pressure spring 11 and push the connecting rod 12, which in turn pushes the hinge 15 to slide along the inside of the connecting pipe 13. The sliding of the hinge 15 causes the bidirectional threaded sleeve 17 to rotate via the hinge block 16. The bidirectional threaded sleeve 17 then drives two threaded rods 18 to move closer together via the threads, causing the two threaded rods 18 to move the adjusting block 19 along the oxygen supply pipe. The internal sliding of valve 3 allows the regulating block 19 to gradually approach the regulating ring 20, reducing the space between the regulating ring 20 and the regulating block 19. This changes the amount of gas flowing through the regulating ring 20 and the regulating block 19, thus reducing the oxygen supply. When the oxygen pressure inside the oxygen supply pipe 6 decreases, the pressure spring 11 pushes the sealing block 10 to reset, causing the sealing block 10 to pull the hinge 15 to reset via the connecting rod 12. The hinge 15 then drives the bidirectional threaded sleeve 17 to reverse and reset via the hinge block 16, increasing the oxygen supply again. This achieves the effect of dynamically adjusting the oxygen supply according to the internal pressure of the oxygen supply pipe 6. When the oxygen intake of the aircraft occupants increases, the oxygen volume inside the oxygen supply pipe 6 decreases, the internal air pressure of the oxygen supply pipe 6 decreases, and the regulating component increases the oxygen supply to provide oxygen for the aircraft occupants. When the oxygen intake of the aircraft occupants decreases, the oxygen volume inside the oxygen supply pipe 6 gradually increases, the internal air pressure of the oxygen supply pipe 6 increases, and the regulating component reduces the oxygen supply to avoid oxygen waste. This achieves the effect of dynamically adjusting the oxygen supply according to the oxygen needs of the aircraft occupants, improving the oxygen supply effect.

[0018] The replacement component includes a sliding sleeve 22 slidably connected inside the filter sleeve 5, a compression spring 21 fixedly installed between the sliding sleeve 22 and the filter sleeve 5, a first filter element 23 inserted inside the sliding sleeve 22, a second diverter pipe 24 fixedly connected to the outer wall of the oxygen supply pipe 6, a placement sleeve 25 fixedly connected to the end of the second diverter pipe 24 away from the oxygen supply pipe 6, a push plate 26 slidably connected inside the placement sleeve 25, a plurality of second filter elements 27 provided on the side of the push plate 26 away from the second diverter pipe 24, a receiving cavity 28 provided on the side of the filter sleeve 5 away from the placement sleeve 25, and both the placement sleeve 25 and the receiving cavity 28 are secured between two protective shells 9, one of the second filter elements 27... A pusher 29 is provided on one side, and an inner rod of a telescopic rod 30 is fixedly connected to the outer wall of the pusher 29. The outer rod of the telescopic rod 30 is slidably connected to the inside of the protective shell 9. A storage spring 31 is fixedly installed between the inner rod and the outer rod of the telescopic rod 30. A first rack 32 is fixedly installed on one side of the outer rod of the telescopic rod 30. A large gear of a double-layer gear 33 meshes with the outer wall of the first rack 32. The double-layer gear 33 is rotatably connected to the inside of the protective shell 9. The double-layer gear 33 is rotatably connected to the inside of the filter sleeve 5. A second rack 34 is provided inside the sliding sleeve 22. The second rack 34 meshes with the small gear of the double-layer gear 33. A replacement groove 35 is provided on the outer wall of the filter sleeve 5. Among them, the replacement component can monitor the first filter 23 inside the filter sleeve 5 in real time. After the first filter 23 fails, the replacement component is automatically triggered to replace the first filter 23, so as to prevent the failed first filter 23 from filtering oxygen and affecting the filtration efficiency and filtration effect. Specifically, during the process of oxygen being discharged into the oxygen supply pipe 6 through the filter sleeve 5, the first filter 23 inside the filter sleeve 5 filters the oxygen. As the first filter 23 gradually becomes ineffective, its filtration efficiency decreases, increasing the oxygen pressure difference across the first filter 23. This causes the first filter 23 to be pushed towards the oxygen supply pipe 6 by the oxygen, which in turn causes the first filter 23 to push the compression spring 21 to contract and store force through the sliding sleeve 22 until the sliding sleeve 22 reaches the end of the filter sleeve 5 and stops. At this point, the groove on the sliding sleeve 22 where the first filter 23 is installed aligns with the replacement groove 35, stopping the seal on the replacement groove 35. The sliding sleeve 22 drives the small gear of the double-layer gear 33 to rotate via the second rack 34, causing the large gear of the double-layer gear 33 to drive the first rack 32 to move. This allows the first rack 32 to drive the outer rod of the telescopic rod 30 to slide along the inside of the protective shell 9, and pulls the storage spring 31 to gradually deform and store force. After the sliding sleeve 22 stops sealing the replacement groove 35, the inner rod of the telescopic rod 30 pushes the second filter 27 through the pusher 29 to enter the interior of the sliding sleeve 22 through the replacement groove 35, and squeezes the first filter 23 inside the sliding sleeve 22 into the interior of the receiving cavity 28. At this time, the storage spring 31 contracts and pulls the inner rod of the telescopic rod 30 to move, causing the telescopic rod 30 to move. The inner rod pushes the corresponding second filter 27 through the pusher 29, inserting it into the interior of the sliding sleeve 22 along the replacement groove 35. It also pushes the failed first filter 23 inside the sliding sleeve 22 into the receiving cavity 28. After the second filter 27 is installed inside the sliding sleeve 22, the oxygen filtration efficiency is restored, the pressure difference on both sides of the second filter 27 decreases, and the compression spring 21 begins to reset the second filter 27 inside the sliding sleeve 22. The reset of the sliding sleeve 22 will drive the double-layer gear 33 to reverse through the second rack 34, causing the double-layer gear 33 to reset through the first rack 32, which in turn drives the telescopic rod 30 to reset. This allows the telescopic rod 30 to reset the pusher 29. At this point... Oxygen inside the oxygen supply tube 6 is discharged into the placement sleeve 25 through the second diverter tube 24, pushing the pusher plate 26 inside the placement sleeve 25. The pusher plate 26 pushes the second filter 27 to move away from the second diverter tube 24. At this time, a new second filter 27 will be pushed to the side of the reset pusher 29, waiting for the replacement component to work again. This achieves the effect of automatically replacing the failed filter, avoiding filter failure during the operation of the oxygen supply system, which would affect the filtration effect and filtration quality of oxygen, and prevent residual dust in the oxygen and dust and debris generated during the operation of the oxygen supply system from mixing in the oxygen and causing damage to the respiratory tract of the aircraft occupants.

[0019] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed invention.

Claims

1. An oxygen supply system for an aircraft, comprising an oxygen cylinder (1), characterized in that, One end of the oxygen cylinder (1) is fixedly connected to an oxygen shut-off valve (2), the outer wall of the oxygen shut-off valve (2) is fixedly connected to an oxygen connection valve (3), the outer wall of the oxygen connection valve (3) is fixedly connected to a connecting pipe (4), the end of the connecting pipe (4) away from the oxygen connection valve (3) is fixedly connected to a filter sleeve (5), the filter sleeve (5) is provided with a replacement component inside, and the end of the filter sleeve (5) away from the connecting pipe (4) is fixedly connected to an oxygen supply pipe (6). An adjustment component is used to automatically and dynamically adjust the oxygen supply according to the needs of the aircraft crew. The adjustment component is connected to the oxygen connection valve (3) and the oxygen supply pipe (6). The regulating assembly includes an regulating ring (20) fixedly installed inside the oxygen connecting valve (3). The oxygen connecting valve (3) is rotatably connected to a bidirectional threaded sleeve (17). The bidirectional threaded sleeve (17) has two threaded rods (18) connected inside by threads. The two threaded rods (18) are arranged in a mirror symmetrical manner. An regulating block (19) is fixedly connected to the end of each threaded rod (18) away from the bidirectional threaded sleeve (17).

2. The oxygen supply system for an aircraft according to claim 1, characterized in that, The adjustment assembly also includes a first diversion pipe (7) fixedly installed on the outer wall of the oxygen supply pipe (6). An exhaust pipe (8) is fixedly connected to the outer wall of the first diversion pipe (7). The outer walls of the filter sleeve (5), oxygen supply pipe (6), first diversion pipe (7) and exhaust pipe (8) are fitted with protective shells (9). The number of protective shells (9) is set to two, and the two protective shells (9) are fixedly connected by threads.

3. An aircraft oxygen supply system according to claim 2, characterized in that, A sealing block (10) is slidably connected inside the first diversion pipe (7). A pressure spring (11) is fixedly installed on one side of the sealing block (10). The end of the pressure spring (11) away from the sealing block (10) is fixedly installed inside the first diversion pipe (7). A connecting rod (12) is fixedly connected to the side of the sealing block (10) near the pressure spring (11). The end of the connecting rod (12) away from the sealing block (10) passes through the first diversion pipe (7) and the protective shell (9) and is fixedly connected to a hinge (15).

4. An aircraft oxygen supply system according to claim 3, characterized in that, The adjusting block (19) is slidably connected inside the oxygen connecting valve (3). The outer wall of the bidirectional threaded sleeve (17) is fixedly connected to the hinge block (16). The hinge (15) is hinged to the outer wall of the hinge block (16). The outer wall of the hinge (15) is slidably connected to the connecting pipe (13). The connecting pipe (13) is sleeved on the outer wall of the connecting rod (12). The connecting pipe (13) is fixedly connected to one side of the oxygen connecting valve (3).

5. An aircraft oxygen supply system according to claim 2, characterized in that, The replacement component includes a sliding sleeve (22) slidably connected inside the filter sleeve (5), a compression spring (21) fixedly installed between the sliding sleeve (22) and the filter sleeve (5), a first filter (23) inserted inside the sliding sleeve (22), a second diversion pipe (24) fixedly connected to the outer wall of the oxygen supply pipe (6), and a placement sleeve (25) fixedly connected to the end of the second diversion pipe (24) away from the oxygen supply pipe (6).

6. An aircraft oxygen supply system according to claim 5, characterized in that, The placement sleeve (25) is slidably connected to a push plate (26). The push plate (26) is provided with multiple second filter elements (27) on the side away from the second diversion pipe (24). The filter sleeve (5) of the second filter element (27) is provided with a storage cavity (28) on the side away from the placement sleeve (25). The placement sleeve (25) and the storage cavity (28) are both locked between two protective shells (9).

7. An aircraft oxygen supply system according to claim 6, characterized in that, One of the second filter elements (27) is provided with a pusher (29) on one side. The inner rod of the telescopic rod (30) is fixedly connected to the outer wall of the pusher (29). The outer rod of the telescopic rod (30) is slidably connected to the inside of the protective shell (9). A storage spring (31) is fixedly installed between the inner rod and the outer rod of the telescopic rod (30).

8. An aircraft oxygen supply system according to claim 7, characterized in that, A first rack (32) is fixedly installed on one side of the outer rod of the telescopic rod (30). The outer wall of the first rack (32) is meshed with a large gear of a double-layer gear (33). The double-layer gear (33) is rotatably connected to the inside of the protective shell (9). The double-layer gear (33) is rotatably connected to the inside of the filter sleeve (5). A second rack (34) is provided inside the sliding sleeve (22). The second rack (34) meshes with the small gear of the double-layer gear (33). A replacement groove (35) is provided on the outer wall of the filter sleeve (5).

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