Integrated light-weight high-pressure gas supply module and aircraft

Abstract

The invention provides an integrated light-weight high-pressure gas supply module and an aircraft. The integrated light-weight high-pressure gas supply module comprises a composite gas cylinder, a skirt flange, an inflation valve, an electric explosion valve and a pipeline assembly. The skirt flange comprises a flange main body and a mounting part, the flange main body sleeves the outer side of a column section of the composite material gas cylinder and is fixedly connected with the composite material gas cylinder, the mounting part covers the upper end surface of the composite material gas cylinder, and the inflation valve and the electric explosion valve are integrated on the mounting part; a filler neck of the composite gas cylinder is connected with one end of the inflation valve and one end of the electric explosion valve through the pipeline assembly, the other end of the inflation valve is connected with an external gas source, and the other end of the electric explosion valve is connected with the aircraft. The skirt flange type composite gas cylinder is adopted, compared with a conventional strap type or two-end fixing installation mode, the integration degree of the installation structure and the gas cylinder is high, the radial design space is greatly saved, installation and fixation with a cabin are facilitated, the skirt flange can absorb radial deformation after the gas cylinder is pressurized, the structural rigidity and strength are better, and the mechanical reliability is high.

Description

Technical Field

[0001] This invention relates to the field of aircraft air supply system technology, specifically to an integrated lightweight high-pressure air supply module and an aircraft. Background Technology

[0002] High-pressure gas supply modules, as devices for storing and managing gases, are widely used in the aerospace field. A typical gas supply module consists of high-pressure gas cylinders, filling valves, electro-explosive valves, and piping, and its main function is to provide the system with the required high-pressure gas source. With the technological development of small aircraft, the demand for miniaturization, integration, and lightweight onboard gas supply devices is becoming increasingly urgent. Traditional independent component design approaches cannot meet the space constraints of onboard aircraft.

[0003] Patent document CN210088465U discloses an integrated gas source assembly that integrates gas sources, valves, and sensors distributed in pipelines into a single unit, achieving multiple functions such as two-stage pressure reduction, gas path shutdown control, safety protection, and pressure monitoring within a single product. However, this gas source assembly still has room for optimization in terms of radial and axial dimensions. Therefore, there is an urgent need in the art for an integrated, lightweight, high-pressure gas supply module that can meet the requirements of miniaturization, integration, and lightweight design. Summary of the Invention

[0004] In view of the deficiencies in the prior art, the purpose of this invention is to provide an integrated lightweight high-pressure air supply module and an aircraft.

[0005] The integrated lightweight high-pressure gas supply module provided by the present invention includes a composite material gas cylinder, a skirted flange, a filling valve, an electric explosion valve, and a pipeline assembly. The skirt flange includes a flange body and an installation part. The flange body is sleeved on the outside of the composite gas cylinder column section and is fixedly connected to the composite gas cylinder. The installation part covers the upper end face of the composite gas cylinder. The inflation valve and the electric explosion valve are both integrated on the installation part. The nozzle of the composite material gas cylinder is connected to one end of the inflation valve and one end of the electric explosion valve through a pipeline assembly. The other end of the inflation valve is connected to an external gas source, and the other end of the electric explosion valve is connected to the aircraft.

[0006] Preferably, the composite gas cylinder includes an inner liner, a composite winding layer, a flange winding layer, a gas port, a connecting nozzle, and a process base; The composite material winding layer covers the outside of the inner liner, the flange body of the skirt flange is sleeved on the outside of the composite material winding layer column section, the flange winding layer covers the outside of the lower end of the flange body, and the process base is set in the inner liner. The air inlet is installed on the top of the liner, and the connecting nozzle is installed on the air inlet. The outer edge of the air inlet has a boss, and the middle part of the skirt flange mounting part has an opening that is sleeved on the outside of the air inlet. The inner edge of the opening is fixedly installed on the boss.

[0007] Preferably, a spring washer is provided between the upper surface of the boss of the air port and the inner edge of the opening in the middle of the skirt flange.

[0008] Preferably, the air port has an external thread section, on which a locking nut is fitted, and the inner edge of the skirt flange opening is fixed to the boss of the air port by the locking nut.

[0009] Preferably, the material of the liner is one of pure titanium TA1, TA2 and titanium alloy TC4. The liner is integrally formed by stamping, spinning or machining, or by welding the upper and lower shells together.

[0010] Preferably, the piping assembly includes a first pipe, a tee connector, a second pipe, a third pipe, and a fourth pipe; One end of the first pipeline is connected to the connecting nozzle, and the other end of the first pipeline is connected to the first interface of the tee connector. One end of the second pipeline is connected to the second interface of the tee connector, and the other end of the second pipeline is connected to the inflation valve. One end of the third pipeline is connected to the third interface of the tee connector, and the other end of the third pipeline is connected to the inlet of the electric explosion valve. One end of the fourth pipeline is connected to the outlet of the electric explosion valve, and the other end of the fourth pipeline is connected to the overall interface of the aircraft.

[0011] Preferably, the inflation valve, the electric explosion valve, and the piping components do not protrude beyond the outer edge of the skirt flange on the projection along the axial direction of the composite gas cylinder.

[0012] Preferably, on the radial projection of the composite gas cylinder, the pipe connection end of the nozzle extends in a direction perpendicular to the axial direction of the composite gas cylinder.

[0013] Preferably, the skirt flange has multiple radial threaded holes along its circumferential direction on its flange body, and the skirt flange is connected to the aircraft cabin through the radial threaded holes.

[0014] The aircraft provided by the present invention employs the aforementioned integrated lightweight high-pressure air supply module.

[0015] Compared with the prior art, the present invention has the following beneficial effects: 1. The present invention has a simple structure and adopts a skirted flange type composite material gas cylinder. Compared with the conventional clamp type or fixed at both ends installation form, on the one hand, the installation structure has a high degree of integration with the gas cylinder, which greatly saves radial design space and is also easy to install and fix with the cabin. On the other hand, the skirt flange can absorb the radial deformation after the gas cylinder is pressurized, and at the same time, the structural rigidity and strength are better and the mechanical reliability is high.

[0016] 2. This invention integrates the installation of valves and pipelines onto the composite material gas cylinder skirt flange. The skirt flange provides a docking interface between the gas cylinder and the cabin, and an installation interface for valves and pipelines. At the same time, considering the axial deformation after the gas cylinder is pressurized, a flexible limiting structure is designed at the joint between the gas port and the skirt flange, which optimizes the spatial layout of the product, reduces the complexity of the pipeline, and makes the entire device compact and highly integrated.

[0017] 3. The gas cylinder in this invention adopts a right-angle through-type nozzle design, which greatly reduces the height of the gas cylinder, optimizes the space in the height direction, and has a high axial space utilization rate. Attached Figure Description

[0018] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the structure of the present invention from a top view angle; Figure 3 This is a cross-sectional schematic diagram of the composite material gas cylinder in this invention.

[0019] The diagram shows: Detailed Implementation

[0020] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0021] This invention discloses an integrated lightweight high-pressure gas supply module and aircraft, which adopts a skirt flange type composite material gas cylinder. Compared with the conventional clamp type or fixed at both ends installation, on the one hand, the installation structure has a high degree of integration with the gas cylinder, which greatly saves radial design space and is also easy to install and fix with the cabin. On the other hand, the skirt flange can absorb the radial deformation after the gas cylinder is pressurized, and at the same time, the structure has better rigidity and strength, and higher mechanical reliability.

[0022] The integrated lightweight high-pressure gas supply module provided by the present invention, such as Figure 1 , Figure 2 As shown, the system includes a composite material gas cylinder 1, a skirt flange 14, an inflation valve 2, an electric explosion valve 3, and a piping assembly 4. The skirt flange 14 includes a flange body and an mounting part. The flange body is fitted onto the outside of the column section of the composite material gas cylinder 1 and is fixedly connected to the composite material gas cylinder 1. The mounting part covers the upper end face of the composite material gas cylinder 1. The inflation valve 2 and the electric explosion valve 3 are both integrated on the mounting part. The inlet 18 of the composite material gas cylinder 1 is connected to one end of the inflation valve 2 and one end of the electric explosion valve 3 through the piping assembly 4. The other end of the inflation valve 2 is connected to an external gas source, and the other end of the electric explosion valve 3 is connected to the aircraft. The skirt flange 14 has multiple radial threaded holes 141 arranged circumferentially on its flange body, and the skirt flange 14 is connected to the aircraft cabin through the radial threaded holes 141.

[0023] like Figure 3 As shown, the composite gas cylinder 1 includes an inner liner 11, a composite winding layer 12, a flange winding layer 13, a gas port 15, a connecting nozzle 18, and a process base 19. The composite winding layer 12 covers the outside of the inner liner 11, the flange body of the skirt flange 14 is sleeved on the outside of the column section of the composite winding layer 12, the flange winding layer 13 covers the lower outer side of the flange body, and the process base 19 is located at the bottom of the inner liner 11. The gas port 15 is installed on the top of the inner liner 11, the connecting nozzle 18 is installed on the gas port 15, the outer edge of the gas port 15 has a boss, the middle part of the skirt flange 14 has an opening, which is sleeved on the outside of the gas port 15, and the inner edge of the opening is fixedly installed on the boss. Considering the axial deformation after the gas cylinder is pressurized, a spring washer 16 is provided between the upper surface of the boss of the gas port 15 and the inner edge of the opening in the middle of the skirt flange 14. The air port 15 has an external thread section, on which a locking nut 17 is fitted. The inner edge of the opening of the skirt flange 14 is fixed to the boss of the air port 15 by the locking nut 17.

[0024] Piping assembly 4 includes a first pipe 41, a tee connector 42, a second pipe 43, a third pipe 44, and a fourth pipe 45; one end of the first pipe 41 is connected to the connecting nozzle 18, and the other end of the first pipe 41 is connected to the first interface of the tee connector 42; one end of the second pipe 43 is connected to the second interface of the tee connector 42, and the other end of the second pipe 43 is connected to the inflation valve 2; one end of the third pipe 44 is connected to the third interface of the tee connector 42, and the other end of the third pipe 44 is connected to the inlet of the electric explosion valve 3; one end of the fourth pipe 45 is connected to the outlet of the electric explosion valve 3, and the other end of the fourth pipe 45 is connected to the overall interface of the aircraft.

[0025] like Figure 2As shown, on the projection along the axial direction of the composite gas cylinder 1, the inflation valve 2, the electric explosion valve 3, and the pipeline assembly 4 do not protrude beyond the outer edge of the skirt flange 14. This design greatly saves radial design space and facilitates installation and fixation with the cabin. On the radial projection of the composite gas cylinder 1, the pipeline connection end of the connecting nozzle 18 extends in a direction perpendicular to the axial direction of the composite gas cylinder 1. This design greatly reduces the height of the gas cylinder and optimizes the space in the height direction.

[0026] Example 1 like Figures 1-3 As shown, this embodiment discloses an integrated lightweight high-pressure gas supply module, including a composite material gas cylinder 1, a skirt flange 14 integrated on the outside of the column section of the composite material gas cylinder 1, an inflation valve 2, an electric explosion valve 3, and a pipeline assembly 4 installed on the skirt flange 14. The composite material gas cylinder 1 consists of an inner liner 11, a composite material winding layer 12, a flange winding layer 13, a skirt flange 14, a gas port 15, a spring washer 16, a locking nut 17, a connecting nozzle 18, and a process base 19. The composite material winding layer 12 wraps around the inner liner 11; the skirt flange 14 is fitted onto the outside of the composite material winding layer 12; the flange winding layer 13 wraps around the skirt flange 14; the inner liner 11 and the gas port 15 are connected; the spring washer 16 is fitted onto the boss of the gas port 15; the upper opening of the skirt flange 14 is fitted onto the boss of the gas port 15 and contacts the spring washer 16; the locking nut 17 is tightened through the thread of the gas port 15; and the connecting nozzle 18 is connected to the gas port 15. The first pipeline 41 is connected at one end to the connecting nozzle 18 on the composite material gas cylinder 1, and at the other end to the tee connector 42; the second pipeline 43 is connected at one end to the tee connector 42, and at the other end to the inflation valve 2; the third pipeline 44 is connected at one end to the tee connector 42, and at the other end to the inlet of the electric explosion valve 3; the fourth pipeline 45 is connected at one end to the outlet of the electric explosion valve 3, and at the other end to the overall interface. The gas supply module is connected to the aircraft structural cabin through multiple radial threaded holes 141 on the skirt flange 14. When the gas supply module is being filled, high-pressure gas is injected into the composite material gas cylinder 1 through the inflation valve 2. When the gas supply module is working, the electric detonator on the electric explosion valve 3 detonates, creating a passage between the high-pressure gas in the composite material gas cylinder 1 and the downstream fourth pipeline 45, supplying high-pressure gas to the aircraft.

[0027] Specifically, in this embodiment, the inner liner 11 is made of one of pure titanium TA1, TA2, or titanium alloy TC4, and is integrally formed by stamping, spinning, and machining processes or by welding the upper and lower shells together.

[0028] Specifically, in this embodiment, the inner lining 11 adopts an ellipsoidal cylindrical structure or a spherical structure.

[0029] Specifically, in this embodiment, the basic wall thickness of the film region of the inner liner 11 is 0.5mm to 1.5mm.

[0030] Specifically, in this embodiment, the composite material winding layer 12 is made of one of the following carbon fibers: T1200, T1100, T1000, T800, and T700, which is impregnated with epoxy resin and then wound onto the inner liner 11, and then cured to form the final product.

[0031] Specifically, in this embodiment, the material of the skirt flange 14 is one of titanium alloy TC4, aluminum alloy 6061, aluminum alloy 2A14, or composite material.

[0032] Specifically, in this embodiment, the skirt flange 14 is bonded to the outside of the composite material winding layer 12, and the bonding gap between the two is 0.3mm to 0.5mm. The skirt flange 14 is provided with an overflow hole, a glue storage groove and a tightening groove.

[0033] Specifically, in this embodiment, the skirt flange 14 is provided with evenly distributed threaded holes around its circumference for connection with the cabin; the top plane of the skirt flange 14 is provided with mounting interfaces for the inflation valve 2, the electric explosion valve 3, and the pipeline assembly 4.

[0034] Specifically, in this embodiment, the flange winding layer 13 is made of one of the following grades of carbon fiber: T1200, T1100, T1000, T800, and T700. After being impregnated with epoxy resin, it is wound around the outside of the skirt flange 14 and then cured to form the desired shape.

[0035] Specifically, in this embodiment, the air vent 15 and the inner liner 11 are welded and sealed using electron beam welding or laser welding.

[0036] Specifically, in this embodiment, the material of the elastic pad 16 is either vacuum rubber or polyurethane, and its thickness is not less than twice the axial deformation of one side of the gas cylinder.

[0037] Specifically, in this embodiment, when the locking nut 17 is installed, the compression of the spring washer 16 is controlled to not exceed 10% of its thickness, and laser spot welding is used to prevent loosening after installation.

[0038] Specifically, in this embodiment, the air port 15 and the connecting nozzle 18 are welded and sealed using electron beam welding or laser welding.

[0039] Specifically, in this embodiment, the conduit in the pipeline assembly 4 is one of TA1 and TA2, and is sealed by argon arc welding.

[0040] The aircraft provided by the present invention employs the above-mentioned integrated lightweight high-pressure air supply module.

[0041] This invention employs a titanium-lined composite material gas cylinder design, resulting in a lightweight structure and high pressure-bearing reliability. Through integrated design, the composite material gas cylinder is combined with the mounting structure, which is designed as a skirt flange, making the entire device compact and maximizing radial space utilization. The radial mounting holes also facilitate docking with small aircraft cabins. The invention utilizes a welded right-angle through-type nozzle design, significantly reducing the cylinder height and maximizing axial space utilization. The invention employs a load-bearing gas cylinder design, leveraging the inherent rigidity of the cylinder to mount valves and pipelines on the skirt flange end face, achieving a centralized component layout and fulfilling the modular design concept. A flexible structure is incorporated at the junction of the gas cylinder and the skirt flange end face to accommodate axial deformation after cylinder pressurization.

[0042] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0043] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. An integrated lightweight high-pressure gas supply module, characterized in that, Includes composite material gas cylinder (1), skirt flange (14), filling valve (2), electric explosion valve (3) and pipeline assembly (4); The skirt flange (14) includes a flange body and an installation part. The flange body is sleeved on the outside of the column section of the composite gas cylinder (1) and is fixedly connected to the composite gas cylinder (1). The installation part covers the upper end face of the composite gas cylinder (1). The inflation valve (2) and the electric explosion valve (3) are both integrated on the installation part. The nozzle (18) of the composite gas cylinder (1) is connected to one end of the inflation valve (2) and one end of the electric explosion valve (3) respectively through the pipeline assembly (4). The other end of the inflation valve (2) is connected to an external gas source, and the other end of the electric explosion valve (3) is connected to the aircraft.

2. The integrated lightweight high-pressure gas supply module according to claim 1, characterized in that, The composite gas cylinder (1) includes an inner liner (11), a composite winding layer (12), a flange winding layer (13), a gas port (15), a connecting nozzle (18), and a process base (19). The composite material winding layer (12) covers the outside of the inner liner (11), the flange body of the skirt flange (14) is sleeved on the outside of the column section of the composite material winding layer (12), the flange winding layer (13) covers the outside of the lower end of the flange body, and the process base (19) is set at the bottom of the inner liner (11). The air inlet (15) is installed on the top of the liner (11), the connecting nozzle (18) is installed on the air inlet (15), the outer edge of the air inlet (15) has a boss, the middle part of the skirt flange (14) has an opening, which is sleeved on the outside of the air inlet (15), and the inner edge of the opening is fixedly installed on the boss.

3. The integrated lightweight high-pressure gas supply module according to claim 2, characterized in that, A spring pad (16) is provided between the upper surface of the boss of the air port (15) and the inner edge of the opening in the middle of the skirt flange (14).

4. The integrated lightweight high-pressure gas supply module according to claim 2, characterized in that, The air port (15) has an external thread section, on which a locking nut (17) is fitted. The inner edge of the opening of the skirt flange (14) is fixed to the boss of the air port (15) by the locking nut (17).

5. The integrated lightweight high-pressure gas supply module according to claim 2, characterized in that, The material of the inner liner (11) is one of pure titanium TA1, TA2 and titanium alloy TC4. The inner liner (11) is integrally formed by stamping, spinning or machining, or by welding the upper and lower shells.

6. The integrated lightweight high-pressure gas supply module according to claim 1, characterized in that, The pipeline assembly (4) includes a first pipeline (41), a tee connector (42), a second pipeline (43), a third pipeline (44), and a fourth pipeline (45). One end of the first pipe (41) is connected to the connecting nozzle (18), the other end of the first pipe (41) is connected to the first interface of the tee connector (42), one end of the second pipe (43) is connected to the second interface of the tee connector (42), and the other end of the second pipe (43) is connected to the inflation valve (2). One end of the third pipe (44) is connected to the third interface of the tee connector (42), and the other end of the third pipe (44) is connected to the inlet of the electric explosion valve (3). One end of the fourth pipe (45) is connected to the outlet of the electric explosion valve (3), and the other end of the fourth pipe (45) is connected to the overall interface of the aircraft.

7. The integrated lightweight high-pressure gas supply module according to claim 1, characterized in that, On the projection along the axial direction of the composite gas cylinder (1), the filling valve (2), the electric explosion valve (3), and the pipeline assembly (4) do not protrude beyond the outer edge of the skirt flange (14).

8. The integrated lightweight high-pressure gas supply module according to claim 1, characterized in that, On the radial projection of the composite gas cylinder (1), the pipe connection end of the nozzle (18) extends in a direction perpendicular to the axial direction of the composite gas cylinder (1).

9. The integrated lightweight high-pressure gas supply module according to claim 1, characterized in that, The skirt flange (14) has multiple radial threaded holes (141) arranged circumferentially on the flange body, and the skirt flange (14) is connected to the aircraft cabin through the radial threaded holes (141).

10. An aircraft, characterized in that, The integrated lightweight high-pressure gas supply module according to any one of claims 1-9 is adopted.

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