Propellant management device and aircraft meeting ultra-large flow conditions

Abstract

The present invention provides a propellant management device and aircraft that meet ultra-large flow conditions. The propellant management device that meets ultra-large flow conditions includes a first filter structure and a second filter structure; the first filter structure includes a lower head assembly, an upper column segment assembly, and an upper head assembly; the second filter structure is installed in the first filter structure; the lower head assembly includes an inlet filter section and a liquid outlet; the second filter structure includes an inner cone assembly, a lower column segment assembly, and a connecting pipe; the inner cone assembly and the lower column segment assembly divide the first filter structure into a first area, a second area, and a third area; the first area and the third area are connected through a connecting pipe; the present invention connects the first area and the third area through a connecting pipe, realizes the parallel connection of the inner cone assembly and the lower column segment assembly, increases the screen area through which the propellant passes, and can meet the discharge requirements of the tank under ultra-large flow conditions.

Description

Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to a propellant management device and an aircraft that meet ultra-large flow conditions. Background Art

[0002] Surface tension tanks utilize the surface tension of liquids to manage propellant. They offer high reliability, long life, and low weight, making them the preferred solution for liquid propulsion systems. The core technology of surface tension tanks lies in their internal propellant management system, which ensures that the propellant within the tank is delivered reliably and without air inclusion to the downstream engine under the pressure of upstream pressure in a microgravity environment.

[0003] In order to ensure that the tank outputs propellant without entrained gas under any circumstances, regardless of whether it is a mesh structure or a plate structure, a layer of screen structure is generally set near the liquid outlet, using the characteristics of the screen to prevent the gas that may be brought in from flowing downstream.

[0004] At present, the maximum volume of the surface tension tank in the domestic attitude and orbit control field does not exceed 2000L, and the discharge flow rate is no more than 200ml / s, so generally a small-area screen structure is arranged at the liquid outlet to meet the discharge requirements of flow resistance.

[0005] In recent years, with the rapid development of applications in satellites, ships, and spacecraft, the demand for surface tension tanks has increased significantly, particularly in response to increasing discharge flow rates, reaching 2.5 to 13.5 L / s, far exceeding those of conventional surface tension tanks. This has also created significant challenges in the design of propellant management systems for surface tension tanks, requiring the deployment of large-scale screen structures to meet these high-flow discharge requirements. However, an inadequate screen area is unable to withstand the impact of the high propellant flow rate, resulting in either screen damage or excessive discharge resistance, leading to reduced or even ineffective discharge performance.

[0006] Patent document CN104691786B discloses a propellant management device for a propellant tank, comprising a central pillar, guide vanes, pillar vanes, large vanes, liquid storage vanes, an upper pressure plate, an upper mesh sheet, an upper support plate, a small cylinder, a frame, a lower pressure plate, a lower mesh sheet, and a lower support plate. The guide vanes, pillar vanes, and large vanes are radially fixed to the central pillar to form an integral structure. The integral structure is fixed to the upper pressure plate via the central pillar. The pillar vanes and large vanes are mounted in the same plane, and the guide vane mounting plane forms a predetermined angle with the large vane mounting plane. The liquid storage vanes are radially fixed to the upper pressure plate. The upper pressure plate, mesh sheet, upper support plate, small cylinder, frame, lower pressure plate, lower mesh sheet, and lower support plate are fixedly mounted in order from top to bottom to form an integral structure, i.e., a liquid storage assembly. This invention suppresses liquid sloshing and has a wide range of in-orbit applications. However, this invention still does not meet the requirements for use in ultra-high flow conditions. Summary of the Invention

[0007] In view of the defects in the prior art, the purpose of the present invention is to provide a propellant management device and aircraft that meet ultra-large flow conditions.

[0008] According to the present invention, a propellant management device that meets ultra-large flow conditions includes a first filtering structure and a second filtering structure;

[0009] The first filtering structure includes a lower head assembly, an upper column segment assembly, and an upper head assembly;

[0010] The second filter structure is installed in the first filter structure;

[0011] The lower head assembly includes an inlet filter section and a liquid outlet;

[0012] The propellant can enter the first filter structure through the inlet filter section in the lower head assembly and the upper column section assembly, and then flow out of the management device through the liquid outlet in the lower head assembly after passing through the second filter structure;

[0013] The ultra-large flow rate means that the propellant flow rate meets the requirement of 2.5~13.5L / s.

[0014] Preferably, the second filtering structure includes an inner cone component, a lower column segment component and a connecting pipe;

[0015] The inner cone assembly and the lower column segment assembly divide the first filter structure into a first area, a second area, and a third area;

[0016] The first area is connected to the third area via a connecting pipe;

[0017] After the propellant enters the interior of the first filter structure, it flows into the liquid outlet in the lower head assembly through the second area, and then flows out of the management device.

[0018] Preferably, the inlet filtration section includes a lower head frame, a lower head pressure plate and a lower head screen;

[0019] The lower head screen is installed between the lower head frame and the lower head pressure plate.

[0020] Preferably, the inner cone assembly includes an inner cone pressure plate, an inner cone screen and an inner cone frame;

[0021] The inner cone screen is installed between the inner cone pressure plate and the inner cone frame;

[0022] The connecting pipe is installed on the inner cone frame.

[0023] Preferably, the lower column section assembly includes a lower column section pressure plate, a lower column section screen and a lower column section frame;

[0024] The lower column section screen is installed between the lower column section pressure plate and the lower column section frame.

[0025] Preferably, the upper column section assembly includes an upper column section inner tube, an upper column section outer tube and an upper column section screen;

[0026] The upper column section screen is installed between the upper column section inner tube and the upper column section outer tube.

[0027] Preferably, the upper head assembly includes a louver pressing plate, a louver screen, a louver frame and an upper head frame;

[0028] The louver screen is installed on the louver pressing plate, the louver pressing plate is fastened to the louver frame, and the louver frame is fastened to the upper head frame.

[0029] Preferably, an ear structure is provided on the lower head frame.

[0030] Preferably, the taper of the inner cone assembly and the taper of the lower end surface of the lower head frame are 0-3 degrees.

[0031] According to an aircraft provided by the present invention, the propellant management device that meets the ultra-large flow condition is adopted.

[0032] Compared with the prior art, the present invention has the following beneficial effects:

[0033] 1. The present invention connects the first area and the third area through a connecting pipe, realizes the parallel connection of the inner cone assembly and the lower column section assembly, increases the screen area through which the propellant passes, and can meet the discharge requirements of the tank under ultra-large flow conditions.

[0034] 2. The present invention designs an outer mesh and an inner mesh structure. By setting up a double-layer mesh structure and a redundant structure design, the single-point failure failure of the single-layer screen structure of the storage tank is avoided. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0036] Figure 1 It is a schematic diagram of the overall axial section of the present invention;

[0037] Figure 2 It is a top view schematic diagram of the lower head skeleton of the present invention;

[0038] Figure 3 It is a schematic axial cross-sectional view of the lower head assembly of the present invention;

[0039] Figure 4 is a schematic axial cross-sectional view of the inner cone assembly of the present invention;

[0040] Figure 5 is a schematic axial cross-sectional view of the lower column segment assembly of the present invention;

[0041] Figure 6 It is a structural schematic diagram of the upper column segment assembly of the present invention;

[0042] Figure 7 for Figure 6 Schematic diagram of the axial section at point A;

[0043] Figure 8 It is a schematic diagram of the upper head assembly of the present invention;

[0044] Figure 9 for Figure 8 Schematic diagram of the axial section at point B.

[0045] The figure shows:

[0046] DETAILED DESCRIPTION

[0047] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0048] The present invention provides a propellant management device that meets ultra-large flow conditions, such as Figure 1-9As shown, it includes a first filter structure 100 and a second filter structure 200. In a preferred embodiment, the first filter structure 100 and the second filter structure 200 are the inner layer net and the outer layer net respectively. The space between the inner layer net and the outer layer net is the management volume.

[0049] The first filter structure 100 includes a lower head assembly 1, an upper column assembly 4, and an upper head assembly 5; the second filter structure 200 is installed within the first filter structure 100; the lower head assembly 1 includes an inlet filter section 14 and a liquid outlet 15; the propellant can enter the interior of the first filter structure through the inlet filter section 14 and the upper column assembly 4 in the lower head assembly 1, and then flow out of the management device through the liquid outlet in the lower head assembly 1 after passing through the second filter structure; the maximum flow rate is the propellant flow rate meeting the requirement of 2.5 to 13.5 L / s. The second filter structure 200 is arranged near the liquid outlet 15.

[0050] The second filter structure includes an inner cone component 2, a lower column segment component 3 and a connecting pipe 24; the inner cone component 2 and the lower column segment component 3 divide the first filter structure 100 into a first area 300, a second area 400 and a third area 500; the first area 300 is connected to the third area 500 through the connecting pipe 24; after the propellant enters the first filter structure 100, it flows into the liquid outlet 15 in the lower head component 1 through the second area 400, and then flows out of the management device.

[0051] The inlet filtration section 14 includes a lower head frame 11, a lower head pressure plate 12, and a lower head screen 13; the lower head screen 13 is installed between the lower head frame 11 and the lower head pressure plate 12. In a preferred embodiment, the portion of the lower head frame 11 within the second region 400 is provided with circumferential holes, with a size of Ø10-Ø20 mm and a number of 4-8 holes. The propellant flows into the liquid outlet 15 through these circumferential holes.

[0052] The inner cone assembly 2 includes an inner cone pressure plate 21, an inner cone screen 22, and an inner cone frame 23. The inner cone screen 22 is installed between the inner cone pressure plate 21 and the inner cone frame 23. The connecting tubes 24 are installed on the inner cone frame 23. The diameter of the connecting tubes 24 ranges from 20 to 30 mm, and there are 8 to 24 connecting tubes 24 distributed along the circumference of the first filter structure 100. The taper of the inner cone assembly 2 and the lower end surface of the lower head frame 11 are 0 to 3 degrees. The minimum distance between the inner cone assembly 2 and the lower head frame 11 is 6 to 10 mm.

[0053] The lower column section assembly 3 includes a lower column section pressing plate 31 , a lower column section screen 32 and a lower column section skeleton 33 ; the lower column section screen 32 is installed between the lower column section pressing plate 31 and the lower column section skeleton 33 .

[0054] The upper column section assembly 4 includes an upper column section inner tube 41 , an upper column section outer tube 42 and an upper column section screen 43 ; the upper column section screen 43 is installed between the upper column section inner tube 41 and the upper column section outer tube 42 .

[0055] The upper head assembly 5 includes an air window pressure plate 51, an air window screen 52, an air window frame 53 and an upper head frame 54; the air window screen 52 is installed on the air window pressure plate 51, the air window pressure plate 51 is fastened to the air window frame 53, and the air window frame 53 is fastened to the upper head frame 54.

[0056] In a preferred example, an ear structure 111 is provided on the lower head skeleton 11; in another preferred example, the lower head skeleton 11 itself is a porous flange ear structure, the number of flange ears is 8 to 32, and the axis of the flange hole is 6 to 12 mm away from the outer diameter of the upper column section outer tube 42; the size of the hole is Ø6 to Ø12 mm, and the distance between the holes is 2 to 3 mm.

[0057] When in use, the propellant management device that meets the ultra-large flow conditions needs to be installed on the lower shell of the tank. Specifically, the lower end surface of the lower head frame 11 is designed according to the shape of the lower shell of the tank, and the distance between the lower end surface and the inner wall surface of the lower shell of the tank is 4~10mm.

[0058] It's worth noting that if the screen area is increased solely to meet high flow requirements, conventional design principles can be achieved by increasing the size of the management device. However, this approach presents two drawbacks: First, a large management device increases the weight of the tank, which contradicts the current trend of lightweight tanks. Second, a large management device designed to fit the tank shell shape can meet the flow and resistance matching requirements when the liquid level completely covers the management device during ultra-high flow discharge. However, as the liquid level gradually decreases, the screen area exposed to the propellant decreases, the flow and resistance matching becomes increasingly poor, and ultimately leads to discharge failure. Neither of these two approaches is optimal, and the design of the present invention overcomes these shortcomings.

[0059] The principle of the present invention is as follows: taking the propellant entering from the lower head assembly 1 as an example, since the first area 300 and the third area 500 are connected by the connecting pipe 24, the propellant in the first area 300 and the third area 500 can flow between the first area 300 and the third area 500 through the connecting pipe 24, that is, a part of the propellant can flow from the first area 300 through the inner cone assembly 2 into the second area 400, and the other part of the propellant can also flow from the first area 300 into the third area 500 and then flow into the second area 400 through the lower column segment assembly 3. In this way, the inner cone assembly 2 and the lower column segment assembly 3 are connected in parallel with each other, and the fluid can enter the second area 400 from the inner cone assembly 2 and the lower column segment assembly 3 respectively at the same time, and the inner cone assembly 2 and the lower column segment assembly 3 respectively include screens, that is, the present invention increases the screen area passed by the propellant by connecting the inner cone assembly 2 and the lower column segment assembly 3 in parallel. The same principle applies to the propellant entering from the lower upper column segment assembly 4. Due to the design of the connecting pipe 24, the fluid can enter the second area 400 from the inner cone assembly 2 and the lower column segment assembly 3 at the same time, increasing the screen area passed by the propellant.

[0060] In addition, the present invention provides an ultra-large area screen structure near the liquid outlet 15, that is, the second filter structure 200 is provided at the lower part of the first filter structure 100, close to the liquid outlet 15. This allows the tank to output air-free propellant to the downstream with high reliability under ultra-large flow conditions, driven by the upstream gas pressure throughout the entire process.

[0061] In the present invention, in order to meet the discharge requirements of ultra-large flow conditions, the screen structures are arranged near the liquid outlet, and the first area 300 is connected to the third area 500 through the connecting pipe 24, realizing the parallel connection of the inner cone assembly 2 and the lower column section assembly 3, which can meet the discharge requirements of the storage tank under ultra-large flow conditions. The reasonable arrangement of the screen structure of the channel of the present invention can design the sum of the screen areas of the inner cone assembly 2 and the lower column section assembly 3 to be more than 200,000 mm2, which can greatly reduce the discharge flow rate per unit screen area, so that the ultra-large flow resistance matching meets the performance index. In addition, the present invention designs the outer mesh and inner mesh structure, and the mesh areas of the outer mesh and the inner mesh can both meet the ultra-large flow resistance matching index. By setting up a double-layer mesh structure and a redundant structure design, the single-point failure failure of the single-layer screen structure of the storage tank is avoided.

[0062] This invention breaks through conventional screen structure design concepts and designs a propellant management device that meets ultra-high flow rate requirements. It can meet the high-flow discharge requirements of tanks used in aerospace applications such as satellites, spacecraft, and space stations. By installing an ultra-large screen structure near the liquid outlet, this invention ensures that, under ultra-high flow conditions, the tank can continuously discharge air-free propellant downstream, driven by upstream gas pressure. This device can be used as a propellant management device for tanks in aerospace products such as satellites, spacecraft, and space stations.

[0063] The assembly process of the present invention is as follows:

[0064] First, the inner cone assembly 2 and the lower head assembly 1 are welded and fixed in two inner and outer circles, then the lower column segment assembly 3 is welded, and then the upper column segment assembly 4 is connected and welded, and finally the upper head assembly 5 is welded and fixed.

[0065] like Figure 3 The figure shows the connection structure of the lower head assembly 1 of the present invention. The installation process of the lower head assembly is as follows: first, weld the lower head screen 13 to the lower head pressure plate 12. After passing the performance test, connect and fix it to the lower head frame 11 by welding.

[0066] like Figure 4 As shown, the connection structure of the inner cone component 2 of the present invention, the installation process of the inner cone component 2 is as follows: first, the inner cone screen 22 is welded to the inner cone pressure plate 21, and after the performance test is passed, the whole is welded and fixed to the inner cone frame 23, and finally, the 12 connecting pipes 24 are fixed to the inner cone frame 23 by welding.

[0067] like Figure 5 As shown, the connection structure of the lower column section assembly 3 of the present invention is as follows: first, the lower column section screen 32 is welded to the lower column section pressure plate 31. After the performance test is passed, the whole is welded to the lower column section frame 33.

[0068] like Figure 6-7 As shown, the connection structure of the upper column section assembly 4 of the present invention, the installation process of the upper column section assembly 4 is as follows: first, the upper column section screen 43 is welded to the upper column section inner tube 41, and after the performance test is passed, it is assembled with the upper column section outer tube 42 without welding and fixing.

[0069] like Figure 8-9 As shown, the connection structure of the upper column section assembly of the present invention, the installation process of the upper head assembly 5 is as follows: there are two air vent pressure plates 51, first the air vent screen 52 is welded to one of the air vent pressure plates 51, after the performance test is passed, the other air vent pressure plate 51 is formed into a "sandwich" and then welded to the air vent frame 53, and finally the whole head frame 54 is connected and fixed, and the fixing form is welding.

[0070] The present invention also provides an aircraft, which adopts the propellant management device that meets the ultra-large flow condition.

[0071] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and 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, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0072] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A propellant management device that meets ultra-large flow conditions, characterized in that: It comprises a first filtering structure (100) and a second filtering structure (200); The first filtering structure (100) comprises a lower head assembly (1), an upper column segment assembly (4), and an upper head assembly (5); The second filtering structure (200) is installed in the first filtering structure (100); The lower head assembly (1) comprises an inlet filter section (14) and a liquid outlet (15); The propellant can enter the interior of the first filter structure (100) through the inlet filter section (14) in the lower head assembly (1) and the upper column section assembly (4), and then flow out of the management device through the liquid outlet (15) in the lower head assembly (1) after passing through the second filter structure (200); Ultra-large flow rate means the propellant flow rate meets the requirement of 2.5~13.5L / s; The second filtering structure comprises an inner cone component (2), a lower column segment component (3), and a connecting pipe (24); The inner cone component (2) and the lower column segment component (3) divide the first filter structure (100) into a first area (300), a second area (400) and a third area (500); The first area (300) is connected to the third area (500) via a connecting pipe (24); After the propellant enters the interior of the first filter structure (100), it flows through the second area (400) into the liquid outlet (15) in the lower head assembly (1), thereby flowing out of the management device; The inlet filter section (14) comprises a lower head frame (11), a lower head pressure plate (12), and a lower head screen (13); The lower head screen (13) is installed between the lower head frame (11) and the lower head pressure plate (12).

2. The propellant management device that meets ultra-large flow conditions according to claim 1 is characterized in that: The inner cone assembly (2) comprises an inner cone pressure plate (21), an inner cone screen (22) and an inner cone frame (23); The inner cone screen (22) is installed between the inner cone pressure plate (21) and the inner cone frame (23); The connecting pipe (24) is mounted on the inner cone frame (23).

3. The propellant management device that meets ultra-large flow conditions according to claim 1 is characterized in that: The lower column section assembly (3) comprises a lower column section pressing plate (31), a lower column section screen (32) and a lower column section frame (33); The lower column section screen (32) is installed between the lower column section pressing plate (31) and the lower column section frame (33).

4. The propellant management device that meets ultra-large flow conditions according to claim 1 is characterized in that: The upper column section assembly (4) comprises an upper column section inner cylinder (41), an upper column section outer cylinder (42), and an upper column section screen (43); The upper column section screen (43) is installed between the upper column section inner tube (41) and the upper column section outer tube (42).

5. The propellant management device that meets ultra-large flow conditions according to claim 1 is characterized in that: The upper head assembly (5) comprises an air window pressure plate (51), an air window screen (52), an air window frame (53) and an upper head frame (54); The air window screen (52) is mounted on the air window pressing plate (51), the air window pressing plate (51) is fastened to the air window frame (53), and the air window frame (53) is fastened to the upper head frame (54).

6. The propellant management device that meets ultra-large flow conditions according to claim 1 is characterized in that: The lower head frame (11) is provided with a lug structure (111).

7. The propellant management device that meets ultra-large flow conditions according to claim 1 is characterized in that: The taper of the inner cone assembly (2) and the taper of the lower end surface of the lower head frame (11) are 0-3 degrees.

8. An aircraft, characterized in that: A propellant management device that meets ultra-large flow conditions is adopted as described in any one of claims 1 to 7.

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