Propellant management device suitable for low-temperature storage tank of carrier rocket

Abstract

The invention provides a propellant management device suitable for a low-temperature storage tank of a carrier rocket. The propellant management device comprises a first storage assembly and a second storage assembly. The first storage assembly is provided with a first storage cavity, and the first storage cavity is provided with a first inflow filtering part and an outflow part; the second storage assembly is provided with a gathering cavity and a second storage cavity, and the second storage assembly is provided with a second inflow filtering part and an exhaust part; a gap communicated with the storage box is formed between the first storage assembly and the second storage assembly; in the sliding stage, the propellant is stored in the first storage cavity through the gap and the first inflow filtering part and stored in the gathering cavity and the second storage cavity through the second inflow filtering part. The first storage assembly and the second storage assembly are used for storing propellants at the same time, the storage space is increased, and the device can be suitable for a storage tank of a large-flow carrier rocket; and the first inflow filtering part can realize gas-liquid isolation, and filters the bubbles flowing into the first storage assembly, so that the bubbles are prevented from entering the first storage assembly.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a propellant management device suitable for a cryogenic tank of a launch vehicle. Background Art

[0002] The final stage of a large cryogenic launch vehicle usually needs to glide on orbit for a period of time, during which the final stage tank of the rocket is in a microgravity environment. In order to ensure that the launch vehicle has the ability to be started multiple times in a microgravity environment, a propellant management device is often used to solve the problem.

[0003] Specifically, the propellant management device is a structure that manages the propellant in the tank. It can control the distribution and position of the propellant to a certain extent, thereby achieving gas-liquid separation, ensuring that the propellant is discharged without entrained air, and ensuring the normal starting and operation of the engine.

[0004] However, existing propellant management devices are mainly used for small tanks and for conventional propellants. Compared with launch vehicles, satellite tanks are smaller in size and have a smaller propellant supply flow rate, so they cannot meet the needs of launch vehicles.

[0005] Therefore, there is an urgent need for a propellant management device suitable for a launch vehicle cryogenic tank to solve the technical problems existing in the prior art to a certain extent. Summary of the invention

[0006] The purpose of this application is to provide a propellant management device and an engine suitable for a launch vehicle cryogenic tank, which can increase the retention capacity to a certain extent and effectively isolate the gas. When the engine is restarted, the propellant retained by the management device can provide the engine with liquid-phase propellant without air entrainment, thereby ensuring reliable starting of the engine.

[0007] The present application provides a propellant management device applicable to a low-temperature tank of a launch vehicle, which is arranged at an outlet of the tank; the propellant management device applicable to a low-temperature tank of a launch vehicle comprises a first retention component and a second retention component;

[0008] The first storage assembly has a first storage chamber, and the first storage assembly has a first inflow filter portion communicating with the first storage chamber and an outflow portion communicating with the first storage chamber and an outflow port of the storage tank respectively and opposite to the first inflow filter portion;

[0009] The second storage assembly comprises a gathering chamber and a second storage chamber communicating with the gathering chamber, and the second storage assembly comprises a second inflow filter communicating with the gathering chamber and an exhaust portion communicating with the second storage chamber and opposite to the second inflow filter;

[0010] The first storage assembly and the second storage assembly are spaced apart and the first inlet filter portion and the second inlet filter portion are opposite to each other, so that a gap communicating with the storage tank is formed between the first storage assembly and the second storage assembly;

[0011] During the gliding stage, the propellant in the tank passes through the gap and is retained in the first retention chamber through the first inlet filter portion, and is sequentially retained in the gathering chamber and the second retention chamber through the second inlet filter portion; the first inlet filter portion and the second inlet filter portion are used to filter the gas in the propellant retained from the tank in the first retention component and the second retention component.

[0012] In the above technical solution, further, the first storage assembly includes a top plate and a first shell;

[0013] The top plate and the first housing surround the first storage chamber;

[0014] The top plate is provided with a first mounting hole, and the first inlet filter is arranged in the first mounting hole; the first shell is provided with a second mounting hole near the outlet of the storage tank, and the outlet is arranged in the second mounting hole.

[0015] In the above technical solution, further, the first inlet filter portion includes a first screen having a first preset mesh size.

[0016] In the above technical solution, further, the first retention assembly also includes a partition;

[0017] The partition is disposed in the middle of the first storage chamber, and can divide the first storage chamber into an upper storage chamber and a lower storage chamber;

[0018] The first inlet filter portion includes a first screen and a screen cylinder; a third mounting hole is opened at a position relative to the top plate and the partition; the first screen is arranged in the third mounting hole of the top plate, and the two ends of the screen cylinder are respectively abutted against the third mounting hole on the top plate and the third mounting hole on the partition.

[0019] In the above technical solution, further, the first inlet filter portion also includes reinforcing ribs;

[0020] The reinforcing rib is arranged on the screen cylinder and two ends thereof are respectively connected to the edge of the third mounting hole on the top plate and the edge of the third mounting hole on the partition plate.

[0021] In the above technical solution, further, the second storage assembly includes a bottom plate, a cover body and a second shell;

[0022] The second shell is buckled on the bottom plate to surround a cavity; the cover is a tapered structure from the bottom plate to the second shell, and the cover is arranged on the cavity to divide the cavity into the gathering chamber and the second storage chamber;

[0023] A fourth mounting hole for mounting the second inlet filter is provided on the bottom plate at a position corresponding to the first mounting hole; a fifth mounting hole is provided on the cover body corresponding to the fourth mounting hole; and a sixth mounting hole for mounting the exhaust part is provided on the second shell corresponding to the fifth mounting hole.

[0024] In the above technical solution, further, the second inlet filter portion includes a second screen having a second preset mesh number that is smaller than the first preset mesh number;

[0025] The exhaust part includes an exhaust pipe and an exhaust screen arranged on the exhaust pipe; the exhaust pipe is arranged on the sixth mounting hole.

[0026] In the above technical solution, further, a storage hole is opened on the edge of the cover body.

[0027] In the above technical solution, further, the propellant management device applicable to the cryogenic tank of a launch vehicle also includes a flow guide assembly;

[0028] The first storage component and the second storage component have oppositely disposed side walls with flow guide holes;

[0029] The flow guide component is arranged in the gap and both ends of the flow guide component are respectively communicated with the flow guide holes, so that the flow guide component can communicate with the first retention component and the second retention component.

[0030] In the above technical solution, further, the flow guide assembly includes a flow guide tube and a flow guide filter;

[0031] The diversion filter is arranged at the diversion hole; and both ends of the diversion tube are respectively connected to the diversion filter.

[0032] Compared with the prior art, this application has the following beneficial effects:

[0033] The present application provides a propellant management device applicable to a low-temperature tank of a launch vehicle, which is arranged at an outlet of the tank; the propellant management device applicable to a low-temperature tank of a launch vehicle comprises a first retention component and a second retention component;

[0034] The first storage assembly has a first storage chamber, and the first storage assembly has a first inflow filter portion communicating with the first storage chamber and an outflow portion communicating with the first storage chamber and an outflow port of the storage tank respectively and opposite to the first inflow filter portion;

[0035] The second storage assembly comprises a gathering chamber and a second storage chamber communicating with the gathering chamber, and the second storage assembly comprises a second inflow filter communicating with the gathering chamber and an exhaust portion communicating with the second storage chamber and opposite to the second inflow filter;

[0036] The first storage assembly and the second storage assembly are spaced apart and the first inlet filter portion and the second inlet filter portion are opposite to each other, so that a gap communicating with the storage tank is formed between the first storage assembly and the second storage assembly;

[0037] During the gliding stage, the propellant in the tank passes through the gap and is retained in the first retention chamber through the first inlet filter portion, and is sequentially retained in the gathering chamber and the second retention chamber through the second inlet filter portion; the first inlet filter portion and the second inlet filter portion are used to filter the gas in the propellant retained from the tank in the first retention component and the second retention component.

[0038] In summary, the present application utilizes the first retention component and the second retention component to simultaneously realize the retention of propellant, thereby increasing the retention space (retention volume), so that it can be suitable for the tank of a large-flow launch vehicle; in addition, during the retention, the propellant in the tank will flow into the first retention component through the first inlet filter portion, and the first inlet filter portion can realize gas-liquid isolation, filter the bubbles in the propellant flowing into the first retention component, and prevent the bubbles from entering the first retention component, thereby reducing the space occupied by the bubbles and ensuring the quality of the retention. Similarly, the effect of the propellant retained in the second retention component through the second inlet filter portion is the same as that of the first retention component, so it will not be elaborated in detail. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the specific implementation methods of the present application or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0040] Figure 1 A schematic diagram of the structure of the propellant management device for a launch vehicle cryogenic tank provided in the present application, which is applied to the tank and is viewed from a first perspective;

[0041] Figure 2 A schematic diagram of the structure of the propellant management device for a launch vehicle cryogenic tank provided in the present application, which is applied to the tank and is viewed from a second perspective;

[0042] Figure 3 A schematic diagram of the structure of a propellant management device suitable for a launch vehicle cryogenic tank provided in this application.

[0043] Figure numerals: 1-storage box; 2-gathering chamber; 3-second storage chamber; 4-exhaust part; 5-gap; 6-top plate; 7-first outer shell; 8-first screen; 9-partition; 10-upper storage chamber; 11-lower storage chamber; 12-screen cylinder; 13-reinforcement ribs; 14-bottom plate; 15-second outer shell; 16-cover body; 17-second screen; 18-exhaust pipe; 19-exhaust screen; 20-retention hole; 21-guide tube; 22-guide filter. DETAILED DESCRIPTION

[0044] The following specific embodiments are provided to help the reader obtain a comprehensive understanding of the methods, devices and / or systems described herein. However, after understanding the disclosure of the present application, various changes, modifications and equivalents of the methods, devices and / or systems described herein will be apparent. For example, the order of operations described herein is merely an example, and is not limited to the order set forth herein, but in addition to the operations that must occur in a particular order, changes that will be apparent after understanding the disclosure of the present application may be made. In addition, in order to improve clarity and brevity, descriptions of features known in the art may be omitted.

[0045] The features described herein may be implemented in different forms and should not be interpreted as being limited to the examples described herein. Rather, the examples described herein have been provided only to illustrate some of the many possible ways of implementing the methods, devices and / or systems described herein that will be apparent after understanding the disclosure of the present application.

[0046] Throughout the specification, when an element (such as a layer, a region, or a substrate) is described as being “on”, “connected to”, “bound to”, “over”, or “covering” another element, it may be directly “on”, “connected to”, “bound to”, “over”, or “covering” another element, or one or more other elements may be present between them. In contrast, when an element is described as being “directly on”, “directly connected to”, “directly bound to”, “directly over”, or “directly covering” another element, there may be no other elements present between them.

[0047] As used herein, the term "and / or" includes any one of the associated listed items and any combination of any two or more items.

[0048] Although terms such as "first," "second," and "third" may be used herein to describe various members, components, regions, layers, or portions, these members, components, regions, layers, or portions are not limited by these terms. Rather, these terms are only used to distinguish one member, component, region, layer, or portion from another member, component, region, layer, or portion. Therefore, without departing from the teachings of the examples described herein, the first member, component, region, layer, or portion referred to may also be referred to as the second member, component, region, layer, or portion.

[0049] For ease of description, spatial relational terms such as "above", "upper", "below", and "lower" may be used herein to describe the relationship of one element to another element as shown in the accompanying drawings. Such spatial relational terms are intended to include different orientations of the device in use or operation in addition to the orientation depicted in the accompanying drawings. For example, if the device in the accompanying drawings is turned over, an element described as being "above" or "upper" relative to another element will subsequently be "below" or "lower" relative to the other element. Therefore, the term "above" includes both "above" and "below" orientations depending on the spatial orientation of the device. The device may also be positioned in other ways (e.g., rotated 90 degrees or in other orientations), and the spatial relational terms used herein will be interpreted accordingly.

[0050] The terms used herein are only used to describe various examples and are not used to limit the present disclosure. Unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. The terms "include", "comprise" and "have" list the stated features, quantities, operations, components, elements and / or their combinations that exist, but do not exclude the existence or addition of one or more other features, quantities, operations, components, elements and / or their combinations.

[0051] Variations in the shapes shown in the drawings may occur due to manufacturing techniques and / or tolerances. Therefore, the examples described herein are not limited to the specific shapes shown in the drawings but include variations in shapes that occur during manufacturing.

[0052] The features of the examples described herein may be combined in various ways that will be apparent after understanding the disclosure of the present application. In addition, although the examples described herein have various configurations, other configurations are possible as will be apparent after understanding the disclosure of the present application.

[0053] Embodiment 1

[0054] The present application provides a propellant management device for a launch vehicle cryogenic tank 1, which is arranged at the outlet of the tank 1. The propellant management device for a launch vehicle cryogenic tank 1 can, to a certain extent, store the propellant in the tank 1 when the tank 1 is in the gliding stage. Figure 1-Figure 3 The propellant management device suitable for the cryogenic tank 1 of the launch vehicle is described in detail.

[0055] The propellant management device suitable for the cryogenic tank 1 of a launch vehicle includes a first retention component and a second retention component.

[0056] Specifically, the first storage assembly has a first storage chamber, and the first storage assembly has a first inlet filter portion connected to the first storage chamber, and an outlet portion connected to the first storage chamber and the outlet of the tank 1 respectively and opposite to the first inlet filter portion; further, the first storage assembly is a hemispherical structure, so that it has a plane end and a spherical end, and the plane end and the spherical end are surrounded by the first storage chamber; the plane end is just connected to the side wall at the outlet of the tank 1, and the spherical end is located outside the tank 1. Further, combined with Figure 3 As shown and Figure 3 Taking the placement perspective as an example, the first inlet filter portion is located at the plane end of the first retention component, the outlet portion is located at the spherical end of the first retention component, and the first inlet filter portion is coaxially arranged relative to the outlet portion.

[0057] Specifically, the second storage assembly has a gathering chamber 2 and a second storage chamber 3 connected to the gathering chamber 2, and the second storage assembly has a second inlet filter portion connected to the gathering chamber 2 and an exhaust portion 4 connected to the second storage chamber 3 and opposite to the second inlet filter portion.

[0058] Furthermore, the second retention assembly is located as a whole in the storage tank 1, and the second retention assembly is a cylindrical structure, which has a planar end and a cylindrical end, and the planar end and the cylindrical end are surrounded by a cavity, and the cavity is divided into a vertically arranged gathering chamber 2 and a second retention chamber 3, and the planar end is close to the first retention assembly.

[0059] Furthermore, a second inlet filter is provided on the plane end.

[0060] Specifically, the first storage assembly and the second storage assembly are spaced apart and the first inlet filter portion and the second inlet filter portion are opposite, that is, the first inlet filter portion and the second inlet filter portion are coaxial; so that a gap 5 connected to the storage tank 1 is formed between the first storage assembly and the second storage assembly.

[0061] In actual use, during the gliding stage, the propellant in the tank 1 passes through the gap 5 and is retained in the first retention chamber through the first inlet filter portion. When the first retention chamber is full, it passes through the second inlet filter portion and is retained in the gathering chamber 2 and the second retention chamber 3 in turn; the first inlet filter portion and the second inlet filter portion are used to filter the gas in the propellant retained from the tank 1 in the first retention component and the second retention component.

[0062] In summary, when the launch vehicle is in the gliding phase, the propellant in the tank 1 is in a microgravity state. In a microgravity environment, the propellant tends to flow into the slit. Therefore, in the gliding phase, the propellant in the tank 1 enters the first retention component and the second retention component through the gap 5. The present application utilizes the first retention component and the second retention component to simultaneously realize the retention of the propellant, thereby increasing the retention space (retention volume), so that it can be suitable for the tank 1 of a launch vehicle with a large flow rate; in addition, during the retention, the propellant in the tank 1 will flow into the first retention component through the first inlet filter portion, and the first inlet filter portion can realize gas-liquid isolation, filter the bubbles in the propellant flowing into the first retention component, prevent the bubbles from entering the first retention component, reduce the space occupied by the bubbles and ensure the quality of the retention. Similarly, the effect of the propellant retained in the second retention component through the second inlet filter portion is the same as that of the first retention component, so it will not be elaborated in detail.

[0063] In this embodiment, further, combined with Figure 3 As shown, the first retention assembly includes a top plate 6 and a first outer shell 7; wherein the top plate 6 is a flat plate, which is the flat end mentioned above; preferably, the top plate 6 is a circular plate; the first outer shell 7 is an arc-shaped outer shell, which is the spherical end mentioned above; preferably, the first outer shell 7 is hemispherical; the top plate 6 and the first outer shell 7 surround a first retention chamber.

[0064] Specifically, a first mounting hole is opened on the top plate 6, and the first inlet filter part is arranged in the first mounting hole; a second mounting hole is opened on the first shell 7 near the outlet of the storage tank 1, and the outlet part is arranged in the second mounting hole.

[0065] In summary, during the taxiing phase, the propellant in the tank 1 is filtered through the first inlet filter to isolate and filter the bubbles in the propellant, thereby preventing the bubbles from accumulating in the first retention chamber; when the engine is restarted, the propellant retained by the management device can provide the engine with liquid-phase propellant without air entrainment, thereby ensuring reliable starting of the engine.

[0066] In this embodiment, further, combined with Figure 3 As shown, the first storage assembly further includes a partition 9; the partition 9 is disposed in the middle of the first storage chamber, and can divide the first storage chamber into an upper storage chamber 10 and a lower storage chamber 11; the partition 9 is a circular plate.

[0067] Specifically, the first inlet filter section includes a first screen 8 and a screen cylinder 12; a third mounting hole is opened at a relative position between the top plate 6 and the partition 9; the first screen 8 is arranged in the third mounting hole of the top plate 6, and the two ends of the screen cylinder 12 are respectively abutted against the edge of the third mounting hole on the top plate 6 and the edge of the third mounting hole on the partition 9.

[0068] During the taxiing phase, the propellant in the tank 1 passes through the gap 5 and is stored in the lower storage chamber 11 through the first screen 8 . When the lower storage chamber 11 is filled, the propellant passes through the screen cylinder 12 and is filled in the upper storage chamber 10 .

[0069] It is worth noting that since the engine is located below the outlet of the tank 1, heat leakage bubbles will be generated in the lower retention chamber 11. Such heat leakage bubbles are like impurities and are not needed by the first retention component. Therefore, it is necessary to discharge the heat leakage bubbles. The present application cleverly provides a partition 9 in the middle of the first retention chamber. The partition 9 can concentrate the heat leakage bubbles at the first inlet filter portion, that is, the heat leakage bubbles generated from the bottom of the lower retention chamber 11 can be discharged from the first inlet filter portion along the vertical direction to the first retention component.

[0070] Furthermore, combined with Figure 3 As shown, since the screen cylinder 12 is a cylindrical structure surrounded by the screen, its own supporting strength is relatively weak. In order to improve the overall supporting strength of the first inlet filter portion, the present application adds a reinforcing rib 13 to the first inlet filter portion. Specifically, the reinforcing rib 13 is respectively connected to the edge of the third mounting hole on the top plate 6 and the edge of the third mounting hole on the partition plate 9 at both ends along its length direction.

[0071] Preferably, the reinforcing ribs 13 are strip-shaped; a plurality of reinforcing ribs 13 are provided, and the plurality of reinforcing ribs 13 are arranged at intervals along the circumferential direction of the screen cylinder 12; more preferably, four reinforcing ribs 13 are provided, and the four reinforcing ribs 13 are equally spaced along the circumferential direction of the screen cylinder 12, thereby being able to improve the support uniformity of the first inlet filter portion in the circumferential direction.

[0072] In this embodiment, further, the second storage assembly includes a bottom plate 14, a cover 16 and a second housing 15; specifically, the bottom plate 14 is in the shape of a circular plate and is close to the first storage assembly; the second housing 15 is in the shape of a cylinder and is arranged above the bottom plate 14. Specifically, the second housing 15 is buckled on the bottom plate 14 and can surround a cavity; the cover 16 is a tapered structure from the bottom plate 14 to the second housing 15, and the cover 16 is arranged in the cavity to divide the cavity into a gathering chamber 2 close to the first storage assembly and a second storage chamber 3 outside the first storage assembly.

[0073] Specifically, a fourth mounting hole for mounting the second inlet filter is provided at a position corresponding to the first mounting hole on the bottom plate 14, that is, the first mounting hole is coaxially arranged with the fourth mounting hole, and preferably, the diameters of the first mounting hole and the second mounting hole are the same. A fifth mounting hole is provided on the cover body 16 corresponding to the fourth mounting hole, that is, the fifth mounting hole is coaxially arranged with the fourth mounting hole, and preferably, the diameters of the fourth mounting hole and the fifth mounting hole are the same. A sixth mounting hole capable of mounting the exhaust unit 4 is provided on the second housing 15 corresponding to the fifth mounting hole.

[0074] Furthermore, the second inlet filter section includes a second screen 17, which has a second preset mesh number that is smaller than the first preset mesh number (the first preset mesh number here is a parameter of the first screen 8); the exhaust section 4 includes an exhaust pipe 18 and an exhaust screen 19 arranged on the exhaust pipe 18; the exhaust pipe 18 is arranged at the sixth mounting hole.

[0075] Furthermore, combined with Figure 3 As shown, the cover body 16 is trumpet-shaped, and a fifth mounting hole is provided on a side away from the bottom plate 14. Such a trumpet-shaped cover body 16 can enrich the propellant on one hand, and can position the leaking heat bubbles discharged from the first storage component on the other hand, so that the leaking heat bubbles discharged from the first storage component can eventually be discharged through the fifth mounting hole and the sixth mounting hole in sequence.

[0076] In addition, since the second preset mesh number of the second screen 17 is smaller than the first preset mesh number, the leaking hot air bubbles can be guided through.

[0077] In this embodiment, further, combined with Figure 3 As shown, a storage hole 20 is opened at the edge of the cover body 16. Preferably, the storage hole 20 is a rectangular hole. Preferably, there are multiple storage holes 20, and the multiple storage holes 20 are arranged at equal intervals along the circumference of the cover body 16 close to the bottom plate 14.

[0078] During the gliding stage, when the lower storage chamber 11 is filled, the propellant will be filled into the upper storage chamber 10 through the screen cylinder 12. When the upper storage chamber 10 is filled, the propellant will be stored in the gathering chamber 2 through the second inlet filter part, and when being stored in the gathering chamber 2, it will be stored in the second storage chamber 3 through the storage hole 20, thereby speeding up the storage speed, saving time and improving efficiency.

[0079] In this embodiment, further, combined with Figure 3 As shown, the propellant management device for the launch vehicle cryogenic tank 1 also includes a flow guide assembly. The side walls of the first storage assembly and the second storage assembly facing each other are provided with flow guide holes opposite to each other; the flow guide assembly is arranged in the gap 5 and the two ends of the flow guide assembly are respectively connected to the flow guide holes, so that the flow guide assembly can connect the first storage assembly and the second storage assembly.

[0080] Furthermore, combined with Figure 3 As shown, the flow guide assembly includes a flow guide tube 21 and a flow guide filter 22; the flow guide filter 22 is arranged in the flow guide hole; and both ends of the flow guide tube 21 are respectively connected to the flow guide filter 22.

[0081] Preferably, a plurality of flow guide components are provided, and the plurality of flow guide components are arranged at equal intervals along the circumferential direction of the bottom plate 14 .

[0082] In actual use, the gap 5 can enrich the propellant and guide the propellant into the first retention assembly and the second retention assembly; a plurality of guide assemblies are arranged between the first retention assembly and the second retention assembly, and the two ends of the guide assembly are respectively connected to the first retention assembly and the second retention assembly. During the start-up of the engine, the propellant in the second retention assembly can be quickly guided to the first retention assembly through the guide assembly. Furthermore, during the restart of the engine, the propellant in the first storage assembly is supplied to the engine through the outflow portion, and the propellant in the second storage assembly is supplemented to the lower storage layer through the guide assembly. As the engine restarts, axial acceleration is gradually established in the tank 1, most of the propellant is relocated to the bottom of the tank 1, and the engine starts to work normally. When the propellant in the outflow portion begins to entrain air, the remaining amount of propellant in the tank 1 is small.

[0083] It is worth noting that the first screen 8, the second screen 17 and the screens in the screen cylinder 12 are all metal screens with small apertures, which can effectively isolate the gas and achieve reliable retention of the propellant. In addition, the metal screen has a smaller aperture, which can also play a role in gas-liquid isolation for low-temperature propellants with small surface tension, thereby preventing bubbles from entering the management device. Compared with the first screen 8 and the second screen 17, the screen apertures of the screen cylinder 12 and the diversion filter 22 are smaller, which further isolates the bubbles and prevents them from entering the outlet.

[0084] In summary, the present application has a large retention volume, a large metal screen area, and a small flow resistance, and can be suitable for a large-flow launch vehicle tank 1; it is suitable for cryogenic propellants, and the structure of the management device determines that the fluid in the device is not easy to lose, and a metal screen is used to effectively isolate the cryogenic propellant from gas and liquid, thereby ensuring the effective refilling and retention of the cryogenic propellant; the structure of the management device is conducive to the discharge of the propellant, and the remaining amount of propellant is small when the engine stops working.

[0085] Embodiment 2

[0086] In this embodiment, another structure of the first inflow filter portion is provided. Specifically, the first inflow filter portion includes a first screen 8, and the first screen 8 has a first preset mesh number. Compared with the first inflow filter portion of the first embodiment, the first inflow filter portion in this embodiment is not provided with a partition 9. This first inflow filter portion without a partition 9 can also achieve the retention of the recommended gold, but does not have the effect of concentrating the heat leakage bubbles, but can still be used, and is also within the protection scope of the present application.

[0087] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit it. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. A propellant management device suitable for a launch vehicle cryogenic tank, arranged at the outlet of the tank; characterized in that: The propellant management device suitable for a launch vehicle cryogenic tank includes a first retention assembly and a second retention assembly; The first storage assembly has a first storage chamber, and the first storage assembly has a first inflow filter portion communicating with the first storage chamber and an outflow portion communicating with the first storage chamber and an outflow port of the storage tank respectively and opposite to the first inflow filter portion; The second storage assembly comprises a gathering chamber and a second storage chamber communicating with the gathering chamber, and the second storage assembly comprises a second inflow filter communicating with the gathering chamber and an exhaust portion communicating with the second storage chamber and opposite to the second inflow filter; The first storage assembly and the second storage assembly are spaced apart and the first inlet filter portion and the second inlet filter portion are opposite to each other, so that a gap communicating with the storage tank is formed between the first storage assembly and the second storage assembly; During the gliding stage, the propellant in the tank passes through the gap and is retained in the first retention chamber through the first inlet filter portion, and is sequentially retained in the gathering chamber and the second retention chamber through the second inlet filter portion; the first inlet filter portion and the second inlet filter portion are used to filter the gas in the propellant retained from the tank in the first retention component and the second retention component.

2. The propellant management device for a launch vehicle cryogenic tank according to claim 1, characterized in that: The first storage assembly includes a top plate and a first shell, The top plate and the first housing surround the first storage chamber; The top plate is provided with a first mounting hole, and the first inlet filter is arranged in the first mounting hole; the first shell is provided with a second mounting hole near the outlet of the storage tank, and the outlet is arranged in the second mounting hole.

3. The propellant management device for a launch vehicle cryogenic tank according to claim 2, characterized in that: The first inlet filter portion includes a first screen having a first preset mesh size.

4. The propellant management device for a launch vehicle cryogenic tank according to claim 2, characterized in that: The first retention assembly also includes a baffle; The partition is disposed in the middle of the first storage chamber, and can divide the first storage chamber into an upper storage chamber and a lower storage chamber; The first inlet filter portion includes a first screen and a screen cylinder; a third mounting hole is opened at a position relative to the top plate and the partition; the first screen is arranged in the third mounting hole of the top plate, and the two ends of the screen cylinder are respectively abutted against the third mounting hole on the top plate and the third mounting hole on the partition.

5. The propellant management device for a launch vehicle cryogenic tank according to claim 4, characterized in that: The first inflow filter portion further includes reinforcing ribs; The reinforcing rib is arranged on the screen cylinder and two ends thereof are respectively connected to the edge of the third mounting hole on the top plate and the edge of the third mounting hole on the partition plate.

6. The propellant management device for a launch vehicle cryogenic tank according to claim 3, characterized in that: The second storage assembly includes a base plate, a cover body and a second shell; The second shell is buckled on the bottom plate to surround a cavity; the cover is a tapered structure from the bottom plate to the second shell, and the cover is arranged on the cavity to divide the cavity into the gathering chamber and the second storage chamber; A fourth mounting hole for mounting the second inlet filter is provided on the bottom plate at a position corresponding to the first mounting hole; a fifth mounting hole is provided on the cover body corresponding to the fourth mounting hole; and a sixth mounting hole for mounting the exhaust part is provided on the second shell corresponding to the fifth mounting hole.

7. The propellant management device for a launch vehicle cryogenic tank according to claim 6, characterized in that: The second inlet filter portion includes a second screen having a second preset mesh number which is smaller than the first preset mesh number; The exhaust part includes an exhaust pipe and an exhaust screen arranged on the exhaust pipe; the exhaust pipe is arranged on the sixth mounting hole.

8. The propellant management device for a launch vehicle cryogenic tank according to claim 6, characterized in that: A storage hole is provided at the edge of the cover body.

9. The propellant management device for a launch vehicle cryogenic tank according to claim 1, characterized in that: The propellant management device suitable for a launch vehicle cryogenic tank also includes a flow guide assembly; The first storage component and the second storage component have oppositely disposed side walls with flow guide holes; The flow guide component is arranged in the gap and both ends of the flow guide component are respectively communicated with the flow guide holes, so that the flow guide component can communicate with the first retention component and the second retention component.

10. The propellant management device for a launch vehicle cryogenic tank according to claim 9, characterized in that: The flow guide assembly includes a flow guide tube and a flow guide filter; The diversion filter is arranged at the diversion hole; and both ends of the diversion tube are respectively connected to the diversion filter.

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