Propellant management device for a launch vehicle cryogenic tank

Abstract

The application provides a propellant management device suitable for a low-temperature storage tank of a carrier rocket, which comprises a first storage assembly and a second storage assembly; the first storage assembly has a first storage chamber, and the first storage chamber has a first inflow filter part and an outflow part; the second storage assembly has a gathering chamber and a second storage chamber, and the second storage assembly has a second inflow filter part and an exhaust part; a gap is formed between the first storage assembly and the second storage assembly and is communicated with the storage tank; when in the sliding stage, the propellant is stored in the first storage chamber through the gap and the first inflow filter part, and is stored in the gathering chamber and the second storage chamber through the second inflow filter part. The first storage assembly and the second storage assembly are used to simultaneously store the propellant, the storage space is increased, and the device can be suitable for the storage tank of a carrier rocket with large flow; the first inflow filter part can realize gas-liquid separation, filter the bubbles flowing into the first storage assembly, and prevent the bubbles 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 upper stages of large cryogenic launch vehicles typically glide in orbit for a period of time, during which the rocket's upper tank remains in a microgravity environment. To ensure the launch vehicle's ability to launch multiple times in microgravity, a propellant management system is often employed.

[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 not discharged with air, and ensuring the normal starting and operation of the engine.

[0004] However, existing propellant management systems are mainly used for small tanks and conventional propellants. Compared with launch vehicles, satellite tanks are smaller and the propellant supply flow is smaller, 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 existing technology to a certain extent. Summary of the Invention

[0006] The purpose of this application is to provide a propellant management device and 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 for a low-temperature storage tank of a launch vehicle, which is arranged at the outlet of the tank; the propellant management device for a low-temperature storage tank of a launch vehicle includes 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 inlet filter portion communicating with the first storage chamber, and an outlet portion communicating with the first storage chamber and an outlet of the storage tank, respectively, and opposite to the first inlet 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 inlet filter communicating with the gathering chamber and an exhaust portion communicating with the second storage chamber and opposite to the second inlet 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 glide phase, 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 gas in the propellant retained from the tank in the first retention assembly and the second retention assembly.

[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 shell enclose the first storage chamber;

[0014] A first mounting hole is formed on the top plate, and the first inlet filter is arranged in the first mounting hole; a second mounting hole is formed on the first shell 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 component also includes a partition;

[0017] The partition is provided in the middle of the first storage chamber, and is capable of dividing 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 provided 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 further 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 enclose a cavity; the cover is a tapered structure from the bottom plate to the second shell, and the cover is arranged in 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 smaller than the first preset mesh number;

[0025] The exhaust portion includes an exhaust pipe and an exhaust screen arranged on the exhaust pipe; the exhaust pipe is arranged in 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 further includes a flow guide assembly;

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

[0029] The flow guide component is arranged in the gap and both ends of the flow guide component are communicated with the flow guide holes respectively, 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 diversion assembly includes a diversion tube and a diversion filter;

[0031] The diversion filter is arranged in 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 for a low-temperature storage tank of a launch vehicle, which is arranged at the outlet of the tank; the propellant management device for a low-temperature storage tank of a launch vehicle includes 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 inlet filter portion communicating with the first storage chamber, and an outlet portion communicating with the first storage chamber and an outlet of the storage tank, respectively, and opposite to the first inlet 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 inlet filter communicating with the gathering chamber and an exhaust portion communicating with the second storage chamber and opposite to the second inlet 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 glide phase, 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 gas in the propellant retained from the tank in the first retention assembly and the second retention assembly.

[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 applied to 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, 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. 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 following is a brief introduction to the drawings required for use in the specific implementation methods or the description of the prior art. 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 any creative work.

[0040] Figure 1 A schematic structural diagram of the propellant management device for a launch vehicle cryogenic tank provided in this application, applied to the tank and viewed from a first-person perspective;

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

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

[0043] Figure markings: 1-storage tank; 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 rib; 14-bottom plate; 15-second outer shell; 16-cover; 17-second screen; 18-exhaust pipe; 19-exhaust screen; 20-retention hole; 21-guide tube; 22-guide filter. DETAILED DESCRIPTION

[0044] The following detailed description is provided to help the reader gain a comprehensive understanding of the methods, devices, and / or systems described herein. However, various changes, modifications, and equivalents of the methods, devices, and / or systems described herein will be apparent upon understanding the disclosure of this application. For example, the order of operations described herein is merely illustrative and is not limited to the order set forth herein. Rather, except for operations that must occur in a particular order, changes may be made that will be apparent upon understanding the disclosure of this application. Furthermore, descriptions of features known in the art may be omitted for clarity and brevity.

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

[0046] Throughout the specification, when an element (such as a layer, region, or substrate) is described as being “on,” “connected to,” “coupled to,” “over,” or “overlaying” another element, it may be directly “on,” “connected to,” “coupled to,” “over,” or “overlaying” 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 coupled to,” “directly over,” or “directly covering” another element, there may be no other elements intervening therebetween.

[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 used only to distinguish one member, component, region, layer, or portion from another member, component, region, layer, or portion. Thus, a first member, component, region, layer, or portion in the examples described herein may also be referred to as a second member, component, region, layer, or portion without departing from the teachings of the examples.

[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 encompass different orientations of the device in use or operation in addition to the orientations 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 would subsequently be "below" or "lower" relative to the other element. Thus, the term "above" includes both the orientations "above" and "below," 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 intended only to describe various examples and are not intended to limit the present disclosure. Unless the context clearly indicates otherwise, the singular is intended to include the plural. The terms "comprise," "include," and "have" list the presence of stated features, quantities, operations, components, elements, and / or combinations thereof, but do not preclude the presence or addition of one or more other features, quantities, operations, components, elements, and / or combinations thereof.

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

[0052] The features of the examples described herein can 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] Example 1

[0054] The present application provides a propellant management device for a low-temperature tank 1 of a launch vehicle, which is arranged at the outlet of the tank 1. The propellant management device for the low-temperature tank 1 of a launch vehicle 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 a launch vehicle cryogenic tank 1 includes a first retention assembly and a second retention assembly.

[0056] Specifically, the first storage assembly has a first storage chamber, and the first storage assembly has a first inlet filter portion communicating with the first storage chamber, and an outlet portion communicating with the first storage chamber and the outlet of the storage tank 1 respectively and opposite to the first inlet filter portion; further, the first storage assembly has a hemispherical structure, so that it has a flat end and a spherical end, and the flat end and the spherical end are surrounded by the first storage chamber; the flat end is exactly connected to the side wall of the outlet of the storage tank 1, and the spherical end is located outside the storage 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 and the outlet portion are coaxially arranged relative to each other.

[0057] Specifically, the second retention assembly has a gathering chamber 2 and a second retention chamber 3 connected to the gathering chamber 2, and the second retention assembly has a second inlet filter portion connected to the gathering chamber 2 and an exhaust portion 4 connected to the second retention 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. The second retention assembly is a cylindrical structure, which has a planar end and a cylindrical end. 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. The planar end is close to the first retention assembly.

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

[0060] Specifically, the first retention assembly and the second retention 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 communicating with the storage tank 1 is formed between the first retention assembly and the second retention assembly.

[0061] During actual use, during the gliding phase, the propellant in the tank 1 passes through the gap 5 and is retained in the first retention chamber through the first inlet filter. When the first retention chamber is full, it passes through the second inlet filter and is retained in the gathering chamber 2 and the second retention chamber 3 in turn. The first inlet filter and the second inlet filter 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 carrier rocket 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 narrow gap. Therefore, during 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 applied to the tank 1 of a carrier rocket 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 part, and the first inlet filter part 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 part 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 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 shell 7 is an arc-shaped shell, which is the spherical end mentioned above; preferably, the first shell 7 is hemispherical; the top plate 6 and the first 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 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 is arranged in the second mounting hole.

[0065] In summary, during the coasting 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 drum 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 drum 12 respectively abut 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 coasting phase, the propellant in the tank 1 passes through the gap 5 and is retained in the lower retention chamber 11 through the first screen 8. When the lower retention chamber 11 is filled, the propellant passes through the screen cylinder 12 and is filled in the upper retention 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, these heat leakage bubbles need to be discharged. The present application cleverly provides a partition 9 in the middle of the first retention chamber. This 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 in the vertical direction out of the first retention component.

[0070] Further, combined with Figure 3 As shown, since the screen cylinder 12 is a cylindrical structure surrounded by screen, its own supporting strength is relatively weak. In order to improve the overall supporting strength of the first inlet filter part, the present application adds a reinforcing rib 13 to the first inlet filter part. Specifically, the reinforcing rib 13 is 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 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 improving the support uniformity of the first inlet filter portion in the circumferential direction.

[0072] In this embodiment, the second storage assembly further includes a base plate 14, a cover 16, and a second housing 15. Specifically, the base plate 14 is circular and located adjacent to the first storage assembly. The second housing 15 is cylindrical and disposed above the base plate 14. Specifically, the second housing 15 is buckled onto the base plate 14 to enclose a cavity. The cover 16 has a tapered structure from the base plate 14 toward the second housing 15. The cover 16 is disposed within the cavity, dividing the cavity into a gathering chamber 2 adjacent 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 defined on the base plate 14 at a position corresponding to the first mounting hole. The first and fourth mounting holes are coaxially disposed, and preferably, the first and second mounting holes have the same diameter. A fifth mounting hole is defined on the housing 16 at a position corresponding to the fourth mounting hole. The fifth and fourth mounting holes are coaxially disposed, and preferably, the fourth and fifth mounting holes have the same diameter. A sixth mounting hole for mounting the exhaust unit 4 is defined on the second housing 15 at a position corresponding to the fifth mounting hole.

[0074] Furthermore, the second inlet filter portion 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 portion 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 Figure 3 As shown, the cover 16 is trumpet-shaped and has a fifth mounting hole on the side away from the base plate 14. This trumpet-shaped cover 16 can not only enrich the propellant, but also locate the heat leakage bubbles discharged from the first retention assembly, so that the heat leakage bubbles discharged from the first retention assembly can ultimately 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, leaked hot air bubbles can be guided through.

[0077] In this embodiment, further, combined with Figure 3 As shown, a retention hole 20 is opened on the edge of the cover body 16. Preferably, the retention hole 20 is a rectangular hole. Preferably, there are multiple retention holes 20, and the multiple retention holes 20 are evenly spaced along the circumference of the cover body 16 near the bottom plate 14.

[0078] During the coasting phase, when the lower storage chamber 11 is full, the propellant will pass through the screen cylinder 12 and fill the upper storage chamber 10. When the upper storage chamber 10 is full, the propellant will pass through the second inlet filter and be stored in the gathering chamber 2. While being stored in the gathering chamber 2, the propellant will also 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 a launch vehicle cryogenic tank 1 also includes a flow guide assembly. The first and second retention assemblies have opposing flow guide holes formed on their facing side walls. The flow guide assembly is positioned within gap 5, with both ends of the flow guide assembly communicating with the flow guide holes, allowing the flow guide assembly to communicate with the first and second retention assemblies.

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

[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] During actual use, gap 5 can enrich propellant and guide it into the first and second storage assemblies. Multiple diversion assemblies are located between the first and second storage assemblies, with their ends connected to the first and second storage assemblies, respectively. During engine startup, the propellant in the second storage assembly can be rapidly diverted into the first storage assembly via the diversion assemblies. Furthermore, during engine restart, the propellant in the first storage assembly is supplied to the engine via the outflow portion, while the propellant in the second storage assembly is replenished to the lower reservoir via the diversion assemblies. As the engine restarts, axial acceleration gradually builds within tank 1, causing most of the propellant to be relocated to the bottom of tank 1, and the engine begins normal operation. When the propellant in the outflow portion begins to entrain air, the remaining propellant in tank 1 is minimal.

[0083] It is worth noting that the first screen 8, the second screen 17, and the screens within the screen drum 12 are all metal screens with small pore sizes, which can effectively isolate gases and achieve reliable retention of propellants. In addition, the metal screens have smaller pore sizes, which can also act as a gas-liquid separator for low-temperature propellants with low surface tension, thereby preventing bubbles from entering the management device. Compared to the first screen 8 and the second screen 17, the screens of the screen drum 12 and the diversion filter 22 have smaller pore sizes, further isolating bubbles and preventing them from entering the outlet.

[0084] In summary, the present application has a large storage volume, a large metal screen area, and a small flow resistance, and can be applied to a large-flow carrier rocket 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 amount of propellant remaining when the engine finishes working is small.

[0085] Example 2

[0086] In this embodiment, another structure of the first inlet filter portion is provided. Specifically, the first inlet filter portion includes a first screen 8 having a first predetermined mesh size. Compared with the first inlet filter portion of the first embodiment, the first inlet filter portion of this embodiment is not provided with a partition 9. This first inlet filter portion without a partition 9 can also achieve the purpose of retaining the recommended gold, but it does not have the effect of concentrating the heat leakage bubbles. However, it is still usable and is also within the scope of protection of this 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 them. 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 make equivalent replacements for some or all of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present application.

Claims

1. A propellant management device for a launch vehicle cryogenic tank, arranged at the outlet of the tank; characterized in that: The propellant management device 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 inlet filter portion communicating with the first storage chamber, and an outlet portion communicating with the first storage chamber and an outlet of the storage tank, respectively, and opposite to the first inlet 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 inlet filter communicating with the gathering chamber and an exhaust portion communicating with the second storage chamber and opposite to the second inlet 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 glide phase, 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 gas in the propellant retained from the tank in the first retention assembly and the second retention assembly.

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 shell enclose the first storage chamber; A first mounting hole is formed on the top plate, and the first inlet filter is arranged in the first mounting hole; a second mounting hole is formed on the first shell 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 further includes a partition; The partition is provided in the middle of the first storage chamber, and is capable of dividing 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 provided 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 inlet 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 enclose a cavity; the cover is a tapered structure from the bottom plate to the second shell, and the cover is arranged in 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 smaller than the first preset mesh number; The exhaust portion includes an exhaust pipe and an exhaust screen arranged on the exhaust pipe; the exhaust pipe is arranged in the sixth mounting hole.

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

9. The propellant management device for a launch vehicle cryogenic tank according to claim 1, characterized in that: The propellant management device for a carrier rocket cryogenic tank further includes a flow guide assembly; The first storage component and the second storage component have oppositely facing side walls provided with flow guide holes; The flow guide component is arranged in the gap and both ends of the flow guide component are communicated with the flow guide holes respectively, 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 diversion assembly includes a diversion tube and a diversion filter; The diversion filter is arranged in the diversion hole; and both ends of the diversion tube are respectively connected to the diversion filter.

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