A type of launch vehicle propellant tank

Abstract

This application relates to the field of aerospace technology, and more particularly to a launch vehicle propellant tank, comprising: an upper partition, a lower partition, a guide plate, an accumulator, an outlet pipe, an exhaust assembly, an anti-sway plate, and a tank body; the accumulator is fixed to the bottom of the tank body; the outlet pipe connects to the receiving cavity of the accumulator, and the outlet of the outlet pipe is located outside the tank body; the exhaust assembly is fixed to the upper end of the accumulator; the guide plate is fixed to the bottom of the tank body, and its inner edge is connected to the outer wall of the accumulator; the upper partition and the lower partition are fixed to the inner wall of the tank body, the upper partition being located above the accumulator, and the lower partition passing through the accumulator in the middle; the upper partition has an upper circular hole, and the lower partition has a lower circular hole, the diameter of the upper circular hole being larger than the diameter of the lower circular hole; the anti-sway plate is fixed to the inner wall of the tank body. This application can provide the engine with propellant without entrapment, and reduces the complexity and weight of the system, improving the rocket's carrying capacity and operational reliability.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to a launch vehicle propellant tank. Background Technology

[0002] The propellant tank is a crucial component of the liquid-fueled rocket propulsion system, providing the liquid rocket engine with a non-entrained propellant throughout the entire mission cycle. Compared to the first-stage propellant tank, the second-stage propellant tank needs to adapt to various flight profiles, including the first-stage flight phase, first-stage engine shutdown, first- and second-stage rocket separation, second-stage engine shutdown, second-stage coasting phase, and second-stage engine restart, making propellant management more challenging. Besides propellant sloshing caused by rocket attitude adjustments, engine thrust changes, gusts, and wind shear, first-stage engine shutdown, first- and second-stage separation, and second-stage engine shutdown all generate negative axial overloads, causing the propellant in the second-stage tank to move away from the outlet. During the second-stage coasting phase, the propellant in the second-stage tank is in a microgravity environment, requiring propellant management to ensure a non-entrained propellant supply for engine restart after prolonged coasting.

[0003] In existing technologies, multiple forward-thrust rockets are arranged in the interstage section between the first and second stages for propellant to sink to the bottom after the first-stage engine shuts down; an auxiliary propulsion system is arranged on the second-stage rocket body, and the forward-thrust engine of the auxiliary propulsion system is used for propellant to sink to the bottom between the shutdown of the second-stage engine and the second restart of the second-stage engine.

[0004] However, using a forward-thrust rocket increases the system's complexity and weight, and reduces the reliability of the first-stage rocket. In addition, using an auxiliary propulsion system with a forward-thrust engine also increases the system's complexity and reduces the reliability of the second-stage rocket. Furthermore, it increases the propellant loading of the auxiliary propulsion system, increases the system's weight, and reduces the rocket's payload capacity.

[0005] In addition, different sinking schemes are required depending on the second-stage coasting time, and the propellant loading amount and tank volume of the auxiliary power system are also adjusted accordingly, which is not conducive to the generalization of product design.

[0006] Therefore, ensuring that the propellant tank can provide gas-free propellant, reducing system complexity and weight, and improving the rocket's carrying capacity and operational reliability are technical problems that urgently need to be solved by those skilled in the art. Summary of the Invention

[0007] This application provides a launch vehicle propellant tank that, through an accumulator, a deflector, an upper baffle, a lower baffle, and an exhaust assembly, enables the launch vehicle propellant tank to supply the engine with a non-entrained propellant. This eliminates the need for a dedicated bottom-feeding system, reduces system complexity, lightens the rocket body's mass, and improves the rocket's carrying capacity.

[0008] To solve the above-mentioned technical problems, this application provides the following technical solution:

[0009] A launch vehicle propellant tank includes: an upper partition, a lower partition, a guide plate, a accumulator, a liquid outlet pipe, an exhaust assembly, an anti-sway plate, and a tank body; wherein, the lower end of the accumulator is fixed to the bottom of the tank body, and the accumulator has an internal receiving cavity, and the outer wall of the accumulator has a screen structure; the inlet end of the liquid outlet pipe is connected to the receiving cavity of the accumulator, the liquid outlet pipe extends through the outer wall of the tank body, and the outlet of the liquid outlet pipe is located outside the tank body; the exhaust assembly has an internal exhaust cavity, the top of the exhaust assembly has a screen structure, the upper end of the accumulator has multiple exhaust holes, the lower ends of all exhaust assemblies are fixed to the upper end of the accumulator, and the lower end of each exhaust assembly achieves exhaust through an exhaust hole. The exhaust chamber of the component is connected to the receiving chamber of the accumulator; the lower edges of multiple guide plates are fixed to the bottom of the tank body, and the guide plates have multiple through holes that pass through both sides, and the inner edge of each guide plate is connected to the outer wall of the accumulator; the outer edge of the upper baffle is fixed to the inner wall of the tank body, and the upper baffle is located above the accumulator; the outer edge of the lower baffle is fixed to the inner wall of the tank body, and the lower baffle is located below the upper baffle, the middle part of the lower baffle passes through the accumulator and is fixedly connected to the accumulator; multiple upper circular holes are opened on the upper baffle, and multiple lower circular holes are opened on the lower baffle, the diameter of the upper circular holes is larger than the diameter of the lower circular holes; the outer edges of multiple anti-sway plates are fixed to the inner wall of the tank body.

[0010] The launch vehicle propellant tank described above preferably includes: a first top cover assembly, a first cylindrical section assembly, a second top cover assembly, and a second cylindrical section assembly; wherein the first top cover assembly is fixed to the upper opening of the first cylindrical section assembly to close the upper opening of the first cylindrical section assembly; the second top cover assembly is annular, and the inner edge of the second top cover assembly is fixed to the lower opening of the first cylindrical section assembly; the outer edge of the second top cover assembly extends outward, and the outer edge of the second top cover assembly is fixed to the upper opening of the second cylindrical section assembly, and the lower opening of the second cylindrical section assembly is fixed to the bottom of the propellant tank body.

[0011] In the launch vehicle propellant tank described above, preferably, the first top cover assembly includes: a first top cover frame, a first top cover support plate, a first top cover screen, and a first top cover pressure plate, wherein the first top cover frame, the first top cover support plate, the first top cover screen, and the first top cover pressure plate are stacked and fixed together from the inside to the outside.

[0012] The launch vehicle propellant tank described above preferably includes a first cylindrical segment assembly comprising: a first cylindrical segment skeleton, a first cylindrical segment support plate, a first cylindrical segment screen, and a first cylindrical segment pressure plate; and the first cylindrical segment skeleton, the first cylindrical segment support plate, the first cylindrical segment screen, and the first cylindrical segment pressure plate are stacked and fixed together from the inside out.

[0013] In the launch vehicle propellant tank described above, preferably, the volume V of the accumulator's receiving cavity is... x Satisfy V x ≥n1·q v ·t s , where t s q represents the time it takes for the water to sink to the bottom. v n1 is the volumetric flow rate of a component in the engine, and n1 is a coefficient ranging from 1.5 to 2.0.

[0014] In the launch vehicle propellant tank described above, preferably, the exhaust assembly includes: an exhaust assembly frame, an exhaust assembly support plate, an exhaust assembly screen, and an exhaust assembly pressure plate; wherein, the exhaust assembly frame is vertically continuous to form an exhaust chamber, and the lower end of the exhaust assembly frame is fixed to the upper end of the accumulator; the exhaust assembly support plate, the exhaust assembly screen, and the exhaust assembly pressure plate are stacked and fixed together from bottom to top; and the exhaust assembly support plate, the exhaust assembly screen, and the exhaust assembly pressure plate are fixed to the upper opening of the exhaust assembly frame to close the upper opening of the exhaust assembly frame.

[0015] In the launch vehicle propellant tank described above, preferably, all deflectors are evenly distributed in the diameter direction of the accumulator.

[0016] In the launch vehicle propellant tank described above, preferably, the through hole on the guide plate is a circular hole with a diameter D = (0.3~0.5)H, where H is the height of the guide plate corresponding to the location of the circular hole.

[0017] In the launch vehicle propellant tank described above, preferably, the total area of ​​the upper circular holes on the upper partition is not less than 2.0 to 2.5 times the flow area of ​​the liquid outlet pipe, and the total area of ​​the lower circular holes on the lower partition is not less than 1.5 to 2.0 times the flow area of ​​the liquid outlet pipe.

[0018] In the launch vehicle propellant tank described above, preferably, the liquid volume V2 below the lower partition is not less than 2.0 to 2.5 times Vx, and the liquid volume V3 below the upper partition is not less than 2.5 to 3.5 times Vx, where Vx is the liquid volume of the accumulator's internal cavity.

[0019] Compared to the aforementioned background technology, the launch vehicle propellant tank in this application can ensure that the tank provides the engine with propellant without air entrapment, and reduces the complexity and weight of the system, improves the rocket's carrying capacity and operational reliability, increases launch efficiency, and reduces mission costs. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0021] Figure 1 This is a schematic diagram of the launch vehicle propellant tank provided in this application;

[0022] Figure 2 This is a schematic diagram of the anti-sway plate, tunnel pipe, upper and lower partitions of the launch vehicle propellant tank provided in this application;

[0023] Figure 3 This is a schematic diagram of the accumulator of the launch vehicle propellant tank provided in this application;

[0024] Figure 4 This is a schematic diagram of the first top cover frame and the first cylindrical section frame of the accumulator of the launch vehicle propellant tank provided in this application;

[0025] Figure 5 This is a schematic diagram of the first top cover assembly of the accumulator of the launch vehicle propellant tank provided in this application;

[0026] Figure 6 This is a schematic diagram of the first cylindrical section assembly of the accumulator of the launch vehicle propellant tank provided in this application;

[0027] Figure 7 This is a schematic diagram of the exhaust assembly of the launch vehicle propellant tank provided in this application. Detailed Implementation

[0028] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0029] like Figure 1 As shown, this application provides a launch vehicle propellant tank, including: an upper partition 110, a lower partition 120, a guide plate 130, a accumulator 140, a liquid outlet pipe 150, an exhaust assembly 160, an anti-sway plate 170, and a propellant tank body 210.

[0030] The lower end of the accumulator 140 is fixed to the bottom of the tank body 210, and the accumulator 140 has an internal receiving cavity, while its outer wall is a screen structure. This allows the propellant in the tank body 210 to enter the receiving cavity of the accumulator 140. Because the propellant forms a liquid film on the outer wall of the screen-structured accumulator 140, it prevents gas from entering the receiving cavity of the accumulator 140, thus ensuring that the propellant in the receiving cavity of the accumulator 140 is free of entrainment. This allows the engine to receive free propellant from the receiving cavity of the accumulator 140.

[0031] Optionally, the accumulator 140 is cylindrical. Alternatively, the axis of the accumulator 140 is coaxial with the axis of the tank body 210, ensuring that the accumulator 140 is located at the lowest point of the tank body 210. Still optionally, the tank body 210 has a tunnel pipe 220 running vertically through it to pass through the propellant supply pipes of other tanks; in this case, the accumulator 140 passes through the tunnel pipe 220 and surrounds the outside of the tunnel pipe 220. Again, optionally, the volume V of the accumulator 140's receiving cavity is... x V should be satisfied x ≥n1·q v ·t s , where t s q represents the time it takes for the water to sink to the bottom. v n1 is the volumetric flow rate of a component of the engine (the propellant in the rocket's propellant tank, specifically referring to oxidizer or fuel), and n1 is a coefficient ranging from 1.5 to 2.0.

[0032] like Figure 3 As shown, the accumulator 140 includes: a first top cover assembly 141, a first cylindrical segment assembly 142, a second top cover assembly 143, and a second cylindrical segment assembly 144; wherein, the first top cover assembly 141 is fixed to the upper opening of the first cylindrical segment assembly 142 to close the upper opening of the first cylindrical segment assembly 142; the second top cover assembly 143 is annular, and the inner edge of the second top cover assembly 143 is fixed to the lower opening of the first cylindrical segment assembly 142; the outer edge of the second top cover assembly 143 extends outward, and the outer edge of the second top cover assembly 143 is fixed to the upper opening of the second cylindrical segment assembly 144, and the lower opening of the second cylindrical segment assembly 144 is fixed to the bottom of the tank body 210.

[0033] Optional, such as Figure 4 and Figure 5As shown, the first top cover assembly 141 includes: a first top cover frame 1411, a first top cover support plate 1412, a first top cover screen 1413, and a first top cover pressure plate 1414, which are stacked and fixed together from the inside out. Optionally, the first top cover frame 1411, the first top cover support plate 1412, the first top cover screen 1413, and the first top cover pressure plate 1414 are stacked and welded together from the inside out. Specifically, the first top cover support plate 1412, the first top cover screen 1413, and the first top cover pressure plate 1414 can be stacked and welded together before being welded to the first top cover frame 1411.

[0034] Optionally, the first top cover frame 1411 is a circular or annular metal plate with fan-shaped windows arranged radially. When there is no tunnel pipe 220 inside the tank body 210, the accumulator 140 does not need to pass through the tunnel pipe 220; in this case, the first top cover frame 1411 is a circular metal plate. When there is a tunnel pipe 220 inside the tank body 210, the accumulator 140 needs to pass through the tunnel pipe 220; in this case, the first top cover frame 1411 is an annular metal plate. Alternatively, the first top cover support plate 1412 and the first top cover pressure plate 1414 are fan-shaped metal plates, with fan-shaped windows arranged inside. Still optional, the thickness of the first top cover support plate 1412 and the first top cover pressure plate 1414 is 1mm to 2mm, and the four corners of the fan-shaped windows are rounded, R1 to R2. Alternatively, the first top cover screen 1413 is a 325×2300 metal twill screen in a fan shape.

[0035] The structure of the second top cover assembly 143 is similar to that of the first top cover assembly 141. Since the second top cover assembly 143 needs to pass through the first cylindrical segment assembly 142, the only difference between the second top cover assembly 143 and the first top cover assembly 141 is that the second top cover frame of the second top cover assembly 143 is an annular metal plate, and the second top cover frame of the second top cover assembly 143 cannot be set as a circular metal plate.

[0036] Optional, such as Figure 4 and Figure 6As shown, the first cylindrical segment assembly 142 includes: a first cylindrical segment frame 1421, a first cylindrical segment support plate 1422, a first cylindrical segment screen 1423, and a first cylindrical segment pressure plate 1424; and the first cylindrical segment frame 1421, the first cylindrical segment support plate 1422, the first cylindrical segment screen 1423, and the first cylindrical segment pressure plate 1424 are stacked and fixed together from the inside to the outside. Optionally, the first cylindrical segment frame 1421, the first cylindrical segment support plate 1422, the first cylindrical segment screen 1423, and the first cylindrical segment pressure plate 1424 are stacked and welded together from the inside to the outside. Specifically, the first cylindrical segment support plate 1422, the first cylindrical segment screen 1423, and the first cylindrical segment pressure plate 1424 can be stacked and welded together, and then welded to the first cylindrical segment frame 1421.

[0037] Optionally, the first cylindrical segment skeleton 1421 is a metal plate wound into a cylindrical shape, with rectangular windows arranged along the axial direction. Alternatively, the first cylindrical segment support plate 1422 and the first cylindrical segment pressure plate 1424 are rectangular metal plates, with rectangular windows arranged inside. Still optional, the thickness of the first cylindrical segment support plate 1422 and the first cylindrical segment pressure plate 1424 is 1mm to 2mm, and the four corners of the rectangular windows are rounded, R1 to R2. Alternatively, the first cylindrical segment screen 1423 is a 325×2300 metal twill screen, in a rectangular shape.

[0038] The structure of the second cylindrical segment assembly 144 is similar to that of the first cylindrical segment assembly 142, except that the height of the second cylindrical segment assembly 144 is less than the height of the first cylindrical segment assembly 142.

[0039] like Figure 1 As shown, the inlet end of the outlet pipe 150 is connected to the receiving cavity of the accumulator 140. The outlet pipe 150 extends out from the outer wall of the tank body 210, and the outlet port 151 of the outlet pipe 150 is located outside the tank body 210, thereby allowing the unentrained propellant in the receiving cavity of the accumulator 140 to be drawn out to the outside of the tank body 210 and supplied to the engine. Optionally, the inlet end of the outlet pipe 150 is located on the side wall of the accumulator 140 and close to the upper end of the accumulator 140. Alternatively, the outlet pipe 150 extends out from the bottom of the tank body 210.

[0040] The exhaust assembly 160 has an exhaust chamber inside, and the top of the exhaust assembly 160 is also a screen structure. The upper end of the accumulator 140 has multiple exhaust holes. The lower ends of all exhaust assemblies 160 are fixed to the upper end of the accumulator 140, and the lower end of each exhaust assembly 160 communicates with the receiving chamber of the accumulator 140 through an exhaust hole. Thus, when the propellant is added, after the upper end of the accumulator 140 is wetted with propellant, a liquid film will form on all the screens on the outer walls of the accumulator 140. However, if the propellant in the tank body 210 shakes or the tank body 210 tilts, the gas in the accumulator 140 will not be completely discharged from the accumulator 140. After the liquid film forms on all the outer walls of the accumulator 140, this part of the gas cannot be discharged from the accumulator 140, resulting in the supply of entrained propellant to the engine. However, in this application, an exhaust assembly 160 is provided at the upper end of the accumulator 140. This way, even if the upper end of the accumulator 140 is wetted with propellant and a liquid film is formed on all the outer walls of the accumulator 140, the gas in the accumulator 140's receiving cavity will enter the exhaust cavity of the exhaust assembly 160 upwards. Since the exhaust assembly 160 is positioned higher than the top of the accumulator 140, it can be ensured that the gas is discharged from the exhaust assembly 160, and the accumulator 140 is filled with propellant, thereby providing the engine with propellant that does not trap gas.

[0041] Optionally, the exhaust assembly 160 may also be cylindrical. Alternatively, the axis of the exhaust assembly 160 may be in the same direction as the axis of the tank body 210. Still alternatively, all exhaust assemblies 160 may be evenly distributed at the upper end of the accumulator 140. Figure 7 As shown, the exhaust assembly 160 includes: an exhaust assembly frame 161, an exhaust assembly support plate 162, an exhaust assembly screen 163, and an exhaust assembly pressure plate 164; wherein, the exhaust assembly frame 161 is vertically continuous to form an exhaust chamber, and the lower end of the exhaust assembly frame 161 is fixed to the upper end of the accumulator 140; the exhaust assembly support plate 162, the exhaust assembly screen 163, and the exhaust assembly pressure plate 164 are stacked and fixed together from bottom to top; and the exhaust assembly support plate 162, the exhaust assembly screen 163, and the exhaust assembly pressure plate 164 are fixed to the upper opening of the exhaust assembly frame 161 to close the upper opening of the exhaust assembly frame 161. Optionally, the exhaust assembly frame 161, the exhaust assembly support plate 162, the exhaust assembly screen 163, and the exhaust assembly pressure plate 164 are stacked and welded together from bottom to top. Alternatively, after the exhaust component support plate 162, the exhaust component screen 163 and the exhaust component pressure plate 164 are stacked and welded, they are then stacked and welded to the upper opening of the exhaust component frame 161.

[0042] Optionally, the exhaust assembly frame 161 is a cylindrical hollow structure, and the upper opening of the exhaust assembly frame 161 is an annular window. Alternatively, the exhaust assembly support plate 162 and the exhaust assembly pressure plate 164 are circular metal plates, and circular windows are provided inside the circular metal plates. Still optional, the thickness of the exhaust assembly support plate 162 and the exhaust assembly pressure plate 164 is 1mm to 2mm. Alternatively, the exhaust assembly screen 163 is a 200×1400 metal twill screen, and its shape is circular. When the engine starts more than twice, exhaust during the propellant refilling process can be achieved by increasing the area of ​​the exhaust assembly screen 163 and increasing the height of the exhaust assembly 160.

[0043] like Figure 1 As shown, the lower edges of multiple guide vanes 130 are fixed to the bottom of the tank body 210, and the guide vanes 130 have multiple through holes that pass through both sides, so that propellant can pass through the through holes and pass through the guide vanes 130. Under microgravity conditions, this makes it easier for the propellant to accumulate around the guide vanes 130. In addition, the inner edge of each guide vane 130 is connected to the outer wall of the accumulator 140. Here, "inner" refers to the side closer to the accumulator 140, thereby guiding the propellant accumulated around the guide vanes 130 to the accumulator 140, thus ensuring the integrity of the liquid film on the outer wall of the accumulator 140, while suppressing the propellant sloshing outside the accumulator 140, and also ensuring that the accumulator 140 can provide the engine with propellant without air entrapment.

[0044] Optionally, the guide plate 130 is a thin metal sheet structure. Alternatively, the thickness of the guide plate 130 is 3–5 mm. Still optional, 12–18 guide plates 130 are fixed to the bottom of the tank body 210. Again optional, all guide plates 130 are evenly distributed along the diameter of the accumulator 140. Also optional, the lower edge of the guide plate 130 is aligned with the inner bottom surface of the tank body 210. Alternatively, the through hole on the guide plate 130 is a circular hole with a diameter D = (0.3–0.5)H, where H is the height of the guide plate 130 corresponding to the location of the circular hole. Still optional, the lower edge of the guide plate 130 is welded to the bottom of the tank body 210, and the inner edge of the guide plate 130 is welded to the outer wall of the accumulator 140.

[0045] like Figure 1 and Figure 2As shown, the outer edge of the upper baffle 110 is fixed to the inner wall of the tank body 210, and the upper baffle 110 is located above the accumulator 140; the outer edge of the lower baffle 120 is fixed to the inner wall of the tank body 210, and the lower baffle 110 is located below the upper baffle 120. The middle part of the lower baffle 110 passes through the accumulator 140 and is fixedly connected to the accumulator 140. In addition, the upper baffle 110 has a plurality of upper circular holes 111, and the lower baffle 120 has a plurality of lower circular holes 121. The diameter of the upper circular holes 111 is larger than the diameter of the lower circular holes 121. The upper baffle 110 and the lower baffle 120 can suppress the movement of propellant in the tank body 210 away from the outlet due to negative axial overload.

[0046] Optionally, if the tank body 210 has a tunnel pipe 220 running through the top and bottom of the tank body 210, then the upper partition 110 is an annular metal plate to pass through the tunnel pipe 220; if the tank body 210 does not have a tunnel pipe 220, then the upper partition 110 is a circular metal plate; and the lower partition 120 is an annular metal plate to pass through the accumulator 140. Alternatively, the lower partition 120 is arranged in the middle of the accumulator 140 near the bottom. Alternatively, all upper circular holes 111 are evenly distributed on the upper partition 110, and all lower circular holes 121 are evenly distributed on the lower partition 120. Still alternatively, the total area of ​​the upper circular holes 111 on the upper partition 110 should be no less than 2.0 to 2.5 times the flow area of ​​the outlet pipe 150, and the total area of ​​the lower circular holes 121 on the lower partition 120 should be no less than 1.5 to 2.0 times the flow area of ​​the outlet pipe 150. Optionally, the liquid volume (including the liquid volume Vx of the accumulator 140 cavity) of the lower partition 120 and below should be no less than 2.0 to 2.5 times Vx, and the liquid volume (including the liquid volume Vx of the accumulator 140 cavity) of the upper partition 110 and below should be no less than 2.5 to 3.5 times Vx.

[0047] like Figure 1 and Figure 2 As shown, the outer edges of multiple anti-sloshing plates 170 are used to fix them to the inner wall of the tank body 210 to prevent the propellant inside the tank body 210 from sloshing. Optionally, the anti-sloshing plates 170 are unevenly distributed along the axial direction of the tank body 210 on the inner wall of the cylindrical section of the tank body.

[0048] Based on the above, the tank body 210 includes: an upper tank bottom 211, a cylindrical tank section 212, and a lower tank bottom 213; the upper tank bottom 211 is fixedly connected to the upper opening of the cylindrical tank section 212 to close the upper opening of the cylindrical tank section 212; the lower tank bottom 213 is fixedly connected to the lower opening of the cylindrical tank section 212 to close the lower opening of the cylindrical tank section 212. Optionally, a filling port 214 is provided on the lower tank bottom 213 for filling propellant into the tank body 210.

[0049] The launch vehicle propellant tank in this application can ensure that the tank provides the engine with propellant without entrainment, and reduces the complexity and weight of the system, improves the rocket's carrying capacity and operational reliability, increases launch efficiency, and reduces mission costs.

[0050] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0051] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A launch vehicle propellant tank, characterized in that, include: Upper baffle, lower baffle, guide plate, accumulator, liquid outlet pipe, venting assembly, anti-sway plate and tank body; The lower end of the accumulator is fixed to the bottom of the tank body, and the inside of the accumulator has a receiving cavity, while the outer wall of the accumulator is a screen structure. The inlet end of the outlet pipe is connected to the receiving cavity of the accumulator, the outlet pipe passes through the outer wall of the tank body, and the outlet of the outlet pipe is located outside the tank body. The exhaust assembly has an exhaust chamber inside, the top of the exhaust assembly is a screen structure, the upper end of the accumulator has multiple exhaust holes, the lower end of all exhaust assemblies is fixed to the upper end of the accumulator, and the lower end of each exhaust assembly communicates the exhaust chamber of the exhaust assembly with the receiving chamber of the accumulator through an exhaust hole; The lower edges of multiple guide plates are fixed to the bottom of the tank body, and the guide plates have multiple through holes that pass through both sides. The inner edge of each guide plate is connected to the outer wall of the accumulator. The outer edge of the upper partition is fixed to the inner wall of the tank body, and the upper partition is located above the accumulator; the outer edge of the lower partition is fixed to the inner wall of the tank body, and the lower partition is located below the upper partition. The middle part of the lower partition passes through the accumulator and is fixedly connected to the accumulator; multiple upper circular holes are provided on the upper partition, and multiple lower circular holes are provided on the lower partition. The diameter of the upper circular holes is larger than the diameter of the lower circular holes. The outer edges of multiple anti-sway plates are fixed to the inner wall of the tank body.

2. The launch vehicle propellant tank according to claim 1, characterized in that, The accumulator includes: a first top cover assembly, a first cylindrical section assembly, a second top cover assembly, and a second cylindrical section assembly; The first top cover assembly is fixed to the upper opening of the first cylindrical segment assembly to close the upper opening of the first cylindrical segment assembly; the second top cover assembly is annular, and the inner edge of the second top cover assembly is fixed to the lower opening of the first cylindrical segment assembly; the outer edge of the second top cover assembly extends outward, and the outer edge of the second top cover assembly is fixed to the upper opening of the second cylindrical segment assembly, and the lower opening of the second cylindrical segment assembly is fixed to the bottom of the tank body.

3. The launch vehicle propellant tank according to claim 1 or 2, characterized in that, The first top cover assembly includes: a first top cover frame, a first top cover support plate, a first top cover screen, and a first top cover pressure plate, wherein the first top cover frame, the first top cover support plate, the first top cover screen, and the first top cover pressure plate are stacked and fixed together from the inside to the outside.

4. The launch vehicle propellant tank according to claim 1 or 2, characterized in that, The first cylindrical segment assembly includes: a first cylindrical segment skeleton, a first cylindrical segment support plate, a first cylindrical segment screen, and a first cylindrical segment pressure plate; and the first cylindrical segment skeleton, the first cylindrical segment support plate, the first cylindrical segment screen, and the first cylindrical segment pressure plate are stacked and fixed together from the inside to the outside.

5. The launch vehicle propellant tank according to claim 1 or 2, characterized in that, The volume V of the accumulator's receiving cavity x Satisfy V x ≥n1·q v ·t s , where t s q represents the time it takes for the water to sink to the bottom. v n1 is the volumetric flow rate of a component in the engine, and n1 is a coefficient ranging from 1.5 to 2.

0.

6. The launch vehicle propellant tank according to claim 1 or 2, characterized in that, The exhaust assembly includes: an exhaust assembly frame, an exhaust assembly support plate, an exhaust assembly screen, and an exhaust assembly pressure plate; wherein, the exhaust assembly frame is vertically continuous to form an exhaust chamber, and the lower end of the exhaust assembly frame is fixed to the upper end of the accumulator; the exhaust assembly support plate, the exhaust assembly screen, and the exhaust assembly pressure plate are stacked and fixed together from bottom to top; and the exhaust assembly support plate, the exhaust assembly screen, and the exhaust assembly pressure plate are fixed to the upper opening of the exhaust assembly frame to close the upper opening of the exhaust assembly frame.

7. The launch vehicle propellant tank according to claim 1 or 2, characterized in that, All guide vanes are evenly distributed along the diameter of the accumulator.

8. The launch vehicle propellant tank according to claim 1 or 2, characterized in that, The through hole on the guide plate is a circular hole with a diameter D = (0.3~0.5)H, where H is the height of the guide plate corresponding to the location of the circular hole.

9. The launch vehicle propellant tank according to claim 1 or 2, characterized in that, The total area of ​​the upper circular holes on the upper partition is not less than 2.0 to 2.5 times the flow area of ​​the liquid outlet pipe, and the total area of ​​the lower circular holes on the lower partition is not less than 1.5 to 2.0 times the flow area of ​​the liquid outlet pipe.

10. The launch vehicle propellant tank according to claim 1 or 2, characterized in that, The liquid volume V2 below the lower partition is not less than 2.0 to 2.5 times Vx, and the liquid volume V3 below the upper partition is not less than 2.5 to 3.5 times Vx, where Vx is the liquid volume of the accumulator's internal cavity.

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