Carrier rocket storage tank

Abstract

The invention relates to the technical field of aerospace, in particular to a carrier rocket storage tank which comprises an upper partition plate, a lower partition plate, a flow guide plate, a flow accumulator, a liquid outlet pipe, an exhaust assembly, an anti-shaking plate and a storage tank body. The flow accumulator is fixed to the bottom of the storage box body; the liquid outlet pipe is communicated to the containing cavity of the flow accumulator, and a liquid outlet of the liquid outlet pipe is located outside the storage box body; the exhaust assembly is fixed to the upper end of the flow accumulator; the guide plate is fixed to the bottom of the storage box body, and the inner edge is connected to the outer wall of the flow accumulator; the upper partition plate and the lower partition plate are fixed to the inner wall of the storage box body, the upper partition plate is located above the flow accumulator, and the middle of the lower partition plate penetrates through the flow accumulator; an upper circular hole is formed in the upper partition plate, a lower circular hole is formed in the lower partition plate, and the diameter of the upper circular hole is larger than that of the lower circular hole; the anti-shaking plate is fixed to the inner wall of the storage box body. According to the invention, the propellant without air entrapment can be provided for the engine, the complexity and the weight of the system are reduced, and the carrying capacity and the working reliability of the rocket are improved.

Description

Technical Field

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

[0002] The tank is an important component of the liquid launch vehicle power system, providing non-air-entrained propellant for the liquid rocket engine throughout the flight mission cycle. Compared with the first-stage tank of the launch vehicle, the second-stage tank needs to adapt to the flight profiles such as the first-stage flight phase, the shutdown of the first-stage engine, the separation of the first and second-stage rockets, the shutdown of the second-stage engine, the second-stage glide phase, and the second-stage engine restart, and the management of propellant is more difficult. In addition to the propellant shaking in the tank caused by the adjustment of the rocket body attitude, the change of engine thrust, gusts and wind shear, the shutdown of the first-stage engine, the separation of the first and second stages, and the shutdown of the second-stage engine will all produce negative axial overloads, causing the propellant in the second-stage tank to move away from the liquid outlet. In the second-stage glide phase, the propellant in the second-stage tank is in a microgravity environment, and the propellant needs to be managed to ensure that it is provided with non-air-entrained propellant when the engine is started again after a long glide.

[0003] In the prior art, a plurality of forward thrust rockets are arranged on the interstage section between the first and second stages to allow the propellant to sink to the bottom after the first-stage engine is shut down; an auxiliary power system is arranged on the second-stage rocket body, and the forward thrust engine of the auxiliary power system is used to allow the propellant to sink to the bottom between the shutdown of the second-stage engine and the second start-up of the second-stage engine.

[0004] However, the use of forward-thrust rockets increases the complexity of the system, increases the weight of the system, and reduces the working reliability of the first-stage rocket. In addition, the use of forward-thrust engines for the auxiliary power system also increases the complexity of the system and reduces the working reliability of the second-stage rocket. In addition, the amount of propellant in the auxiliary power system is increased, which increases the weight of the system and reduces the carrying capacity of the rocket.

[0005] In addition, since different sinking plans need to be adopted according to the different secondary glide times, the auxiliary power system propellant filling amount and the auxiliary power system tank volume are also adjusted accordingly, which is not conducive to the universal design of the product.

[0006] Therefore, how to ensure that the tank can provide propellant without air, reduce the complexity and weight of the system, and improve the carrying capacity and working reliability of the rocket is a technical problem that technical personnel in this field urgently need to solve. Summary of the invention

[0007] The present application provides a launch vehicle tank, which uses an accumulator, a guide plate, an upper baffle, a lower baffle and an exhaust assembly to provide a non-air-entrained propellant supply to the engine, eliminates a special bottom sinking system, reduces system complexity, reduces the mass of the rocket body, and improves the rocket's carrying capacity.

[0008] In order to solve the above technical problems, this application provides the following technical solutions:

[0009] A launch vehicle tank comprises: an upper baffle, a lower baffle, a guide plate, an 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 interior of the accumulator has a containing cavity, and the outer wall of the accumulator is a screen structure; the inlet end of the liquid outlet pipe is connected to the containing cavity of the accumulator, the liquid outlet pipe passes through the outer wall of the tank body, and the liquid outlet of the liquid outlet pipe is located outside the tank body; the exhaust assembly has an exhaust cavity inside, the top of the exhaust assembly is a screen structure, the upper end of the accumulator has a plurality of exhaust holes, the lower ends of all the exhaust assemblies are fixed to the upper end of the accumulator, and the lower end of each exhaust assembly realizes the exhaust through an exhaust hole The exhaust chamber of the component is connected with the accommodating chamber of the accumulator; the lower edges of multiple guide plates are fixed to the bottom of the tank body, and the guide plates are provided with multiple through holes running 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 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; a plurality of upper circular holes are opened on the upper partition, and a plurality of lower circular holes are opened on the lower partition, and the diameter of the upper circular holes is greater 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 tank as described above, wherein, preferably, the accumulator 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 end opening of the first cylindrical section assembly to close the upper end 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 end 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 end opening of the second cylindrical section assembly, and the lower end opening of the second cylindrical section assembly is fixed to the bottom of the tank body.

[0011] The launch vehicle tank as described above, wherein 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, and 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 tank as described above, wherein preferably, the first cylindrical section assembly comprises: a first cylindrical section frame, a first cylindrical section support plate, a first cylindrical section screen and a first cylindrical section pressure plate; and the first cylindrical section frame, the first cylindrical section support plate, the first cylindrical section screen and the first cylindrical section pressure plate are stacked and fixed together from the inside to the outside.

[0013] The launch vehicle tank as described above, wherein preferably, the volume V of the accumulator accommodation chamber is x Meet V x ≥n1·q v ·t s , where t s is the sinking time, q v is the volume flow rate of a component of the engine, n1 is the coefficient, and takes 1.5~2.0.

[0014] The launch vehicle tank as described above, wherein 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 connected from top to bottom to form an exhaust cavity, 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 end opening of the exhaust assembly frame to close the upper end opening of the exhaust assembly frame.

[0015] The launch vehicle tank as described above, wherein preferably, all guide plates are evenly distributed in the diameter direction of the accumulator.

[0016] In the launch vehicle tank as described above, preferably, the through hole on the guide plate is a circular hole, and the diameter of the circular hole D=(0.3-0.5)H, wherein H is the height of the guide plate corresponding to the position of the circular hole.

[0017] In the launch vehicle tank as described above, preferably, the total area of ​​the upper circular holes opened 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 opened 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 tank as 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 storage chamber in the accumulator.

[0019] Compared with the above-mentioned background technology, the launch vehicle tank in the present application can ensure that the tank provides the engine with non-air-entrained propellant, and reduces the complexity and weight of the system, improves the rocket's carrying capacity and working reliability, improves launch efficiency, and reduces mission costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0021] Figure 1 It is a schematic diagram of a launch vehicle tank provided by the present application;

[0022] Figure 2 It is a schematic diagram of the anti-sway plate, tunnel tube, upper and lower partitions of the launch vehicle tank provided by the present application;

[0023] Figure 3 is a schematic diagram of an accumulator of a launch vehicle tank provided by the present application;

[0024] Figure 4 It is a schematic diagram of a first top cover frame and a first cylindrical section frame of an accumulator of a launch vehicle tank provided by the present application;

[0025] Figure 5 Schematic diagram of a first top cover assembly of an accumulator of a launch vehicle tank provided by the present application;

[0026] Figure 6 Schematic diagram of a first cylindrical section assembly of an accumulator of a launch vehicle tank provided by the present application;

[0027] Figure 7 It is a schematic diagram of the exhaust assembly of the launch vehicle tank provided in this application. DETAILED DESCRIPTION

[0028] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be interpreted as limiting the present invention.

[0029] like Figure 1 As shown, the present application provides a launch vehicle tank, including: an upper partition 110, a lower partition 120, a guide plate 130, an accumulator 140, a liquid outlet pipe 150, an exhaust assembly 160, an anti-sway plate 170 and a 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 a receiving cavity inside, and the outer wall of the accumulator 140 is a mesh structure. In this way, the propellant in the tank body 210 can enter the receiving cavity of the accumulator 140, and because the propellant forms a liquid film on the outer wall of the accumulator 140 with the mesh structure, it can prevent the gas in the tank body 210 from entering the receiving cavity of the accumulator 140, thereby ensuring that the propellant in the receiving cavity of the accumulator 140 does not contain air, so that the engine can be provided with propellant without air from the receiving cavity of the accumulator 140.

[0031] Optionally, the accumulator 140 is cylindrical. Optionally, the axis of the accumulator 140 is coaxial with the axis of the tank body 210, so that the accumulator 140 can be located at the lowest point of the tank body 210. Optionally, the tank body 210 has a tunnel tube 220 that runs through the tank body 210 from top to bottom, so as to pass through the propellant supply pipe of other tanks. In this case, the accumulator 140 passes through the tunnel tube 220 and is surrounded by the outside of the tunnel tube 220. Optionally, the volume V of the accommodating chamber of the accumulator 140 is x Should meet V x ≥n1·q v ·t s , where t s is the sinking time, q v is the volume flow rate of a component of the engine (the propellant in the launch vehicle tank, specifically the oxidizer or fuel), n1 is the coefficient, and takes a value of 1.5 to 2.0.

[0032] like Figure 3 As shown, the accumulator 140 includes: a first top cover assembly 141, a first cylindrical section assembly 142, a second top cover assembly 143 and a second cylindrical section assembly 144; wherein, the first top cover assembly 141 is fixed to the upper end opening of the first cylindrical section assembly 142 to close the upper end opening of the first cylindrical section 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 end opening of the first cylindrical section 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 end opening of the second cylindrical section assembly 144, and the lower end opening of the second cylindrical section 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 pressing plate 1414, and the first top cover frame 1411, the first top cover support plate 1412, the first top cover screen 1413 and the first top cover pressing plate 1414 are stacked and fixed together from the inside to the outside. 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 pressing plate 1414 are stacked and welded together from the inside to the outside. Specifically, the first top cover support plate 1412, the first top cover screen 1413 and the first top cover pressing plate 1414 can be stacked and welded, and then welded to the first top cover frame 1411.

[0034] Alternatively, the first top cover frame 1411 is a circular or annular metal plate, and the metal plate is provided with a fan-shaped window in the radial direction. When there is no tunnel tube 220 in the tank body 210, the accumulator 140 does not need to pass through the tunnel tube 220. In this case, the first top cover frame 1411 is a circular metal plate; when there is a tunnel tube 220 in the tank body 210, the accumulator 140 needs to pass through the tunnel tube 220. In this case, the first top cover frame 1411 is a circular metal plate. Alternatively, the first top cover support plate 1412 and the first top cover pressure plate 1414 are fan-shaped metal plates, and fan-shaped windows are provided inside the fan-shaped metal plates. Alternatively, the thickness of the first top cover support plate 1412 and the first top cover pressure plate 1414 is 1 mm to 2 mm, and rounded corners, R1 to R2, are provided at the four corners of the fan-shaped window. Optionally, 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 has to pass through the first cylindrical section 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 a circular 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 section assembly 142 includes: a first cylindrical section skeleton 1421, a first cylindrical section support plate 1422, a first cylindrical section screen 1423 and a first cylindrical section pressure plate 1424; and the first cylindrical section skeleton 1421, the first cylindrical section support plate 1422, the first cylindrical section screen 1423 and the first cylindrical section pressure plate 1424 are stacked and fixed together from the inside to the outside. Optionally, the first cylindrical section skeleton 1421, the first cylindrical section support plate 1422, the first cylindrical section screen 1423 and the first cylindrical section pressure plate 1424 are stacked and welded together from the inside to the outside. Specifically, the first cylindrical section support plate 1422, the first cylindrical section screen 1423 and the first cylindrical section pressure plate 1424 can be stacked and welded, and then welded to the first cylindrical section skeleton 1421.

[0037] Optionally, the first cylindrical section skeleton 1421 is a metal plate wrapped into a cylindrical shape, and a rectangular window is provided in the axial direction of the metal plate. Optionally, the first cylindrical section support plate 1422 and the first cylindrical section pressure plate 1424 are rectangular metal plates, and a rectangular window is provided inside the rectangular metal plate. Still optionally, the thickness of the first cylindrical section support plate 1422 and the first cylindrical section pressure plate 1424 is 1mm to 2mm, and the four corners of the rectangular window are rounded, R1 to R2. Optionally, the first cylindrical section screen 1423 is a 325×2300 metal twill screen, which is rectangular in shape.

[0038] The structure of the second cylindrical segment assembly 144 is similar to that of the first cylindrical segment assembly 142 , with the only difference being that the height of the second cylindrical segment assembly 144 is smaller than the height of the first cylindrical segment assembly 142 .

[0039] like Figure 1 As shown, the inlet end of the liquid outlet pipe 150 is connected to the accommodating chamber of the accumulator 140, the liquid outlet pipe 150 passes through the outer wall of the tank body 210, and the liquid outlet 151 of the liquid outlet pipe 150 is located outside the tank body 210, so that the non-air-entrained propellant in the accommodating chamber of the accumulator 140 can be led out to the outside of the tank body 210, and then provided to the engine. Optionally, the inlet end of the liquid outlet pipe 150 is located on the side wall of the accumulator 140 and close to the upper end of the accumulator 140. Also optionally, the liquid outlet pipe 150 passes through the bottom of the tank body 210.

[0040] The exhaust assembly 160 has an exhaust cavity inside, and the top of the exhaust assembly 160 is also a mesh structure. The upper end of the accumulator 140 has a plurality of exhaust holes. The lower ends of all the exhaust assemblies 160 are fixed to the upper end of the accumulator 140, and the lower end of each exhaust assembly 160 is connected to the exhaust cavity of the exhaust assembly 160 and the accommodating cavity of the accumulator 140 through an exhaust hole. In this way, when the propellant is filled, when the upper end of the accumulator 140 is soaked by the propellant, a liquid film will be formed on all the outer wall meshes of the accumulator 140. However, at this time, 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. In this way, after the liquid film is formed on all the outer walls of the accumulator 140, this part of the gas cannot be discharged from the accumulator 140, thereby providing the engine with air-entrained propellant. However, in the present application, an exhaust assembly 160 is provided at the upper end of the accumulator 140, so that even if the upper end of the accumulator 140 is infiltrated by the propellant and a liquid film is formed on all outer walls of the accumulator 140, the gas in the containing cavity of the accumulator 140 will also flow upward into the exhaust cavity of the exhaust assembly 160. Moreover, since the position of the exhaust assembly 160 is higher than the top of the accumulator 140, it is possible to ensure that the gas is discharged from the exhaust assembly 160, and the interior of the accumulator 140 is filled with propellant, thereby providing the engine with propellant without air entrainment.

[0041] Optionally, the exhaust assembly 160 is also cylindrical. Optionally, the axis of the exhaust assembly 160 is in the same direction as the axis of the tank body 210. Optionally, all the exhaust assemblies 160 are 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 connected from top to bottom to form an exhaust cavity, 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 end opening of the exhaust assembly frame 161 to close the upper end 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. Optionally, 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 component skeleton 161 is a cylindrical hollow structure, and the upper end opening of the exhaust component skeleton 161 is a ring window. Optionally, the exhaust component support plate 162 and the exhaust component pressure plate 164 are circular metal plates, and a circular window is provided inside the circular metal plate. Still optionally, the thickness of the exhaust component support plate 162 and the exhaust component pressure plate 164 is 1mm to 2mm. Optionally, the exhaust component screen 163 is a 200×1400 metal twill screen in a circular shape. When the number of engine starts is greater than 2 times, the exhaust of the propellant refilling process can be achieved by increasing the area of ​​the exhaust component screen 163 and increasing the height of the exhaust component 160.

[0043] like Figure 1 As shown, the lower edges of the plurality of guide plates 130 are fixed to the bottom of the tank body 210, and the guide plates 130 have a plurality of through holes extending through both sides, so that the propellant can pass through the guide plates 130 through the through holes, and the propellant can be more easily gathered around the guide plates 130 under microgravity conditions; in addition, the inner edge of each guide plate 130 is connected to the outer wall of the accumulator 140, where "inner" refers to the side close to the accumulator 140, so that the propellant gathered around the guide plates 130 is guided to the accumulator 140, thereby ensuring the integrity of the liquid film on the outer wall of the accumulator 140, while suppressing the shaking of the propellant outside the accumulator 140, and ensuring that the accumulator 140 can provide the engine with propellant without air entrainment.

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

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

[0046] Optionally, if the tank body 210 has a tunnel tube 220 that passes through the tank body 210 from top to bottom, the upper partition 110 is a circular metal plate to pass through the tunnel tube 220; if the tank body 210 does not have a tunnel tube 220, the upper partition 110 is a circular metal plate; the lower partition 120 is a circular metal plate to pass through the accumulator 140. Optionally, the lower partition 120 is arranged in the middle of the accumulator 140 near the bottom. Optionally, all the upper circular holes 111 are evenly distributed on the upper partition 110, and all the lower circular holes 121 are evenly distributed on the lower partition 120. Optionally, the total area of ​​the upper circular holes 111 opened on the upper partition 110 should not be less than 2.0 to 2.5 times the flow area of ​​the liquid outlet pipe 150, and the total area of ​​the lower circular holes 121 opened on the lower partition 120 should not be less than 1.5 to 2.0 times the flow area of ​​the liquid outlet pipe 150. Still optionally, the liquid volume V2 below the lower partition 120 (including the liquid volume Vx of the storage chamber in the accumulator 140) should be no less than 2.0 to 2.5 times of Vx, and the liquid volume V3 below the upper partition 110 (including the liquid volume Vx of the storage chamber in the accumulator 140) should be no less than 2.5 to 3.5 times of Vx.

[0047] like Figure 1 and Figure 2 As shown, the outer edges of the plurality of anti-sway plates 170 are used to be fixed to the inner wall of the tank body 210 to prevent the propellant in the tank body 210 from swaying. Optionally, the anti-sway plates 170 are unevenly distributed on the inner wall of the cylindrical section of the tank body along the axis direction of the tank body 210.

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

[0049] The launch vehicle tank in the present application can ensure that the tank provides the engine with non-air-entrained propellant, and reduces the complexity and weight of the system, improves the rocket's carrying capacity and working reliability, improves launch efficiency, and reduces mission costs.

[0050] It will be apparent to those skilled in the art that the 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 the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0051] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A launch vehicle tank, characterized in that: include: Upper baffle, lower baffle, guide plate, accumulator, liquid outlet pipe, exhaust assembly, anti-sway plate and tank body; The lower end of the accumulator is fixed to the bottom of the tank body, and the interior of the accumulator has a receiving cavity, and the outer wall of the accumulator is a screen structure; The inlet end of the liquid outlet pipe is connected to the accommodating chamber of the accumulator, the liquid outlet pipe passes through the outer wall of the tank body, and the liquid outlet of the liquid outlet pipe is located outside the tank body; The exhaust assembly has an exhaust cavity inside, the top of the exhaust assembly is a screen structure, the upper end of the accumulator has a plurality of exhaust holes, the lower ends of all the exhaust assemblies are fixed to the upper end of the accumulator, and the lower end of each exhaust assembly realizes communication between the exhaust cavity of the exhaust assembly and the accommodating cavity of the accumulator through an exhaust hole; The lower edges of the plurality of guide plates are fixed to the bottom of the tank body, and the guide plates are provided with a plurality of through holes penetrating 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 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, and the middle part of the lower partition passes through the accumulator and is fixedly connected to the accumulator; a plurality of upper circular holes are opened on the upper partition, and a plurality of lower circular holes are opened on the lower partition, and the diameter of the upper circular holes is greater than the diameter of the lower circular holes; The outer edges of the plurality of anti-sway plates are fixed to the inner wall of the tank body.

2. The launch vehicle tank according to claim 1, characterized in that: The accumulator includes: a first top cover assembly, a first cylindrical segment assembly, a second top cover assembly, and a second cylindrical segment assembly; Among them, the first top cover assembly is fixed to the upper end opening of the first cylindrical section assembly to close the upper end 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 end 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 end opening of the second cylindrical section assembly, and the lower end opening of the second cylindrical section assembly is fixed to the bottom of the tank body.

3. The launch vehicle 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 pressing plate, and the first top cover frame, the first top cover support plate, the first top cover screen and the first top cover pressing plate are stacked and fixed together from inside to outside.

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

5. The launch vehicle tank according to claim 1 or 2, characterized in that: The volume V of the accumulator chamber x Meet V x ≥n1·q v ·t s , where t s is the sinking time, q v is the volume flow rate of a component of the engine, n1 is the coefficient, and takes 1.5~2.

0.

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

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

8. The launch vehicle tank according to claim 1 or 2, characterized in that: The through hole on the guide plate is a circular hole, and the diameter of the circular hole is D=(0.3-0.5)H, wherein H is the height of the guide plate corresponding to the position of the circular hole.

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

10. The launch vehicle 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 accommodating chamber in the accumulator.

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