A tank suitable for a reusable launch vehicle

Abstract

The application discloses a tank suitable for a reusable carrier, relates to the field of reusable earth-to-space shuttles, and comprises a tank body and a partition plate assembly arranged in the tank body. The partition plate assembly comprises a passage communicating between two sides of the partition plate and a movable plate. Propellant can flow downward through the passage. When the propellant shakes upward, the propellant pushes the movable plate to move upward and closes the passage. The tank can adapt to flight overload. When propellant moves forward due to the overload, the movable plate moves forward to close the opening of the top plate, so that the propellant is closed at the bottom of the tank, the movement of the propellant to the front bottom of the tank is effectively inhibited, and the manufacturing scheme is simple and reliable and has high universality.

Description

Technical Field

[0001] This invention relates to a storage tank suitable for reusable launch vehicles, specifically for propellant storage tanks in reusable launch vehicles, and belongs to the field of reusable space-to-ground transport technology. Background Technology

[0002] Anti-sloshing structures are an important component of launch vehicle propellant tanks, playing a crucial role in improving propellant sloshing damping and reducing propellant sloshing amplitude. Reusable spacecraft have significantly different anti-sloshing requirements for their propellant tanks compared to conventional rockets. Reusable spacecraft must consider not only propellant sloshing in the booster tanks but also propellant management during the reentry phase.

[0003] The requirements for propellant tank anti-sloshing in reusable spacecraft differ significantly from those in traditional rockets. Reusable spacecraft must consider not only the sloshing of propellant in the booster tanks but also the management of propellant during reentry. For lift-type reusable spacecraft, during unpowered reentry, the spacecraft primarily experiences normal overload. If the remaining propellant in the tanks is not effectively controlled, the sloshing of the propellant within the tanks will severely affect the spacecraft's center of gravity, adversely impacting its attitude control. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a propellant tank suitable for reusable launch vehicles, which solves the problem of the propellant in the tank swaying significantly towards the front bottom of the tank after the active phase of the reusable launch vehicle is shut down.

[0005] The technical solution of this invention is:

[0006] A tank suitable for reusable launch vehicles includes a tank body and a partition assembly disposed within the tank body. The partition assembly includes a passage connecting the two sides of the partition and a movable plate. Propellant can flow downward through the passage. When the propellant moves upward, the propellant pushes the movable plate upward to close the passage.

[0007] The partition assembly includes a bottom plate and a top plate arranged sequentially from bottom to top. Both the bottom plate and the top plate are fixedly connected to the inner wall of the box. The bottom plate is hollow, and the top plate has a circular through hole. The passage is formed from the hollow structure of the bottom plate to the circular through hole of the top plate. The movable plate is located between the bottom plate and the top plate and moves along the axis of the box. The outer diameter of the movable plate is smaller than that of the bottom plate and larger than that of the circular through hole.

[0008] The hollowed-out shape of the base plate is a regular hexagon.

[0009] The base plate is positioned inside the tank at a height h above the liquid level, where h is the liquid level height after the aircraft is powered off.

[0010] The circular through hole is located in the middle of the top plate, which is a tapered structure whose outer diameter gradually decreases along the direction away from the bottom plate.

[0011] The diameter of the circular through hole is: d = α × β × D.

[0012] Where d is the diameter of the circular through hole; D is the diameter of the tank section; α is the viscosity coefficient of the propellant; and β is the propellant type coefficient.

[0013] An overflow notch is provided at the edge of the top plate.

[0014] The movable plate is a spherical thin plate, with the middle part of the movable plate protruding towards the bottom plate.

[0015] The density of the movable plate must be greater than the density of the propellant.

[0016] Multiple guide posts are provided between the top plate and the bottom plate, and the guide posts pass through the movable plate and are slidably connected to the movable plate.

[0017] The baffle assembly does not restrict the flow of propellant from the rear bottom of the tank, ensuring uninterrupted propellant delivery to the engine when needed during flight. However, it does restrict the flow of propellant from the front bottom. When the engine shuts down or the aircraft experiences axial overload, causing fluid to flow towards the top of the tank, the baffle assembly actively restricts this flow, confining the propellant to a limited area at the bottom and reducing the space for fluid movement, thus minimizing propellant sloshing. Since the tank filling port is typically located at the bottom, the baffle also allows propellant to flow smoothly and slowly from the bottom to the top of the tank during filling.

[0018] In summary, this application includes at least the following beneficial technical effects:

[0019] (1) The tank partition scheme proposed in this invention is adaptive to flight overload. When propellant moves forward due to overload, the movable plate moves forward to close the top plate opening, thereby sealing the propellant at the bottom of the tank. It effectively suppresses the movement of propellant towards the front bottom of the tank. The manufacturing scheme is simple, reliable, and highly versatile, making it very suitable for reusable launch vehicles.

[0020] (2) The cryogenic storage tank insulation support structure proposed in this invention can effectively insulate and withstand large normal loads.

[0021] (3) It does not restrict the flow of the tank to the rear bottom, and does not affect the normal delivery of propellant from the tank to the engine when the engine needs propellant during flight. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of a storage tank suitable for a reusable vehicle, as described in an embodiment of this application.

[0023] Figure 2 This is a schematic diagram of the top plate structure in an embodiment of this application;

[0024] Figure 3 This is a schematic diagram of the structure of the base plate in an embodiment of this application;

[0025] Figure 4 This is a schematic diagram of the structure of the movable plate and guide column in the embodiments of this application;

[0026] Figure 5 This is a simulation analysis diagram based on the structure of the tank with partition assembly in the embodiments of this application.

[0027] Explanation of reference numerals in the attached drawings: 1. Top plate; 11. Circular through hole; 12. Overflow notch; 2. Bottom plate; 3. Movable plate; 4. Guide column; 5. Box body. Detailed Implementation

[0028] The present application will now be described in further detail with reference to the accompanying drawings and specific embodiments:

[0029] This application discloses a storage tank suitable for reusable vehicles, such as... Figure 1 As shown, it includes a housing 5 and a baffle assembly disposed inside the housing 5. The two ends of the housing 5 are respectively the rear bottom of the tank and the front bottom of the tank. The propellant can flow downward through the baffle assembly. When the propellant moves upward, the baffle assembly restricts the propellant from moving upward.

[0030] like Figure 1 As shown, the partition assembly includes a top plate 1, a bottom plate 2, a movable plate 3, and a guide post 4. The top plate 1 and the bottom plate 2 are welded and fixed near the rear bottom of the tank, and the top plate 1 is located on the side of the bottom plate 2 away from the rear bottom of the tank. The movable plate 3 and the guide post 4 are arranged between the top plate 1 and the bottom plate 2. The guide post 4 is connected to the top plate 1 and the bottom plate 2 to guide the movable plate 3 and guide the movable plate 3 to move vertically between the top plate 1 and the bottom plate 2, preventing the movable plate 3 from moving laterally or tipping over.

[0031] like Figure 2 As shown, the top plate 1 is a conical structure, and its outer diameter gradually decreases along the direction away from the bottom plate 2. A circular through-hole 11 with a diameter of d is provided in the middle of the top plate 1. The top plate 1 and the bottom plate 2 form an open cavity structure. When the reusable launch vehicle is erected on the launch pad for refueling, the propellant is slowly added from the bottom and rises from the through-hole to the designated refueling level. During the launch vehicle's active phase flight, the propellant above the top plate 1 can reach the delivery pipe at the bottom of the tank through the through-hole without affecting the normal refueling of the tank and its flight use. Four liquid overflow notches 12 are provided on the connection side between the top plate 1 and the tank, allowing the liquid located between the conical top plate 1 and the tank sidewall to flow to the bottom without affecting the normal supply of propellant.

[0032] The diameter d of the circular through hole 11 in the top plate 1 can be calculated using the following formula:

[0033] d=α×β×D

[0034] Wherein, d is the diameter of the circular through hole 11 and the hexagonal through hole 11 of the top plate 1; D is the diameter of the tank section; α is the viscosity coefficient of the propellant, with a value of 1 for liquid oxygen, 1.2 for kerosene, 1.1 for methane, and 1.05 for liquid hydrogen. Other propellants can be determined by referring to the above-mentioned propellant viscosity relationship; β is the propellant type coefficient, with a value of 0.5 for room temperature propellants and 0.4 for cryogenic propellants.

[0035] An overflow notch 12 is provided at the edge of the top plate 1. In addition to flowing down through the circular through hole 11, the propellant above the top plate 1 can flow down through the overflow notch 12 between the upper surface of the top plate 1 and the inner wall of the housing 5, thus preventing the propellant from accumulating on the upper surface of the top plate 1.

[0036] like Figure 3 As shown, the base plate 2 is designed with a hollow structure, with the hollow shape set as multiple regular hexagons or other shapes to facilitate the passage of liquid and to a certain extent suppress sloshing. The base plate 2 is set at a position slightly higher than the liquid surface h according to the liquid level height after the aircraft is shut down. The value of h controls the activity space of the remaining propellant, and the specific height value is determined according to the overall simulation of the launch vehicle control.

[0037] like Figure 4 As shown, the movable plate 3 is a spherical thin plate with its center protruding towards the bottom plate 2. It is positioned between the top plate 1 and the bottom plate 2, and its diameter is larger than the diameter of the through hole in the top plate 1. When the carrier experiences a forward overload after shutdown, the movable plate 3, under inertia, moves upward and adheres to the top plate 1. Because the diameter of the movable plate 3 is larger than the diameter of the through hole in the top plate 1, it completely blocks the through hole, preventing the propellant from moving upward to the top of the tank and confining the propellant in the smaller tank space below the top plate 1. When the movable plate 3 falls downward onto the bottom plate 2, because it is a spherical plate, it causes minimal obstruction to the perforated portion of the bottom plate 2's hollow structure. At this time, the baffle assembly does not affect the upward or downward flow of the liquid.

[0038] The density of the movable plate 3 material must be greater than the density of the propellant. After the propellant is loaded in the upright position, the density of the movable plate 3 is greater than that of the propellant. It is located at the bottom of the tank and does not hinder the normal loading and supply of propellant.

[0039] The implementation principle of this application is as follows: Figure 5As shown, when the engine requires propellant during flight, the baffle assembly does not affect the normal propellant delivery from the tank to the engine. When the engine shuts down or the aircraft experiences axial overload, and the propellant flows towards the top of the tank, due to inertia or the propellant's inherent force, the propellant can push the movable plate 3 towards the top plate 1 until the movable plate 3 blocks the circular through-hole 11 of the top plate 1. At this point, the baffle assembly actively restricts the flow of liquid towards the front bottom of the tank, confining the propellant within a limited area at the bottom, reducing the liquid's flow space, and thus reducing propellant sloshing. The tank filling port is generally located at the bottom of the tank. When the propellant is added slowly and uniformly, the baffle allows the propellant to flow smoothly from the bottom to the top of the tank.

[0040] The contents not described in detail in this invention are common knowledge in the field.

[0041] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope defined in the claims of the present invention.

Claims

1. A tank suitable for a reusable launch vehicle, characterized by: The application relates to a propellant tank, which comprises a tank body (5), a partition assembly arranged in the tank body (5), a passageway for the propellant to flow downwards and an activity plate (3) which is pushed upwards by the propellant to close the passageway when the propellant shakes upwards.

2. A tank suitable for use with a reusable carrier according to claim 1, wherein: The partition assembly comprises a bottom plate (2) and a top plate (1) arranged in sequence from bottom to top, the bottom plate (2) and the top plate (1) are fixedly connected with the inner wall of the tank body (5), the bottom plate (2) is in a hollow shape, the top plate (1) is provided with a circular through hole (11), the hollow structure of the bottom plate (2) forms the passageway to the circular through hole (11) of the top plate (1), the activity plate (3) is located between the bottom plate (2) and the top plate (1) and moves along the axial direction of the tank body (5), the outer diameter of the activity plate (3) is smaller than that of the bottom plate (2) and larger than that of the circular through hole (11).

3. A tank suitable for use with a reusable carrier according to claim 2, wherein: The hollow shape of the bottom plate (2) is a regular hexagon.

4. A tank suitable for use with a reusable carrier according to claim 2, wherein: The bottom plate (2) is arranged in the tank body (5) at a position higher than the liquid level h, and h is the liquid level height after the aircraft is shut down.

5. A tank suitable for use with a reusable carrier according to claim 2, wherein: The circular through hole (11) is arranged in the middle of the top plate (1), and the top plate (1) is a conical structure with a gradually decreasing outer diameter in the direction away from the bottom plate (2).

6. A tank suitable for use with a reusable carrier according to claim 2, wherein: The diameter of the circular through hole (11) is d = alpha * beta * D, wherein d is the diameter of the circular through hole (11), D is the diameter of the tank barrel section, alpha is the viscosity coefficient of the propellant, and beta is the type coefficient of the propellant.

7. A tank suitable for use with a reusable carrier according to claim 2, wherein: An overflow notch (12) is arranged at the edge position of the top plate (1).

8. A tank suitable for use with a reusable carrier according to claim 2, wherein: The activity plate (3) is a spherical thin plate, and the middle part of the activity plate (3) is convex to the bottom plate (2).

9. A tank suitable for use with a reusable carrier according to claim 2, wherein: The density of the activity plate (3) is greater than that of the propellant.

10. A tank suitable for use with a reusable carrier according to claim 2, wherein: A plurality of guide columns (4) are arranged between the top plate (1) and the bottom plate (2), the guide columns (4) pass through the activity plate (3) and are slidably connected with the activity plate (3).

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