Storage box for vertically recycling carrier rocket propellants

Abstract

The invention is suitable for the field of spaceflight carrier rockets, and provides a vertical recovery carrier rocket propellant storage box which comprises an upper cabin, a lower cabin, a partition plate assembly, a flow accumulator, an anti-shaking plate and an anti-vortex and anti-collapse device. The storage box is divided into an upper cabin and a lower cabin through the partition plate assembly. The lower cabin is provided with a flow accumulator, and an outlet of the flow accumulator is provided with an anti-vortex and anti-collapse device; and the anti-shaking plates are unevenly distributed on the upper cabin and the lower cabin along the axis of the storage box. According to the invention, the management problem of vertical recovery carrier rocket propellants is solved, and the ignition condition of multiple starting of an engine can be met; a special bottom sinking system is omitted, and compared with an existing scheme adopting a bottom sinking engine, the system complexity is reduced, the mass of a rocket body is reduced, and the reliability of first-sublevel recycling work is improved.

Description

Technical Field

[0001] The present invention belongs to the field of space launch vehicles, and particularly relates to a propellant tank for a vertically recoverable launch vehicle. Background Art

[0002] With the continuous development of the space field, the application demand for vertical recovery technology in launch vehicles is increasing day by day. Under this background, the power system faces a series of new challenges, among which technologies such as return-stage propellant management, large-range thrust adjustment, and multiple engine starts have become the key points.

[0003] During the flight of the first stage of a vertically recoverable launch vehicle, its process mainly includes multiple stages such as the ascent stage, separation of the first and second stages, attitude adjustment of the first stage of the rocket, reverse thrust deceleration in the reentry stage, aerodynamic deceleration, and reverse thrust deceleration before landing; after the separation of the first and second stages is completed, the first stage will enter the glide attitude adjustment stage; at this time, it will be affected by various interference factors such as the aftereffect of the shutdown of the first-stage engine, the force of gas-driven separation, and the attitude control force; these interferences cause the cryogenic propellant in the tank to mix violently with the high-temperature gas pillow, thereby triggering a series of problems, such as propellant floating, tank pressure reduction, propellant temperature increase, and gas-liquid phase change, which have a serious impact on the ignition conditions for the second start of the engine.

[0004] At present, there are some existing technical solutions for the above problems. For example, the existing patent CN116971894A proposes a combined solution of an isolation structure and a retention device, and it is necessary to combine the continuous forward thrust operation of a submerged engine to achieve propellant management; however, this solution has many drawbacks: using a submerged engine undoubtedly increases the complexity of the system; at the same time, in order to generate the submerged force, it is necessary to consume propellant or gas in a high-pressure gas cylinder, which undoubtedly increases the system weight; moreover, the increase in system complexity and the additional consumption also correspondingly reduce the reliability of the recovery work of the first stage.

[0005] Again, the existing patent CN117823296A adopts a partition tank combined with a pneumatically controlled isolation valve solution to achieve propellant management. However, in this solution, since the isolation valve is pneumatically controlled, it is necessary to introduce multiple gas pipeline paths into the tank, making the structure complex and the reliability reduced accordingly.

[0006] In view of the above defects existing in the existing technical solutions, therefore, there is an urgent need for a propellant tank for a vertically recoverable launch vehicle that can effectively solve the above problems. Summary of the Invention

[0007] The purpose of the embodiments of the present invention is to provide a propellant tank for a vertically recoverable launch vehicle to solve the problems mentioned in the above background art.

[0008] To achieve the above object, the present invention provides the following technical solutions:

[0009] A propellant tank for a vertical recovery launch vehicle, characterized in that it includes: an upper cabin, a lower cabin, a partition assembly, a accumulator, an anti-slosh plate, an anti-vortex and anti-collapse device, a pressurization port, an exhaust port, a liquid outlet and a filling port; wherein, the partition assembly divides the tank into an upper cabin and a lower cabin, and an accumulator is arranged in the lower cabin; a pressurization port and an exhaust port are arranged at the top of the upper cabin, a gas damper is installed on the pressurization port, and a safety overflow valve is installed on the exhaust port; a liquid outlet and a filling port are arranged at the bottom of the lower cabin, and an anti-vortex and anti-collapse device is arranged at the liquid outlet.

[0010] A further technical solution is that the volume of the lower cabin is smaller than that of the upper cabin, and is not less than 1.2 to 1.5 times the amount of propellant used by the engines in the reentry reverse thrust deceleration section and the pre-landing reverse thrust deceleration section.

[0011] A further technical solution is that the partition assembly includes a partition, a check valve and a screen window. Among them, the partition is an inner concave ellipsoidal shell, and screen windows are evenly arranged in the outermost circle, and check valves are evenly arranged in the remaining windows.

[0012] A further technical solution is that the screen window includes a cover, a screen window pressing plate, a screen, a screen window support plate and a screen window skeleton, and the cover, the screen window pressing plate, the screen, the screen window support plate and the screen window skeleton are stacked and fixed together from top to bottom; wherein, the screen window support plate and the screen window pressing plate are metal plates with circular windows, and the thickness is 1 mm to 2 mm; the screen is a 200×1400 metal twill screen; the cover is a hollow cylindrical metal structure with round holes on the surface.

[0013] A further technical solution is that the check valve adopts a butterfly or wafer type check valve, and the total flow area is not less than 1.5 to 2.0 times the flow area of the liquid outlet.

[0014] A further technical solution is that the accumulator is a hollow metal structure, including a top cover, an exhaust pipe assembly and a conical section assembly.

[0015] A further technical solution is that the exhaust pipe assembly includes an exhaust pipe assembly skeleton, an exhaust pipe assembly support plate, an exhaust pipe assembly screen and an exhaust pipe assembly pressing plate; and the lower end of the exhaust assembly skeleton is fixed to the top cover; the exhaust assembly support plate, the exhaust assembly screen and the exhaust assembly pressing plate are stacked and fixed together from bottom to top; and the exhaust assembly support plate, the exhaust assembly screen and the exhaust assembly pressing plate are fixed to the upper end opening of the exhaust assembly skeleton to close the upper end opening of the exhaust assembly skeleton; wherein, the exhaust pipe assembly skeleton is a hollow structure with a cylindrical window, the exhaust pipe assembly support plate and the exhaust pipe assembly pressing plate are metal plates with circular windows, and the thickness is 1 mm to 2 mm, and the exhaust assembly screen is a 200×1400 metal twill screen.

[0016] Further technical solution: The conical section assembly includes a conical section framework, conical section support plates, conical section pressing plates, and a conical section screen, and the conical section framework, conical section support plates, conical section screen, and conical section pressing plates are stacked and fixed together from the inside to the outside; among them, the conical section framework is a frustum-shaped annular metal plate, and the metal plate is provided with fan-shaped windows along the radial direction; the conical section support plates and conical section pressing plates are metal plates with square windows, with a thickness of 1 mm to 2 mm, and rounded corners are provided at the four corners of the square windows, R1 to R2; the conical section screen is a 325×2300 metal twill screen.

[0017] Further technical solution: The anti-slosh plates are unevenly distributed on the upper tank and the lower tank along the axis of the storage tank.

[0018] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0019] In the present invention, the dedicated sinking system is abandoned. Compared with the existing solutions using sinking engines, the system complexity is reduced, the extra weight brought by the sinking system is avoided, the mass of the rocket body is reduced, and the overall performance of the launch vehicle is improved;

[0020] In the present invention, through the organic combination of one-way valves, partition windows, and accumulators, the problem of propellant management in the return stage is effectively solved; in different flight stages, the flow and state of the propellant can be accurately controlled to meet the conditions for the engine to restart and ignite, and the adverse effects of problems such as propellant floating and gas-liquid phase change on engine startup are avoided;

[0021] In the present invention, the adaptability to working conditions is enhanced: it can be extended and applied to the working conditions of multiple engine startups. Compared with the prior art, it has a wider applicability and can better meet the diverse mission requirements of vertical recovery launch vehicles;

[0022] In the present invention, the propellant has a wide applicability: the storage tank is applicable to both normal-temperature propellants and cryogenic propellants, expanding the application range and improving the versatility and practicality.

[0023] In order to more clearly illustrate the structural features and functions of the present invention, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic structural diagram of the upper tank of the present invention;

[0025] Figure 2 It is a schematic structural diagram of the partition assembly of the present invention;

[0026] Figure 3 It is a schematic structural diagram of the screen window of the present invention;

[0027] Figure 4 It is a schematic structural diagram of the conical section assembly of the present invention;

[0028] Figure 5 This is a schematic structural diagram of the exhaust pipe assembly of the present invention.

[0029] In the figure: 1. Upper cabin; 2. Lower cabin; 3. Partition assembly; 31. Partition; 32. Screen window; 33. Check valve; 321. Protective cover; 322. Screen window pressing plate; 323. Screen; 324. Screen window support plate; 325. Screen window frame; 4. Accumulator; 41. Exhaust pipe assembly; 411. Exhaust pipe frame; 412. Exhaust pipe support plate; 413. Exhaust pipe screen; 414. Exhaust pipe pressing plate; 42. Top cover; 43. Cone section assembly; 431. Cone section frame; 432. Cone section support plate; 433. Cone section screen; 434. Cone section pressing plate; 5. Anti-vortex and anti-collapse device; 6. Anti-slosh plate; 7. Boost port; 8. Exhaust port; 9. Liquid outlet; 10. Filling port; 11. Gas damper; 12. Safety overflow valve. Specific embodiments

[0030] In order to make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0031] The following describes in detail the specific implementation of the present invention with reference to specific embodiments.

[0032] Embodiment 1

[0033] As Figures 1 - 5 shown, the embodiment of the present invention provides a propellant tank for a vertical recovery launch vehicle, including: an upper cabin 1, a lower cabin 2, a partition assembly 3, an accumulator 4, an anti-slosh plate 6, an anti-vortex and anti-collapse device 5, a boost port 7, an exhaust port 8, a liquid outlet 9, and a filling port 10.

[0034] The upper cabin 1 is used to store the propellant and provide the propellant for the engine during the ascending stage. The top of the upper cabin 1 is provided with a boost port 7 and an exhaust port 8;

[0035] The lower cabin 2 has a volume smaller than that of the upper cabin 1 and is not less than 1.2 - 1.5 times the amount of propellant used by the engines during the reentry reverse thrust deceleration stage and the pre-landing reverse thrust deceleration stage, and is used to provide the propellant for the engines during the reentry reverse thrust deceleration stage and the pre-landing reverse thrust deceleration stage;

[0036] The anti-vortex and anti-collapse device 5 is arranged at the liquid outlet 9 and is used to prevent the occurrence of vortices and collapses, reduce the mass of unusable propellant in the tank, and improve the propellant utilization rate;

[0037] The anti-slosh plate 6 is unevenly distributed along the axis of the tank on the upper cabin 1 and the lower cabin 2 and is used to reduce the sloshing of the propellant, avoid excessive mixing of the propellant with the gas cushion, and ensure the stable state of the propellant;

[0038] The pressurizing port 7 is arranged at the top of the upper tank 1 and is used for pressurizing the storage tank. A gas damper 11 is installed thereon. When the storage tank is pressurized, the gas damper 11 absorbs the gas flow energy through the porous structure to avoid the impact of the pressurizing gas on the liquid level;

[0039] The exhaust port 8 is arranged at the top of the upper tank 1 and is used for discharging the excess gas in the storage tank. A safety overflow valve 12 is installed thereon. When the pressure in the storage tank exceeds the set threshold value, the safety overflow valve 12 automatically opens to discharge the excess gas and maintain the pressure stability of the storage tank;

[0040] The liquid outlet 9 is arranged at the bottom of the lower tank 2 and is used for supplying propellant to the engine;

[0041] The filling port 10 is arranged at the bottom of the lower tank 2 and is used for filling propellant into the storage tank;

[0042] The partition assembly 3 is connected between the upper tank 1 and the lower tank 2 and is used for dividing the storage tank into the upper tank 1 and the lower tank 2. It includes a partition 31, a check valve 33 and a screen window 32. The partition 31 is an inner concave ellipsoidal shell. The screen windows 32 are evenly arranged in the outermost circle of the partition assembly 3, and the check valves 33 are evenly arranged in the remaining windows; the screen windows 32 and the check valves 33 are connected to the partition by welding;

[0043] As Figure 2 shown, specifically, the check valve 33 adopts a butterfly or wafer check valve, and the total flow area of the check valve 33 is not less than 1.5 to 2.0 times the flow area of the liquid outlet 9 to ensure the normal supply of propellant and prevent the backflow of the lower tank propellant to the upper tank;

[0044] As Figure 3 shown, specifically, the screen window 32 is composed of a cover 321, a screen window pressing plate 322, a screen 323, a screen window support plate 324 and a screen window frame 325, and is used for exhausting gas during the filling of the lower tank of the storage tank to prevent the lower tank propellant from flowing back to the upper tank through the screen window;

[0045] The screen window support plate 324 and the screen window pressing plate 322 are both metal plates with circular windows, and the thickness is 1 mm to 2 mm; the screen 323 is a 200×1400 metal diagonal screen; the cover 321 is a hollow cylindrical metal structure with circular holes on the surface; the components of the screen window 32 are connected by welding process. First, the screen window support plate 324, the screen window pressing plate 322 and the screen 323 are welded, then welded to the screen window frame 325, and finally welded to the cover 321;

[0046] As Figure 1As shown, the accumulator 4 is arranged in the lower compartment 2 and is a hollow metal structure, including a top cover 42, an exhaust pipe assembly 41 and a conical section assembly 43, and is used to provide the propellant required by the engine during the reentry reverse thrust deceleration section and the landing front reverse thrust deceleration section from startup to when the propellant completely sinks to the bottom;

[0047] As Figure 5 shown, the exhaust pipe assembly 41 includes an exhaust pipe assembly skeleton 411, an exhaust pipe assembly support plate 412, an exhaust pipe assembly screen 413 and an exhaust pipe assembly pressing plate 414; and the lower end of the exhaust assembly skeleton 411 is welded to the top cover 42; each component of the exhaust pipe assembly 41 is connected by a welding process. First, the exhaust pipe assembly support plate 412, the exhaust pipe assembly screen 413 and the exhaust pipe assembly pressing plate 414 are welded, and then they are welded to the upper end opening of the exhaust pipe assembly skeleton 411; the exhaust pipe assembly skeleton is a hollow structure with a cylindrical window, the exhaust pipe assembly support plate and the exhaust pipe assembly pressing plate are metal plates with circular windows, with a thickness of 1 mm to 2 mm, and the exhaust assembly screen is a 200×1400 metal twill screen;

[0048] As Figure 4 shown, the conical section assembly 43 includes a conical section skeleton 431, a conical section support plate 432, a conical section pressing plate 434 and a conical section screen 433; each component of the conical section assembly 43 is connected by a welding process. First, the conical section support plate 432, the conical section screen 433 and the conical section pressing plate 434 are welded, and then they are welded to the conical section skeleton 431; the conical section skeleton 431 is a frustum-shaped annular metal plate, and the metal plate is provided with fan-shaped windows along the radial direction; the conical section support plate 431 and the conical section pressing plate 434 are metal plates with square windows, with a thickness of 1 mm to 2 mm, and the four corners of the square windows are provided with rounded corners, R1 to R2; the conical section screen 433 is a 325×2300 metal twill screen.

[0049] As Figure 1 shown, the anti-vortex and anti-collapse device 5 prevents the formation of vortices and collapses near the liquid outlet 9, reduces the mass of unusable propellant, and improves the propellant utilization rate;

[0050] As Figure 1 shown, the anti-slosh plate 6 adopts a non-uniform distribution strategy: in the middle region of the storage tank, the propellant sloshing is relatively intense, so the distribution density of the anti-slosh plate is relatively large; while in the regions near the top and bottom of the storage tank, the propellant sloshing is relatively small, and the distribution density of the anti-slosh plate is correspondingly reduced.

[0051] Embodiment 2

[0052] Please refer to Figures 1 - 5, the difference between this embodiment and Embodiment 1 is that: in this embodiment, the exhaust pipe assembly 41 of the accumulator 4 can improve the filling rate of the external propellant of the accumulator into the interior by adjusting the opening areas of the exhaust pipe support plate 412 and the exhaust pipe pressing plate 414 and the height of the exhaust pipe skeleton 411, ensuring that the accumulator 4 is always filled with liquid propellant to meet the liquid supply requirements of the engine.

[0053] When using cryogenic propellants, a polyurethane foam insulation layer is pasted on the outside of the tank.

[0054] The working principle and usage process of the present invention:

[0055] Tank filling: The one-way valve 33 on the partition assembly 3 is closed to prevent the propellant in the lower compartment from flowing upward into the upper compartment 1. After the propellant enters the lower compartment 2 from the filling port 10, the gas in the lower compartment 2 is discharged into the upper compartment 1 through the screen window 32. When the lower compartment 2 is full, the overflow valve 12 at the exhaust port 8 is used to exhaust gas to maintain the stability of the tank pressure;

[0056] Ascent stage: The tank maintains pressurization. Under the combined action of the liquid column pressure and the pressurization pressure, the one-way valve 33 on the partition assembly 3 opens to consume the propellant in the upper compartment 1, and the lower compartment 2 remains full to ensure a stable supply of propellant during the ascent process;

[0057] First-stage and second-stage separation, rocket first-stage attitude adjustment stage, and aerodynamic deceleration stage: The one-way valve 33 is closed to prevent the propellant in the lower compartment 2 from flowing back into the upper compartment 1. The screen 323 of the screen window 32 is wetted by the propellant, which can prevent the gas in the upper compartment from entering the lower compartment, ensure that the lower compartment remains full, and prevent the propellant in the lower compartment from sloshing, preparing for the second startup of the engine.

[0058] Reentry stage reverse thrust deceleration, pre-landing reverse thrust deceleration stage: The accumulator 4 provides the propellant required by the engine during the period from startup to when the propellant completely sinks to the bottom. During the sinking process of the propellant, the propellant in the lower compartment 2 continuously fills into the accumulator 4 to meet the liquid supply requirements of the engine and achieve the vertical recovery of the rocket.

[0059] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, and improvements made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims

1. A propellant tank for a vertical recovery launch vehicle, characterized in that: Comprising: An upper cabin, a lower cabin, a partition assembly, a accumulator, an anti-slosh plate, an anti-whirl and anti-collapse device, a pressurization port, an exhaust port, a liquid outlet, and a filling port; wherein, the partition assembly divides the storage tank into an upper cabin and a lower cabin, and an accumulator is arranged in the lower cabin; a pressurization port and an exhaust port are arranged at the top of the upper cabin, a gas damper is installed on the pressurization port, and a safety overflow valve is installed on the exhaust port; a liquid outlet and a filling port are arranged at the bottom of the lower cabin, and an anti-whirl and anti-collapse device is arranged at the liquid outlet.

2. The propellant tank of the vertical recovery launch vehicle according to claim 1, wherein: The volume of the lower cabin is less than that of the upper cabin, and is not less than 1.2 to 1.5 times the propulsion dosage used by the engines in the reentry reverse thrust deceleration section and the pre-landing reverse thrust deceleration section.

3. The vertical recovery launch vehicle propellant tank according to claim 1, wherein: The partition assembly includes a partition, a check valve, and a screen window; wherein, the partition is a concave ellipsoidal shell, and screen windows are uniformly arranged in the outermost circle, and check valves are uniformly arranged in the remaining windows.

4. The vertical recovery launch vehicle propellant tank according to claim 1 or 3, characterized in that: The screen window includes a cover, a screen window pressing plate, a screen, a screen window support plate, and a screen window skeleton, and the cover, the screen window pressing plate, the screen, the screen window support plate, and the screen window skeleton are stacked and fixed together from top to bottom; wherein, the screen window support plate and the screen window pressing plate are metal plates with circular windows, and the thickness is 1 mm to 2 mm; the screen is a 200×1400 metal inclined screen; the cover is a hollow cylindrical metal structure with round holes on the surface.

5. The vertical recovery launch vehicle propellant tank according to claim 1 or 3, characterized in that: The check valve adopts a butterfly type or wafer type check valve, and the total flow area is not less than 1.5 to 2.0 times the flow area of the liquid outlet.

6. The vertical recovery launch vehicle propellant tank according to claim 1, characterized in that: The accumulator is a hollow metal structure, including a top cover, an exhaust pipe assembly, and a conical section assembly.

7. The vertical recovery launch vehicle propellant tank according to claim 6, wherein: The exhaust pipe assembly includes an exhaust pipe assembly skeleton, an exhaust pipe assembly support plate, an exhaust pipe assembly screen, and an exhaust pipe assembly pressing plate; and the lower end of the exhaust assembly skeleton is fixed to the top cover; the exhaust assembly support plate, the exhaust assembly screen, and the exhaust assembly pressing plate are stacked and fixed together from bottom to top; and the exhaust assembly support plate, the exhaust assembly screen, and the exhaust assembly pressing plate are fixed to the upper end opening of the exhaust assembly skeleton to close the upper end opening of the exhaust assembly skeleton; wherein, the exhaust pipe assembly skeleton is a hollow structure with a cylindrical window, the exhaust pipe assembly support plate and the exhaust pipe assembly pressing plate are metal plates with circular windows, and the thickness is 1 mm to 2 mm, and the exhaust assembly screen is a 200×1400 metal inclined screen.

8. The vertical-recovery launch vehicle propellant tank according to claim 6, wherein: The conical section assembly includes a conical section skeleton, a conical section support plate, a conical section pressing plate, and a conical section screen, and the conical section skeleton, the conical section support plate, the conical section screen, and the conical section pressing plate are stacked and fixed together from inside to outside; wherein, the conical section skeleton is a frustum-shaped annular metal plate, and fan-shaped windows are arranged along the radial direction of the metal plate; the conical section support plate and the conical section pressing plate are metal plates with square windows, and the thickness is 1 mm to 2 mm, and fillets with R1 to R2 are arranged at the four corners of the square windows; the conical section screen is a 325×2300 metal inclined screen.

9. The vertical recovery launch vehicle propellant tank according to claim 1, wherein: The anti-slosh plates are unevenly distributed on the upper cabin and the lower cabin along the axis of the storage tank.

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