Management device for rocket propellant supply control
Through the combination of lightweight partitions and communication pipes, the problem of storage tank pressure reduction caused by mixing low-temperature propellant and supercharged gas during the launch vehicle return process is solved, and simple and reliable propellant management is achieved to meet the engine's reignition needs.
Patent Information
- Application Number
- CN202521393868.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-07-04
- Publication Date
- 2025-08-08
- Estimated Expiration
- 2035-07-04
AI Technical Summary
In the prior art, the reused launch vehicle is violently blended with the pressurized gas during the return process, resulting in a reduced storage tank pressure. The existing management plan is complex and heavy, making it difficult to meet the demand for reignition.
The lightweight partition is used to combine with the connecting pipe management device. The propellant storage box is divided into two parts through the partition, and an anti-reflux device is installed on the connecting pipe to limit the low-temperature propellant at the bottom of the storage box to avoid mixing.
It effectively avoids the reduction of the tank pressure, simplifies the system structure, reduces the system complexity and weight, and ensures that the propellant always gathers at the bottom of the tank during the return process, meeting the needs of the engine to reignite.
Smart Images
Figure CN223203143U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the field of rocket propellant supply control, in particular to a management device for rocket propellant supply control. Background Art
[0002] Rocket propellant is usually stored in some form in large quantities in propellant tanks and ejected in large quantities from rocket engines in the form of fluid jets to generate thrust. Propellant supply control is particularly important for reusable rockets.
[0003] Currently, there are four main methods for controlling the supply of propellant in the prior art, each of which has corresponding shortcomings / deficiencies:
[0004] 1. Gas-liquid separation management: This method primarily uses a rubber bladder or other device (such as a metal diaphragm) to separate the propellant from the air cushion. High-pressure gas squeezes the diaphragm to deliver the propellant to the engine combustion chamber. This method is commonly used for conventional propellant management in satellite tanks and other highly maneuverable, short-duration spacecraft. However, for large cryogenic tanks, the device used in this management method is large in size and mass, and there are issues with compatibility between the diaphragm and the cryogenic propellant, as well as fatigue.
[0005] 2. Forward-thrust bottoming: This method utilizes a bottom-thrusting engine to provide thrust, ensuring the propellant remains stable at the bottom of the tank. This prevents the cryogenic propellant from mixing violently with the pressurized gas, which would cause a pressure drop and a temperature rise in the cryogenic propellant, thereby reducing propellant quality. This method is commonly used in the final stages of large launch vehicles and is a relatively mature propellant management method. During the return of a launch vehicle sub-stage, a forward-thrust bottoming propulsion system is required, generating bottoming thrust by consuming propellant or gas from high-pressure cylinders.
[0006] 3. Retention Net Solution: This solution uses a propellant management device to retain and collect propellant using surface tension. It utilizes the surface tension of the liquid in microgravity and the retention properties of the fine mesh to retain the liquid propellant at the bottom of the tank. This solution has limited application scenarios and is primarily used in an on-orbit microgravity environment.
[0007] 4. Independent tank solution: By setting up independent and separate propellant tanks, the ascent phase propellant and the return propellant of the carrier rocket are stored independently. The system is complex. In addition to setting up independent tanks, it also requires additional supporting equipment such as pressurized delivery pipelines and valves, which is heavy and expensive. Utility Model Content
[0008] The purpose of the present utility model is to at least partially solve the above-mentioned technical problems and to provide a new management device for rocket propellant supply control.
[0009] The management device for rocket propellant supply control of the present utility model is used to solve one or at least part of the following technical problems:
[0010] It meets the demand for control and management of tens of tons of propellant supply, and is used for the re-ignition of spacecraft such as launch vehicles; in the face of complex interferences such as negative overload and large-scale attitude adjustment during the return process of reusable launch vehicles and other spacecraft, it limits the large-scale free flow of cryogenic propellant during the return process and keeps the propellant always gathered at the bottom of the propellant tank; overcomes the violent mixing of cryogenic propellant and pressurized gas during the return process of the first stage of the launch vehicle, and reduces the tank pressure; abandons propellant management schemes such as forward thrust sinking and independent tanks, simplifies existing cryogenic propellant management schemes, and reduces system complexity and structural heaviness.
[0011] Generally speaking, the inventive concept of the present utility model is to innovatively propose a management device, such as a cryogenic propellant supply control, in the form of a lightweight partition combined with a connecting pipe, which is used for the effective management of tens of tons of cryogenic propellant during the return process of reusable launch vehicles and other spacecraft, and to always keep the cryogenic propellant at the bottom of the tank in a simple, reliable, efficient and economical manner to meet the requirements of engine re-ignition.
[0012] In one aspect of the present invention, a management device for rocket propellant supply control is provided, the management device comprising a partition for dividing a propellant tank into two parts, the management device further comprising:
[0013] A plurality of straight-through communication pipes arranged at intervals on the partition plate;
[0014] A backflow prevention device is provided on the end of each straight-through communicating pipe away from the partition plate.
[0015] In some embodiments, the partition is provided with a reinforcing plate and / or reinforcing ribs.
[0016] In some embodiments, the backflow prevention device is a backflow prevention bowl fixed to the straight-through connecting pipe by welding a rod system.
[0017] In some embodiments, the partition is disposed at a height that is 1.5-2 times the height of the liquid level of the remaining propellant in the propellant tank.
[0018] In some embodiments, a circle of T-shaped frames for mounting the bulkheads is welded in sections in the propellant tank.
[0019] In some embodiments, the partition is fixedly connected to a circle of T-shaped frames by bolts, and the distance between two adjacent bolts does not exceed 100 mm.
[0020] In some embodiments, the circle of T-shaped frames includes multiple segments, and fluoroplastic sealing rings are provided in the gaps between adjacent segments.
[0021] In some embodiments, a plurality of through girders for enhancing the bearing capacity of the partition are provided on the circle of T-shaped frames.
[0022] In some embodiments, the plurality of through-beams are screwed to a circle of T-shaped frames via joints.
[0023] In some embodiments, the total flow area of the straight-through connecting pipe is greater than or equal to twice the cross-sectional area of the total propellant delivery pipe;
[0024] The plurality of through girders are three through girders.
[0025] In some embodiments, the anti-backflow bowl is a hemispherical shell with a radius of 400-500 mm (eg, 455 mm) and a wall thickness of 1-3 mm, preferably 2 mm.
[0026] In some embodiments, the depth of the lower end of the straight-through connecting pipe entering the anti-backflow bowl is 50 mm-100 mm.
[0027] A management device for rocket propellant supply control according to an embodiment of the present invention has at least one or at least some of the following advantages:
[0028] (1) It effectively avoids the drop in tank pressure caused by the violent mixing of cryogenic propellant and the main pressurized gas in the propellant tank, thus saving the configuration demand for booster gas cylinders;
[0029] (2) Since the partition largely restricts the free flow of cryogenic propellant and is always located near the bottom of the tank, the propellant sinking requirement can be met by relying solely on the overload generated by the aerodynamic drag during the return process, eliminating the need for a forward thrust engine system.
[0030] (3) The cryogenic propellant management device in the form of a lightweight baffle and a connecting pipe is a simple structure with no moving parts, no special materials and processes. The device is simple, reliable and low-cost. BRIEF DESCRIPTION OF THE DRAWINGS
[0031] These and / or other aspects and advantages of the present invention will become apparent and readily understood from the following description of preferred embodiments in conjunction with the accompanying drawings, in which:
[0032] Figure 1 1 is a schematic diagram of the overall structure of a management device for rocket propellant supply control according to an embodiment of the present utility model;
[0033] Figure 2 yes Figure 1A perspective view of the management device for rocket propellant supply control is shown;
[0034] Figure 3 is with Figure 2 A schematic diagram showing a circle of T-frames and crossbeams for the management system used to control the supply of rocket propellant. DETAILED DESCRIPTION
[0035] The following examples and accompanying drawings further illustrate the technical solution of the present invention. In the specification, the same or similar reference numerals indicate the same or similar components. The following description of the embodiments of the present invention with reference to the accompanying drawings is intended to explain the overall inventive concept of the present invention and should not be construed as limiting the present invention.
[0036] See also Figure 1 , showing a schematic diagram of the three-dimensional structure of a management device 100 for rocket propellant supply control according to one embodiment of the present invention. In some usage scenarios, such as after the separation of the primary and secondary stages of a reusable launch vehicle, the primary stage will experience negative overload from the separation force and the engine plume after the secondary stage is activated. During the return process, a large 180° turn and attitude adjustment will be required. If cryogenic propellant management measures are not implemented, there is a risk of abnormally low pressure drop in the propellant tank 200, and propellant air inclusion will affect engine ignition.
[0037] To meet the cryogenic propellant management requirements for reusable launch vehicles and other spacecraft during re-entry, a simple, reliable, and efficient distributed, straight-through connecting pipe cryogenic propellant management device 100, utilizing a combination of baffles and connecting pipes, is proposed. This device effectively manages tens of tons of cryogenic propellant, preventing large amounts of cryogenic propellant from freely flowing and diffusing within the cryogenic propellant tank 200 during re-entry, thus minimizing the drop in tank pressure and the degradation of cryogenic propellant quality, such as temperature and gas content, thereby meeting the requirements for engine re-ignition.
[0038] The management device 100 adopts a distributed straight-through communication method with partitions and connecting pipes, which can effectively confine tens of tons of cryogenic propellant to the bottom area of the propellant tank 200, thereby realizing effective supply management of propellant during the return process.
[0039] Specifically, combined Figure 2The management device 100 includes a partition 10, a plurality of straight-through communication tubes 20, and a corresponding number of backflow prevention devices 30. Specifically, the management device 100 is disposed at the lower end of a propellant tank 200, and the partition 10 divides the propellant tank 200 into upper and lower sections. The straight-through communication tubes 20 on the partition 10 are spaced apart, for example, at a fixed interval. The intervals between the tubes 20 can also be adjusted as needed, meaning they do not necessarily need to be equally spaced.
[0040] It can be seen from this that the management device 100 of this embodiment adopts the form of a partition combined with a straight-through connecting pipe, which has the characteristics of simplicity, reliability, efficiency and economy.
[0041] As shown in the figure, the partition 10 is specifically installed in the lower section of the cylinder section of the cryogenic propellant tank 200. Typically, the installation height of the partition 10 in the propellant tank 200 is set at approximately 1.5 to 2 times the remaining propellant liquid level, based on the reserved amount of return cryogenic propellant. For example, if 25 tons of liquid oxygen are reserved and the liquid level is approximately 0.8 meters from the equatorial plane of the rear bottom of the propellant tank 200, the height of the partition 10 should be set at approximately 1.6 meters from the equatorial plane of the rear bottom of the propellant tank 200.
[0042] In some embodiments, the bulkhead 10 is provided with corresponding reinforcement plates, ribs, etc. according to the load requirements of the rocket. During the flight of the reusable rocket, the bulkhead 10 needs to withstand certain mechanical loads such as flight overload and propellant negative overload recoil pressure. The wall thickness of the bulkhead 10 is set to 1.5 mm, for example.
[0043] A backflow prevention device 30 is provided below each straight-through connecting pipe 20. The backflow prevention device 30 is provided in the form of an backflow prevention bowl, which is used to prevent a large amount of cryogenic propellant from flowing back from the straight-through connecting pipe 20 to the upper part of the propellant tank 200 during negative overload and large-scale attitude adjustment. The backflow prevention bowl and the straight-through connecting pipe 20 are fixed by a rod system (for example, welding) and are reliably connected.
[0044] See also Figure 3 , showing the Figure 2 A ring of T-shaped frames 40, used in conjunction with the management device 100, is located below the bulkhead 10. This ring of T-shaped frames 40 is welded in sections to corresponding locations within the barrel section of the propellant tank 200. In one embodiment, to reduce installation gaps and ensure ease of operation, the location where the bulkhead 10 is mounted within the barrel section of the cryogenic propellant tank 200 is welded in four sections to form a ring of T-shaped frames 40. The wall thickness of this ring of T-shaped frames 40 is 8 mm.
[0045] The bulkhead 10 is connected to the T-frame 40 by bolts. The maximum spacing between adjacent bolts is typically no more than 100 mm to enhance the connection reliability between the bulkhead 10 and the propellant tank 200 cylinder. Fluoroplastic gaskets are installed in the gaps between the segments of the T-frame 40 to prevent cryogenic propellant from flowing back into the upper portion of the propellant tank 200. These gaskets can also be secured by a pressure plate.
[0046] Furthermore, to ensure structural integrity and reliability, and to ensure effective propellant supply control and management, multiple spaced-apart through-stringers 50 are installed on the ring of T-frames 40. As shown in the figure, three through-stringers 50 are installed, each with a wall thickness of 6 mm, thereby enhancing the load-bearing capacity of the bulkhead 10. Each of the three through-stringers 50 is bolted to the ring of T-frames 40 via joints. The bulkhead 10, the ring of T-frames 40, and the through-stringers 50 can all be made of 7A09.
[0047] During the reusable launch vehicle's ascent phase, propellant above bulkhead 10 must flow smoothly through direct-through pipe 20 into the propellant tank 200 below bulkhead 10 and into the engine. To meet the engine's operating flow rate and reduce the flow resistance of propellant through the distributed direct-through pipe cryogenic propellant management system 100, the total flow area of the distributed direct-through pipe 20 is twice or more, preferably twice, the cross-sectional area of the total propellant delivery pipe.
[0048] In this example, the diagram shows three straight-through connecting tubes 20. Each straight-through connecting tube 20 has a diameter of 500 mm and a wall thickness of 1.5 mm. The backflow prevention bowl is a hemispherical shell with a radius of 400-500 mm (e.g., 455 mm) and a wall thickness of 1-3 mm, e.g., 2 mm. To effectively prevent cryogenic propellant from flowing back through the backflow prevention bowl and into the straight-through connecting tube 20, the depth of the lower end of the straight-through connecting tube 20 into the backflow prevention bowl is approximately 50-100 mm.
[0049] The management device 100 for rocket propellant supply control according to an embodiment of the present invention has at least one or at least some of the following advantages:
[0050] 1) Simulation analysis shows that the distributed, straight-through, cryogenic propellant management device 100 of this embodiment, when repeatedly used during the return of a launch vehicle's first stage, effectively prevents cryogenic propellant below the bulkhead 10 from flowing back to the upper portion of the bulkhead 10, keeping the total mass of propellant flowing out within a control range of 3‰. The tank pressure drop can also be controlled within 0.1 MPa. Compared to solutions without propellant management measures or with a retention net, this system can effectively manage tens of tons of cryogenic propellant, reducing the tank pressure drop by over 50%.
[0051] 2) The total weight of the distributed, straight-through, interconnecting cryogenic propellant management device 100 does not exceed 200 kg, significantly reducing weight compared to independent tank-based propellant management solutions.
[0052] 3) The distributed straight-through connecting tube type cryogenic propellant management device 100 has no moving parts. The internal connections between the device and the propellant tank 200 are all fixed connections, which are reliable to install. The main material is mature and applied lightweight aluminum alloy, which has low cost and high reliability. It can be used multiple times, is easy to detect, and has low maintenance cost.
[0053] Although some embodiments of the present general inventive concept have been shown and described, it will be appreciated by those skilled in the art that changes may be made to these embodiments without departing from the principles and spirit of the present general inventive concept, the scope of which is defined by the claims and their equivalents.
Claims
1. A management device for controlling the supply of rocket propellant, said management device comprising a partition for dividing a propellant tank into two parts, characterized in that: The management device further includes: A plurality of straight-through communication pipes arranged at intervals on the partition plate; A backflow prevention device is provided on the end of each straight-through communicating pipe away from the partition plate.
2. The management device according to claim 1, characterized in that The partition is provided with a reinforcing plate and / or reinforcing ribs.
3. The management device according to claim 1, characterized in that The anti-backflow device is an anti-backflow bowl fixed to the straight-through connecting pipe by welding a rod system; The depth of the lower end of the straight-through connecting pipe entering the anti-backflow bowl is 50mm-100mm; The anti-backflow bowl has a hemispherical shell with a radius of 400-500 mm and a wall thickness of 1-3 mm.
4. The management device according to claim 1, characterized in that The height position at which the partition is arranged in the propellant tank is 1.5-2 times the height of the liquid level of the remaining propellant in the propellant tank.
5. The management device according to any one of claims 1 to 4, characterized in that: A circle of T-shaped frames for mounting partitions is welded in sections in the propellant tank.
6. The management device according to claim 5, characterized in that: The partition is fixedly connected to a circle of T-shaped frames by bolts, and the distance between two adjacent bolts does not exceed 100 mm.
7. The management device according to claim 6, characterized in that The circle of T-shaped frames includes a plurality of segments, and fluoroplastic sealing rings are provided at the gaps between adjacent segments.
8. The management device according to claim 7, characterized in that: A plurality of through girders for enhancing the bearing capacity of the partitions are provided on the circle of T-shaped frames.
9. The management device according to claim 8, characterized in that The plurality of through girders are screwed to a circle of T-shaped frames through joints.
10. The management device according to claim 9, characterized in that: The total flow area of the straight-through connecting pipe is greater than or equal to twice the cross-sectional area of the total propellant delivery pipe; The plurality of through girders are three through girders.