A rocket propellant filling system

Abstract

The utility model provides a rocket propellant filling system, include: storage tank for storing rocket propellant, filling pump, through first pipeline connection in storage tank for through pressurization extrude propellant in storage tank, supercooler, through second pipeline connection in filling pump for cooling propellant, cold source medium storage tank, through sixth pipeline connection in supercooler for providing cold source medium to supercooler, the propellant after cooling enters rocket storage tank through third pipeline. This filling system simple structure can improve the reliability of rocket propellant filling process.

Description

Technical Field

[0001] This utility model relates to the field of aerospace launch vehicle refueling, specifically to a rocket propellant refueling system. Background Technology

[0002] In recent years, my country's aerospace industry has made great achievements. Cryogenic propellants (such as liquid oxygen / methane and liquid oxygen / liquid hydrogen) have advantages such as being non-toxic, non-polluting, low-cost, high specific impulse, and high thrust as propellants for launch vehicles, making them the best propellant choice for large launch vehicles.

[0003] Currently, cryogenic liquid propellants are supplied using a combination of vacuum-insulated tanks and self-pressurized delivery to meet the refueling requirements of large launch vehicles. However, this approach has significant limitations: First, the launch site storage area requires the construction of large-scale tank areas, pressurizers, and complex pipelines, valves, and control systems, resulting in high infrastructure construction costs. Second, the large number of equipment pipelines and complex instruments and control systems not only lead to low space utilization but also significantly increase the difficulty of system integration and debugging.

[0004] Therefore, there is an urgent need to design a rocket propellant loading system that is simple in structure, low in cost, and capable of rapid response. Utility Model Content

[0005] The purpose of this invention is to overcome the shortcomings of the existing technology and provide a rocket propellant loading system.

[0006] This utility model provides a rocket propellant refueling system, comprising: a storage tank for storing rocket propellant; a refueling pump connected to the storage tank via a first pipe for pressurizing and extruding the propellant from the storage tank; a supercooler connected to the refueling pump via a second pipe for cooling the propellant; a cold source medium tank connected to the supercooler via a sixth pipe for supplying a cold source medium to the supercooler; and the cooled propellant entering the rocket propellant tank via a third pipe.

[0007] According to one embodiment of the present invention, the rocket propellant loading system further includes: a first valve disposed on the first pipe; a second valve disposed on the third pipe; and a sixth valve disposed on the sixth pipe.

[0008] According to one embodiment of the present invention, the rocket propellant refueling system further includes: a vaporizer, which is connected in parallel to the storage tank via a fourth pipe to maintain the pressure stability of the storage tank; and a third valve, which is provided on the fourth pipe.

[0009] According to one embodiment of the present invention, the rocket propellant refueling system further includes: a return pipe disposed between the refueling pump outlet pipe and the storage tank; and a fourth valve disposed on the return pipe.

[0010] According to one embodiment of the present invention, the rocket propellant loading system further includes: a collection tank connected to the third pipe via a fifth pipe for collecting propellant; and a fifth valve disposed on the fifth pipe.

[0011] According to one embodiment of the present invention, the rocket propellant loading system further includes: a first discharge tower disposed on the supercooler; and a second discharge tower disposed on the collection tank.

[0012] According to one embodiment of the present invention, the rocket propellant loading system further includes a temperature sensor and a pressure sensor, both of which are disposed on the storage tank, the first pipe, the second pipe, the third pipe, the fifth pipe, and the sixth pipe.

[0013] According to one embodiment of the present invention, the rocket propellant loading system further includes: a first regulating valve disposed on the third pipe; a second regulating valve disposed on the fifth pipe; and a third regulating valve disposed on the sixth pipe.

[0014] According to one embodiment of the present invention, the rocket propellant loading system further includes: a first flow meter disposed on the second pipe; and a second flow meter disposed on the sixth pipe.

[0015] According to one embodiment of the present invention, the outlet of the storage tank is provided with an anti-vortex device.

[0016] In this embodiment, the propellant supplied by the storage tank is pressurized and delivered into the supercooler by the refueling pump. The propellant is cooled by the cold source medium in the supercooler, and the cooled propellant is then sent into the rocket propellant tank. This refueling method, combining the storage tank and the refueling pump, offers high space utilization, optimized processes, a simple system, fewer risk points, and improves the reliability of the rocket propellant refueling process.

[0017] It should be understood that the above general description and the following specific embodiments are merely exemplary and illustrative, and do not limit the scope of the present invention. Attached Figure Description

[0018] The accompanying drawings are part of the specification of this utility model and illustrate exemplary embodiments of the utility model. The drawings, together with the description in the specification, are used to illustrate the principles of the utility model.

[0019] Figure 1This is a schematic diagram of a rocket propellant loading system according to an embodiment of the present invention;

[0020] Figure 2 This is a schematic diagram of a rocket propellant loading system according to another embodiment of the present invention. Attached image description:

[0022] 101-Storage tank, 102-Injection pump, 103-Subcooler, 104-Cold source medium storage tank, 105-Vaporizer, 106-Collection tank, 201-First pipeline, 202-Second pipeline, 203-Third pipeline, 204-Fourth pipeline, 205-Fifth pipeline, 206-Sixth pipeline, 207-Return pipeline, 301-First valve, 302-Second valve, 303-Third valve, 304-Fourth valve, 305-Fifth valve, 306-Sixth valve, 401-First discharge tower, 402-Second discharge tower, 501-First regulating valve, 502-Second regulating valve, 601-First flow meter, 602-Second flow meter. Detailed Implementation

[0023] The features and exemplary embodiments of various aspects of this utility model will be described in detail below. To make the objectives, technical solutions, and advantages of this utility model clearer, the following detailed description is provided in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain this utility model and to exemplarily illustrate the principles of this utility model, and are not configured to limit this utility model. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of this utility model.

[0024] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of this utility model. In the description of this utility model, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0025] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0026] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., and should not be considered limiting. Similar terms are used throughout the description to refer to similar elements.

[0027] For those skilled in the art, this invention can be implemented without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples.

[0028] Figure 1 This is a schematic diagram of a rocket propellant loading system according to an embodiment of the present invention; Figure 2 This is a schematic diagram of a rocket propellant loading system according to another embodiment of the present invention.

[0029] like Figure 1 As shown, this utility model provides a rocket propellant refueling system, including: a storage tank 101 for storing rocket propellant; a refueling pump 102 connected to the storage tank 101 via a first pipe 201 for pressurizing and extruding the propellant from the storage tank 101; a supercooler 103 connected to the refueling pump 102 via a second pipe 202 for cooling the propellant; a cold source medium storage tank 104 connected to the supercooler 103 via a sixth pipe 206 for providing a cold source medium to the supercooler 103; and the cooled propellant entering the rocket propellant tank Z via a third pipe 203.

[0030] Specifically, the storage tank 101 can adopt a double-layer structure, consisting of an inner tank, an outer tank, a bottom insulation layer, a perlite insulation layer in between, steel structure accessories, and a piping system. The inner tank is designed for normal pressure, the interlayer is filled with perlite insulation material, and a slight positive pressure protection (approximately 0.5–0.8 kPa) is maintained to prevent instability of the outer tank.

[0031] The refueling pump 102 is a cryogenic variable frequency pump that uses impeller rotation to propel propellant from the inlet of the pump 102 at high speed towards the impeller edge. During this process, the flow rate and pressure of the propellant in the pipeline are significantly increased. By adjusting the motor frequency in the variable frequency pump, the impeller speed can be adjusted to achieve flow rate and pressure regulation, meeting the dynamic requirements of propellant refueling parameters at different refueling stages.

[0032] For example, the subcooler 103 includes a tube side and a shell side. The tube side is made of a high-strength material with high thermal conductivity, commonly stainless steel or aluminum. The shell side is also made of a high-strength material, with an outer layer of insulation material to effectively prevent the loss of cold from the cold source medium. The tube side of the subcooler 103 is connected to the propellant loading pipeline, and the shell side is connected to the cold source medium pipeline. The cold source medium is located outside the propellant loading pipeline, reducing the propellant temperature to below the standard boiling point, resulting in a denser propellant.

[0033] In this embodiment, the propellant provided by the storage tank 101 is pressurized and delivered into the supercooler 103 by the refueling pump 102. The propellant is cooled by the cold source medium in the supercooler 103, and the cooled propellant enters the rocket propellant tank Z. Compared with the existing technology that uses multiple pressure tanks for compression refueling, the combined refueling method of the storage tank 101 and the refueling pump 102 offers higher space utilization, optimized process, simpler system, fewer risk points, and improved reliability of the rocket propellant refueling process. Using the refueling pump 102 as the system pressurization device enables rapid pressure and frequency response, significantly improving the system pressurization capacity. Furthermore, the system refueling flow rate and temperature can be controlled by adjusting the frequency and regulating valve opening, meeting the dynamic requirements of refueling parameters at different stages, optimizing propellant refueling time, and improving the controllability of the rocket refueling process.

[0034] like Figure 2 As shown, according to one embodiment of the present invention, the rocket propellant loading system further includes: a first valve 301 disposed on the first pipe 201; a second valve 302 disposed on the third pipe 203; and a sixth valve 306 disposed on the sixth pipe 206.

[0035] According to one embodiment of the present invention, the rocket propellant refueling system further includes: a vaporizer 105, which is connected in parallel to the storage tank 101 via a fourth pipe 204 to maintain the pressure stability of the storage tank 101; and a third valve 303, which is connected to the fourth pipe 204.

[0036] According to one embodiment of the present invention, the rocket propellant refueling system further includes: a return pipe 207, which is disposed between the liquid outlet pipe of the refueling pump 102 and the storage tank 101; and a fourth valve 304, which is disposed on the return pipe 207.

[0037] According to one embodiment of the present invention, the rocket propellant loading system further includes: a collection tank 106, which is connected to the third pipe 203 via a fifth pipe 205 for collecting propellant; and a fifth valve 305, which is disposed on the fifth pipe 205.

[0038] According to one embodiment of the present invention, the rocket propellant loading system further includes: a first discharge tower 401 disposed on the supercooler 103; and a second discharge tower 402 disposed on the collection tank 106.

[0039] According to one embodiment of the present invention, the rocket propellant loading system further includes a temperature sensor and a pressure sensor, both of which are installed on the storage tank 101, the first pipe 201, the second pipe 202, the third pipe 203, the fifth pipe 205 and the sixth pipe 206.

[0040] According to one embodiment of the present invention, the rocket propellant loading system further includes: a first regulating valve 501 disposed on the third pipe 203; a second regulating valve 502 disposed on the fifth pipe 205; and a third regulating valve 503 disposed on the sixth pipe 206.

[0041] According to one embodiment of the present invention, the rocket propellant loading system further includes: a first flow meter 601, which is disposed on the second pipe 202; and a second flow meter 602, which is disposed on the sixth pipe 206.

[0042] According to one embodiment of the present invention, the outlet of the storage tank 101 is provided with an anti-vortex device.

[0043] Specifically, based on the multi-stage refueling requirements of the rocket, the storage tank 101 can be equipped with multiple liquid outlets. To prevent the formation of vortices within the storage tank 101 during the high-flow-rate refueling process, anti-vortex plate devices are installed at the liquid outlets within the storage tank 101 to ensure the safe and stable operation of the storage tank 101. The anti-vortex device can employ a star-shaped or other multi-cross plate support, with circular or spherical cover plates installed on the support. The propellant flow within the storage tank 101 passes through multiple channels between the cover plates and the support plates to reach the liquid outlets. This device effectively suppresses vortex phenomena that may form during propellant discharge, not only eliminating the risk of propellant entrainment but also ensuring the continuous, stable, and efficient discharge of propellant.

[0044] Furthermore, the return pipe 207 enables rapid precooling of the fueling pump 102 and allows for rapid restart of the fueling pump 102 in case of an emergency shutdown. If an emergency shutdown occurs during the startup of the fueling pump 102, and the pressure in the third pipe 203 exceeds that in the second pipe 202, preventing the fueling pump 102 from starting smoothly, the fourth valve 304 on the return pipe 207 can be opened. The hydrostatic pressure of the liquid column propels the propellant to circulate within the fueling pump 102, achieving continuous precooling during the shutdown process. The return pipe 207 prevents the fueling pump 102 from overheating due to the cessation of propellant flow after shutdown. Once the fueling pump 102 reaches the precooled temperature, it can be restarted pneumatically, and the fourth valve 304 on the return pipe 207 is adjusted to a small opening. As the frequency of the filling pump 102 gradually increases, when the pressure in the second pipeline 202 exceeds that in the third pipeline 203, the second valve 302 on the third pipeline 203 is gradually opened, and the fourth valve 304 of the return pipeline 207 is simultaneously closed, restarting the filling process. The inclusion of the return pipeline 207 significantly improves the system's fault tolerance, enhances the efficiency of system fault handling, and ensures the safety and stability of the filling system.

[0045] The cryogenic propellant output from storage tank 101 is vaporized by the self-pressurizing vaporizer 105 on the fourth pipe 204, and then the gaseous propellant is returned to the gas phase space of storage tank 101, forming a closed-loop pressure maintenance system. A third valve 303 is installed on the fourth pipe 204, which can be automatically interlocked with the pressure of storage tank 101 via an automatic control system. When the pressure of storage tank 101 falls below a preset safety threshold, the third valve 303 automatically opens, pressurizing storage tank 101 through the vaporizer 105. Once the pressure of storage tank 101 returns to the safe pressure, the third valve 303 closes, ensuring that the pressure of storage tank 101 remains stable within the safe pressure range. This scheme significantly reduces equipment risk and ensures the stable operation of the entire refueling system.

[0046] In one embodiment, the reflux pipe 207 is a branch pipe on the outlet pipe of the refueling pump 102, connected to the gas phase space of the storage tank 101. The reflux pipe 207 serves to rapidly pre-cool the refueling pump 102, reduce the risk of cavitation, and regulate the flow rate and pressure after the pump. A fourth valve 304 is installed on the reflux pipe to control the propellant flow rate of the refueling pump 102 within the reflux pipe. During the low-frequency operation phase of the refueling pump 102, the fourth valve 304 on the reflux pipe can be opened slightly to release trapped air in the pipe, thus avoiding the risk of cavitation in the refueling pump 102.

[0047] The collection tank 106 is a unit that collects and processes the cooled propellant after it has been supercooled by the cold source medium. The cooled propellant is discharged through the second discharge tower 402 connected to the collection tank 106. Before entering the rocket propellant tank Z, the cooled propellant can be discharged through the discharge system consisting of the collection tank 106 and the second discharge tower 402, primarily used during the pre-cooling stage of the propellant in the refueling pipeline. The fifth pipeline 205 is equipped with temperature and pressure sensors to monitor the temperature and pressure of the propellant medium within the pipeline.

[0048] For example, the first discharge tower 401 connected to the supercooler 103 can discharge the cold source medium, such as liquid nitrogen, which is used as the cold source medium to exchange heat with the propellant through the supercooler 103 and is then discharged through the first discharge tower 401.

[0049] In some optional embodiments, switchable bypass circuits are connected in parallel at both ends of the refueling pump 102 and the supercooler 103, allowing the propellant in the rocket tank Z to be drained back without flowing through the refueling pump 102 and the supercooler 103, thus reducing the flow resistance during propellant draining. A shut-off valve can be installed on the bypass circuit to control the switching of propellant between the bypass line and the refueling line.

[0050] This solution simplifies the structure of the cryogenic propellant refueling system and deeply optimizes the refueling process through the integrated design of the atmospheric pressure storage tank 101 and the high-efficiency refueling pump 102. Compared with the existing technology of storing propellant in multiple vacuum insulated tanks, the refueling system proposed in this invention can greatly reduce the space occupancy rate, optimize the refueling process to shorten the refueling time, reduce the system construction and operation and maintenance costs, and reduce the need for manual operation, providing reliable support for unattended refueling and high-frequency flight launch requirements.

[0051] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A rocket propellant loading system, characterized in that, include: Storage tanks are used to store rocket propellants; A fueling pump, connected to the storage tank via a first pipe, is used to expel propellant from the storage tank by pressurization; A subcooler, connected via a second pipe, is used to cool the propellant from the fueling pump; A cold source medium storage tank is connected to the subcooler via a sixth pipe to supply cold source medium to the subcooler; The cooled propellant enters the rocket's propellant tank through a third pipe.

2. The rocket propellant loading system according to claim 1, characterized in that, Also includes: The first valve is installed on the first pipeline; The second valve is installed on the third pipe; The sixth valve is installed on the sixth pipeline.

3. The rocket propellant loading system according to claim 2, characterized in that, Also includes: A vaporizer is connected in parallel to the storage tank via a fourth pipe to maintain the pressure stability of the storage tank; The third valve is installed on the fourth pipe.

4. The rocket propellant loading system according to claim 3, characterized in that, Also includes: A return pipe is installed between the liquid outlet pipe of the filling pump and the storage tank; The fourth valve is located on the return pipe.

5. The rocket propellant loading system according to claim 4, characterized in that, Also includes: A collection tank, connected to the third pipe via a fifth pipe, is used for propellant collection; The fifth valve is installed on the fifth pipeline.

6. The rocket propellant loading system according to claim 5, characterized in that, Also includes: The first discharge tower is installed on the subcooler; The second discharge tower is installed on the collection tank.

7. The rocket propellant loading system according to claim 5, characterized in that, Also includes: Temperature and pressure sensors are both installed on the storage tank, the first pipe, the second pipe, the third pipe, the fifth pipe, and the sixth pipe.

8. The rocket propellant loading system according to claim 5, characterized in that, Also includes: A first regulating valve is installed on the third pipeline; A second regulating valve is installed on the fifth pipe; The third regulating valve is installed on the sixth pipe.

9. The rocket propellant loading system according to claim 5, characterized in that, Also includes: The first flow meter is installed on the second pipe; The second flow meter is installed on the sixth pipe.

10. The rocket propellant loading system according to any one of claims 1-9, characterized in that, The storage tank is equipped with an anti-vortex device at its outlet.

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