CN218519861U - Rocket liquid propellant filling system - Google Patents
Rocket liquid propellant filling system Download PDFInfo
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- CN218519861U CN218519861U CN202222230537.XU CN202222230537U CN218519861U CN 218519861 U CN218519861 U CN 218519861U CN 202222230537 U CN202222230537 U CN 202222230537U CN 218519861 U CN218519861 U CN 218519861U
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- filling
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Abstract
The utility model provides a rocket liquid propellant filling system includes filling pipeline and filling connector on the frame of being connected with ground filling system at least to and exhaust pipeline and row's connector on the frame of being connected with ground exhaust-gas treatment system. One end of the filling connector is connected with the filling pipeline on the frame, and the other end of the filling connector is connected with the storage tank through the storage tank filling valve; one end of the exhaust connector is connected with the exhaust pipeline on the rack, and the other end of the exhaust connector is connected with the storage tank through a storage tank exhaust valve; the on-frame filling pipeline is connected with the on-frame exhaust pipeline through a filling pipeline, and the filling pipeline is provided with a filling stop valve; a ground filling valve is arranged on one side of the frame filling pipeline connected with the ground filling system; by regulating the ground filling valve, the filling connector, the storage tank filling valve, the storage tank exhaust valve, the exhaust connector and the filling stop valve, the storage tank can be filled with liquid propellant and replenished with liquid propellant.
Description
Technical Field
The utility model relates to a rocket launch technical field, concretely relates to rocket liquid propellant filling system.
Background
For liquid rockets, it is generally necessary to lay the propellant filling lines on the riser and to place the filling valves of the filling system on the ground, in order to avoid the weight of the valves and the connecting structure from adversely affecting the design and use of the riser. By the arrangement, if the storage tank needs to be refilled with the propellant, the storage tank can be refilled with the ground refilling system after the propellant refilling pipeline is refilled with the propellant in the storage tank. Because the temperature difference between the emptied filling pipeline and the propellant in the storage tank is large, potential safety hazards can be caused to a filling system.
Accordingly, it is desirable to provide a propellant filling system that can be used to fill an evacuated propellant filling line with a surface filling system.
SUMMERY OF THE UTILITY MODEL
To the above-mentioned technical problem among the correlation technique, the utility model provides a rocket liquid propellant filling system has realized the safe packing when the storage tank propellant filling is accomplished the back and need replenish the filling once more, thereby has avoided the evacuation filling pipeline to arouse the pressure shock that the violent exchange of temperature brought when carrying out the propellant filling, has improved propellant filling system's security.
The utility model provides a rocket liquid propellant filling system, which at least comprises an on-frame filling pipeline and a filling connector which are connected with a ground filling system, and an on-frame exhaust pipeline and an exhaust connector which are connected with a ground waste gas treatment system; one end of the filling connector is connected with the filling pipeline on the frame, and the other end of the filling connector is connected with the storage tank through the storage tank filling valve; one end of the exhaust connector is connected with the exhaust pipeline on the rack, and the other end of the exhaust connector is connected with the storage tank through a storage tank exhaust valve; the filling pipeline on the frame is connected with the exhaust pipeline on the frame through a filling pipeline, and the filling pipeline is provided with a filling stop valve; a ground filling valve is arranged on one side of the frame filling pipeline connected with the ground filling system;
by regulating the ground filling valve, the filling connector, the storage tank filling valve, the storage tank exhaust valve, the exhaust connector and the filling stop valve, the storage tank can be filled with liquid propellant and replenished with liquid propellant.
In one embodiment, the on-shelf refill line is further provided with a filter to filter out excess in the propellant.
In one embodiment, the filter is disposed downstream of the surface filling valve.
In one embodiment, a pressure sensor is further arranged between the ground filling valve and the filter; the pressure sensor is used for monitoring the pressure of the filling pipeline on the frame when the storage tank is filled in a supplementing mode, and the fact that the measuring pressure of the pressure sensor is higher than the opening pressure of the storage tank filling valve is avoided.
In one embodiment, the tank fill valve has an opening pressure of no greater than 0.4MPa.
In one embodiment, the filling line is further provided with a temperature sensor; the temperature sensor is used for monitoring the temperature of the propellant when the storage tank is replenished, and when the measured temperature is reduced to a preset temperature, the filling stop valve is closed after the storage tank filling valve is opened, and the refilling of the propellant is started.
In one embodiment, the tank fill valve is opened for 10 seconds and then the fill stop valve is closed when the measured temperature drops to a predetermined temperature.
In one embodiment, the tank fill valve is disposed at the bottom of the tank and the tank vent valve is disposed at the top of the tank.
In one embodiment, the filling connector is removably connected to the tank filling valve; the vent connector is removably connected to the tank vent valve.
In one embodiment, at least part of the on-shelf filling line and the on-shelf exhaust line are laid on the riser.
The embodiment of the utility model provides a pair of rocket liquid propellant filling system has replaced utilizing the storage tank to fill the means of propellant for the evacuation on the frame, when having avoided the evacuation filling pipeline to carry out propellant filling, thereby arouse the pressure shock that the violent exchange of temperature brought because of the difference in temperature is too big.
The utility model discloses a set up the filling pipeline between filling pipeline and the exhaust pipeline on putting up on the frame to set up the packing stop valve on filling pipeline. Therefore, after the storage tank finishes primary propellant filling and the on-shelf filling pipeline is emptied, when the storage tank needs to be refilled with propellant, the filling stop valve can be opened, so that the on-shelf filling pipeline, the filling pipeline and the on-shelf emptying pipeline form a passage. The gasified propellant can be discharged through the emptying pipeline on the shelf after the propellant is filled into the filling pipeline on the shelf, and the storage tank filling valve is opened to continuously replenish the propellant for the storage tank until the filling pipeline on the shelf is completely filled with the propellant.
Those skilled in the art will recognize additional features and advantages upon reading the detailed description, and upon viewing the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural view of a liquid propellant filling system according to an embodiment of the present invention.
Detailed Description
The technical solution of the present invention is further explained by the following embodiments with reference to the accompanying drawings. Spatially relative terms such as "under," "below," "…," "low," "above," "…," "high," and the like are used to facilitate description to explain the positioning of one element relative to a second element, indicating that these terms are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. In addition, terms such as "first", "second", and the like are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.
Referring to fig. 1, the present invention provides a rocket liquid propellant filling system, which at least comprises an on-frame filling pipeline 1 and a filling connector 2 connected with a ground filling system 100, and an on-frame exhaust pipeline 3 and an exhaust connector 4 connected with a ground exhaust gas treatment system 200. One end of the filling connector 2 is connected with the on-shelf filling pipeline 1, and the other end is connected with the storage tank 300 through the storage tank filling valve 5. Since the tank filling valve 5 is provided in the tank 300, the tank 300 can bear the weight of the filling connector 2 when the filling connector 2 is connected to the tank filling valve 5. The exhaust connector 4 has one end connected to the rack exhaust line 3 and the other end connected to the tank 300 through the tank exhaust valve 6. Since the tank vent valve 6 is provided in the tank 300, the weight of the exhaust connector 4 can be borne by the tank 300 after the exhaust connector 4 is connected to the tank vent valve 6.
A filling pipeline 7 is further arranged between the on-shelf filling pipeline 1 and the on-shelf exhaust pipeline 3, and the filling pipeline 7 is used for communicating the on-shelf filling pipeline 1 with the on-shelf exhaust pipeline 3. The filling pipeline 7 is provided with a filling stop valve 71 which is used for controlling the on-off of pipelines among the filling pipeline 1 on the shelf, the filling pipeline 7 and the exhaust pipeline 3 on the shelf. A ground filling valve 11 is arranged at one side of the on-shelf filling pipeline 1 connected with the ground filling system 100. After the ground filling valve 11 is opened, propellant in the ground filling system 100 can be filled into the on-frame filling pipeline 1, and the liquid propellant can be filled and replenished into the storage tank by regulating and controlling the ground filling valve, the filling connector, the storage tank filling valve, the storage tank exhaust valve, the exhaust connector and the filling stop valve.
Specifically, the filling line needs to be pre-cooled before the storage tank is filled with the liquid propellant. First, the ground filling valve 11, the tank filling valve 5, and the tank vent valve 6 are opened to communicate the filling connector 2 with the discharge connector 4. The liquid propellant enters the storage tank 300 from the ground filling system 100 through the ground filling valve 11, the on-shelf filling pipeline 1, the filling connector 2 and the storage tank filling valve 5, and part of the liquid propellant is gasified into the gaseous propellant in the precooling process. And the gaseous propellant is discharged to the ground waste gas treatment system 200 through the storage tank exhaust valve 6, the exhaust connector 4 and the shelf exhaust pipeline 3 until precooling is completed. During the precooling process, the flow rate of the propellant is kept between 300 and 500L/min.
After the liquid propellant filling system is precooled, the ground filling valve 11, the storage tank filling valve 5 and the storage tank exhaust valve 6 are opened, the filling connector 2 and the exhaust connector 4 are communicated, and the filling stop valve 71 is closed. The liquid propellant enters the tank 300 from the ground filling system 100 through the ground filling valve 11, the on-shelf filling pipe 1, the filling connector 2 and the tank filling valve 5. With the increase of the propellant in the storage tank, the gas in the storage tank is exhausted to the ground waste gas treatment system 200 through the storage tank exhaust valve 6, the exhaust connector 4 and the on-shelf exhaust pipeline 3 until the filling of the liquid propellant in the storage tank is completed.
The propellant in the on-shelf filling line 1 can be emptied after the tank filling is completed. When the tank needs to be refilled, the on-shelf refill line 1 is filled with liquid propellant from the surface refill system 100 by first opening the fill stop valve 71 and then opening the surface refill valve 11. The propellant that is vaporized during the filling process flows out through the filling line 7 and the rack exhaust line 3 to the ground exhaust gas treatment system. In this process, the filling flow rate of the liquid propellant is controlled at 200 to 300L/min. After the filling of the on-shelf filling line 1 is completed, the tank filling valve 5 is opened and then the filling stop valve 71 is closed, so that the liquid propellant enters the tank 300 and the tank is filled again.
Further, when the shelf filling line 1 is emptied and the liquid propellant in the storage tank 300 needs to be discharged, the filling stop valve 71 is opened first, then the ground filling valve 11 is opened, the ground filling system 100 supplies the low-temperature propellant to the shelf filling line 1, and the shelf filling line 1 is filled. The propellant flows through the filling shut-off valve 71 into the rack exhaust line 3 to exhaust gas treatment. The propellant filling flow is generally controlled at 200-300L/min, when the temperature of the low-temperature propellant is reduced to a preset temperature, the ground filling valve 11 is closed and the storage tank filling valve 5 is opened, after 10s, the filling stop valve 71 is closed, the ground filling valve 11 is opened, the on-shelf filling pipeline 1 is communicated with a propellant storage area, and the propellant in the storage tank is discharged to a storage tank of the storage area through the filling connector 2 and the on-shelf filling pipeline 1.
In the above embodiment, at least part of the on-shelf filling line 1 and the on-shelf exhaust line 3 are laid on the rising frame 400, and the weight of the on-shelf filling line and the on-shelf exhaust line is loaded by the rising frame 400.
With continued reference to fig. 1, in one embodiment, the on-shelf filling line 1 is also provided with a filter 12. The utility model discloses rocket liquid propellant filling system can filter the surplus thing in the propellant, guarantees to fill the propellant of entering the storage tank and does not have other impurity to sneak into.
Further, to extend the useful life of the filter, a filter 12 may be provided downstream of the surface filling valve 11. That is, the propellant in the surface filling system 100 is filtered through the filter 12 and eventually filled into the tank after the surface filling valve 11 is opened.
In one embodiment, a pressure sensor 13 is also provided between the surface filling valve 11 and the filter 12. The pressure sensor 13 is used for monitoring the pressure of the filling pipeline 1 on the shelf when the storage tank is subjected to supplementary filling, and the measured pressure of the pressure sensor 1 is prevented from being higher than the opening pressure of the storage tank filling valve 5.
Specifically, the flow rate of the liquid propellant is typically controlled to 200 to 300L/min when replenishing the tank with propellant. During propellant filling, the pressure measured by the pressure sensor 13 needs to be observed, and if the pressure of the pressure sensor is higher than the opening pressure of the tank filling valve 5, the filling flow of the propellant needs to be reduced in time. For example, the propellant fill flow rate may be varied by varying the opening of the surface fill valve.
Further, the opening pressure of the tank filling valve is not more than 0.4MPa.
With continued reference to fig. 1, in one embodiment, the fill line 7 is also provided with a temperature sensor 72. The temperature sensor 72 is used to monitor the temperature of the propellant as the reservoir 300 is refilled. When the measured temperature falls to a predetermined temperature (typically not higher than 120K), the tank filling valve 10s is opened and the filling stop valve 71 is closed to allow liquid propellant to enter the tank and start refilling of the propellant.
In one embodiment, to facilitate filling of the reservoir with liquid propellant and venting of gaseous propellant, a reservoir fill valve 5 may be provided at the bottom of the reservoir 300 and a reservoir vent valve 6 may be provided at the top of the reservoir 300.
In the above embodiments, the filling connector 2 may be removably connected to the tank filling valve 5 to facilitate installation, removal and replacement of the filling connector. To facilitate installation, removal and replacement of the vent connector, the vent connector 4 may be removably connected to the tank vent valve 6.
The above embodiments of the present invention can be combined with each other, and have corresponding technical effects.
The utility model provides a pair of rocket liquid propellant filling system has replaced utilizing the tank to fill the means of propellant for the evacuation on-frame filling pipeline among the prior art, when having avoided the evacuation filling pipeline to carry out propellant filling, thereby arouse the pressure shock that the violent exchange of temperature brought because of the difference in temperature is too big. The safe filling when the supplementary filling is needed again after the storage tank propellant is filled is realized, the pressure impact caused by the violent temperature exchange when the emptied filling pipeline is used for filling the propellant is avoided, and the safety of the propellant filling system is improved.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A rocket liquid propellant filling system is characterized by at least comprising an on-frame filling pipeline and a filling connector which are connected with a ground filling system, and an on-frame exhaust pipeline and an exhaust connector which are connected with a ground exhaust gas treatment system;
one end of the filling connector is connected with the filling pipeline on the frame, and the other end of the filling connector is connected with the storage tank through the storage tank filling valve; one end of the exhaust connector is connected with the exhaust pipeline on the rack, and the other end of the exhaust connector is connected with the storage tank through a storage tank exhaust valve;
the on-frame filling pipeline is connected with the on-frame exhaust pipeline through a filling pipeline, and the filling pipeline is provided with a filling stop valve; a ground filling valve is arranged on one side of the on-frame filling pipeline connected with the ground filling system;
by regulating the ground filling valve, the filling connector, the storage tank filling valve, the storage tank exhaust valve, the exhaust connector and the filling stop valve, the storage tank can be filled with liquid propellant and replenished.
2. A rocket liquid propellant filling system as recited in claim 1, wherein said on-shelf filling line is further provided with a filter to filter out excess in propellant.
3. A rocket liquid propellant filling system as recited in claim 2, wherein said filter is disposed downstream of said ground filling valve.
4. A rocket liquid propellant filling system as recited in claim 3, wherein a pressure sensor is further disposed between said ground filling valve and said filter; the pressure sensor is used for monitoring the pressure of the filling pipeline on the frame when the storage tank is filled in a supplementing mode, and the fact that the measuring pressure of the pressure sensor is higher than the opening pressure of the storage tank filling valve is avoided.
5. A rocket liquid propellant filling system as recited in claim 4, wherein the tank fill valve has an opening pressure of no more than 0.4MPa.
6. A rocket liquid propellant filling system as claimed in any one of claims 1 to 5, wherein said filling line is further provided with a temperature sensor; the temperature sensor is used for monitoring the temperature of the propellant when the storage tank is replenished, and when the measured temperature is reduced to a preset temperature, the filling stop valve is closed after the storage tank filling valve is opened, and the refilling of the propellant is started.
7. A rocket liquid propellant filling system as recited in claim 6, wherein said filling shut-off valve is closed after opening said tank filling valve for 10 seconds when the measured temperature falls to a predetermined temperature.
8. A rocket liquid propellant filling system as recited in claim 6, wherein said tank fill valve is disposed at the bottom of the tank and said tank vent valve is disposed at the top of the tank.
9. A rocket liquid propellant filling system as recited in claim 8, wherein said filling connector is removably connected to said tank filling valve; the vent connector is removably connected to the tank vent valve.
10. A rocket liquid propellant filling system as recited in claim 1, wherein at least some of said on-carriage filling lines and said on-carriage exhaust lines are laid on a riser.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222230537.XU CN218519861U (en) | 2022-08-24 | 2022-08-24 | Rocket liquid propellant filling system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222230537.XU CN218519861U (en) | 2022-08-24 | 2022-08-24 | Rocket liquid propellant filling system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218519861U true CN218519861U (en) | 2023-02-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222230537.XU Active CN218519861U (en) | 2022-08-24 | 2022-08-24 | Rocket liquid propellant filling system |
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| Country | Link |
|---|---|
| CN (1) | CN218519861U (en) |
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2022
- 2022-08-24 CN CN202222230537.XU patent/CN218519861U/en active Active
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