CN119826023A - POGO vibration suppression system and POGO vibration suppression method - Google Patents
POGO vibration suppression system and POGO vibration suppression method Download PDFInfo
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- CN119826023A CN119826023A CN202510140231.0A CN202510140231A CN119826023A CN 119826023 A CN119826023 A CN 119826023A CN 202510140231 A CN202510140231 A CN 202510140231A CN 119826023 A CN119826023 A CN 119826023A
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Abstract
The invention discloses a POGO vibration suppression system and a POGO vibration suppression method, which belong to the field of liquid carrier rocket power systems and comprise an accumulator and an air injection pipeline, wherein the accumulator is a sealed pressure container with a containing cavity inside, a propellant storage tank conveying pipe is communicated with the containing cavity, the accumulator is configured to depend on propellant conveyed to the containing cavity by the propellant storage tank conveying pipe, an air pillow for suppressing POGO vibration is formed at the upper part of the containing cavity, an inlet end of the air injection pipeline is connected with a propellant pressurizing pipeline, an outlet end of the air injection pipeline is communicated with the containing cavity at the upper part of the accumulator, and the air injection pipeline is configured to realize volume control of the air pillow by filling gasified propellant into the containing cavity. The invention does not need to carry an extra helium gas source or carry out inflation before shooting, thereby greatly reducing the complexity of a power system on an arrow and improving the reliability of shooting.
Description
Technical Field
The invention relates to the field of liquid carrier rocket power systems, in particular to a POGO vibration suppression system and a POGO vibration suppression method.
Background
POGO vibration refers to unstable low-frequency vibration generated by mutual coupling of dynamic characteristics of a liquid carrier rocket structure system and a propulsion system, is automatically generated, increased, then reduced and even eliminated along with rocket flight in the launching process, and can cause the effective load to be damaged or exceed the bearing limit of astronauts, so that the potential danger of longitudinal coupling vibration of a large liquid carrier rocket is generally existed in the flight process.
The method for suppressing the longitudinal vibration of the POGO is to install a large concentrated elastic element, namely an accumulator, at the inlet of the engine pump, and is generally classified into a spring type, a gas storage type and a gas injection type according to the type of accumulator.
The prior Chinese patent No. 117006111A discloses a gas injection type pressure accumulator, a POGO vibration suppression system and a POGO vibration suppression method, and the gas injection type pressure accumulator of helium is utilized to realize the POGO vibration suppression of a large carrier rocket. According to the scheme, a helium pressurization scheme is adopted, a high-pressure helium gas cylinder is inflated when a rocket is launched, and the opening and closing of an accumulator inflation electromagnetic valve are controlled in real time to supplement air according to the required air pillow volume in an accumulator air cavity in the flying process. The scheme leads to the improvement of the complexity of the rocket system, additional helium gas sources, inflation valves and other rocket-mounted components are needed to be carried, and meanwhile, the ground system is also needed to be matched with an inflation tool. In addition, this solution also easily causes the leakage of the cylinder before the rocket is launched, which results in a delay of the launch.
In view of the foregoing, it is necessary to provide a new solution to the above-mentioned problems.
Disclosure of Invention
In order to solve the technical problems, the application provides a POGO vibration suppression system and a POGO vibration suppression method, and provides a scheme for injecting gas by utilizing self-generated pressurized gas of a storage tank, so that an additional helium gas source is not needed to be carried, and inflation before shooting is not needed, the complexity of a power system on an arrow is greatly reduced, and the reliability of emission is also improved.
A POGO vibration suppression system comprising:
The device comprises a storage cavity, an accumulator, a propellant storage tank conveying pipe, a gas cushion, a gas pump and a control valve, wherein the storage cavity is arranged in the storage cavity;
The inlet end of the gas injection pipeline is connected with the propellant pressurizing pipeline, the outlet end of the gas injection pipeline is communicated with the accommodating cavity at the upper part of the pressure accumulator, and the gas injection pipeline is configured to realize the volume control of the gas pillow by filling the gasified propellant volume into the accommodating cavity.
Preferably, the device further comprises a liquid level detection device which is arranged in the accommodating cavity and used for detecting the liquid level of the propellant in the accommodating cavity.
Preferably, the device further comprises a discharge pipeline for discharging redundant gas in the accommodating cavity.
Preferably, the discharge pipeline is communicated with the accommodating cavity, and the discharge port of the discharge pipeline is positioned above the level of the highest point at which the propellant storage tank conveying pipe is communicated with the accommodating cavity.
Preferably, an emergency discharge valve for controlling the on-off of the discharge pipeline is arranged on the discharge pipeline.
Preferably, the gas injection pipeline is provided with a stop valve and a flow limiting device, and the stop valve and the flow limiting device are arranged on the gas injection pipeline in series.
Preferably, the stop valve is an electromagnetic stop valve.
Preferably, the flow limiting device is an orifice plate.
According to another aspect of the present application, there is also provided a POGO vibration suppression method, which utilizes a POGO vibration suppression system to achieve POGO vibration suppression;
The accumulator is a sealed pressure container with a containing cavity inside; the pressure accumulator is configured to rely on the propellant conveyed to the accommodating cavity by the propellant conveying pipe, and a gas pillow for inhibiting POGO vibration is formed at the upper part of the accommodating cavity;
The gas injection pipeline is configured to realize volume control of the gas pillow by filling the gasified propellant volume into the accommodating cavity, and is provided with a stop valve and a flow limiting device which are arranged on the gas injection pipeline in series;
The liquid level detection device is arranged in the accommodating cavity and is used for detecting the liquid level of the propellant in the accommodating cavity;
The device comprises a storage cavity, a propellant storage tank conveying pipe, a discharge pipeline, an emergency discharge valve, a control valve and a control valve, wherein the storage cavity is communicated with the storage cavity;
the POGO vibration suppression method comprises the following steps:
propellant is filled in the propellant storage tank before rocket launching, the propellant enters the accommodating cavity through the propellant storage tank conveying pipe, and a gas cushion is formed at the upper part of the accommodating cavity;
detecting the liquid level of the propellant in the accommodating cavity through a liquid level detection device in the rocket flight process, and calculating the air pillow volume through the liquid level of the propellant;
and (3) performing inflation control according to the preset air pillow volumes required by different flight periods and the corresponding upper and lower limit ranges of the liquid level, so as to further realize POGO vibration suppression.
Preferably, the inflation control is performed according to the preset air pillow volumes required by different flight periods and the corresponding upper and lower liquid level limit ranges, including:
the rocket power control system collects the liquid level height in the accommodating cavity through the liquid level detection device;
When the volume of the air pillow in the accommodating cavity is smaller, a stop valve on the air injection pipeline is opened to charge air into the accommodating cavity, and the stop valve is closed after the liquid level is reduced to a lower limit range, so that the POGO inhibiting capacity is achieved;
when the liquid level in the accommodating cavity is too low, the emergency discharge valve is opened to discharge air so as to improve the liquid level of the propellant in the accommodating cavity and ensure the safety of the engine.
Compared with the prior art, the application has at least the following beneficial effects:
1. the gas injection accumulator system has simple principle, reduces the complexity of rocket and ground gas supply systems, and improves the emission reliability of rockets.
2. The invention carries out the gas injection of the accumulator by self-generated pressurized gas, does not need to additionally carry a gas source, and has simple system structure.
3. The invention does not need to be inflated before transmitting, reduces the complexity of a ground system and simplifies the transmitting step.
4. The invention greatly reduces the weight of the rocket and improves the carrying capacity of the rocket.
5. According to the invention, the liquid level in the accommodating cavity can be detected through the liquid level detection device in the accumulator, so that the inflation time can be effectively judged.
Drawings
Some specific embodiments of the invention will be described in detail hereinafter by way of example and not by way of limitation with reference to the accompanying drawings. The same reference numbers will be used throughout the drawings to refer to the same or like parts or portions. It will be appreciated by those skilled in the art that the drawings are not necessarily drawn to scale. In the accompanying drawings:
FIG. 1 is a schematic diagram of the system connection of the POGO vibration suppression system of the present invention.
Wherein the above figures include the following reference numerals:
10. the device comprises an accumulator, 11 parts of a containing cavity, 12 parts of a liquid level detection device, 20 parts of an air injection pipeline, 21 parts of a stop valve, 22 parts of a flow limiting device, 30 parts of a discharge pipeline, 31 parts of an emergency discharge valve, 40 parts of a propellant storage tank, 50 parts of a propellant storage tank conveying pipe, 51 parts of a connecting hole, 60 parts of a propellant pressurizing pipeline.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be clearly and completely described below with reference to specific embodiments of the present application and corresponding drawings. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
Example 1
As shown in fig. 1, a POGO vibration suppression system includes an accumulator 10 and an air injection line 20.
The accumulator 10 is a sealed pressure vessel having a housing chamber 11 therein, a propellant reservoir delivery pipe 50 communicates with the housing chamber 11, and the accumulator 10 is configured to rely on the propellant delivered from the propellant reservoir delivery pipe 50 to the housing chamber 11, and a gas cushion for suppressing the vibration of the POGO is formed at the upper portion of the housing chamber 11.
The propellant tank delivery pipe 50 is a pipeline between the propellant tank 40 and the rocket engine pump and is used for delivering corresponding propellant to the rocket engine pump, and the propellant tank delivery pipe can be an oxidant delivery pipe or a fuel delivery pipe.
In the present embodiment, the propellant reservoir delivery tube 50 located within the receiving chamber 11 is provided with a communication aperture 51. By virtue of the communication action of the communication holes 51, the propellant in the propellant reservoir delivery tube 50 can enter the accommodating chamber 11 and can form a gas cushion in the upper part of the accommodating chamber 11.
Preferably, the communication hole 51 is provided on the propellant tank delivery tube 50 at the lower portion of the housing chamber 11. This arrangement ensures that the gas in the gas holder is prevented to the maximum extent from entering the propellant reservoir delivery tube 50 through the communication hole 51 while the gas holder is formed in the upper portion of the housing chamber 11, thereby ensuring the safety of the engine.
Preferably, the accumulator 10 is mounted at the end of the propellant reservoir delivery tube 50 to be as close as possible to the rocket engine pump inlet to enhance the effectiveness of POGO vibration suppression.
The inlet end of the gas injection pipeline 20 is connected with the propellant pressurizing pipeline 60, the outlet end of the gas injection pipeline 20 is communicated with the accommodating cavity 11 at the upper part of the pressure accumulator 10, and the gas injection pipeline 20 is configured to realize the volume control of the gas pillow by filling the gasified propellant volume into the accommodating cavity 11.
The propellant booster line 60 is a branch line led out from the high-pressure delivery line after the engine pump, and is used to pressurize the propellant reservoir 40 to ensure that the propellant is stably delivered to the engine pump and pumped to the rocket engine. Propellant in a branch of a high-pressure conveying pipeline behind the engine pump is gasified through an evaporator and is regulated to a proper temperature to form pressurized gas, the pressurized gas is introduced into the propellant storage tank 40 through a propellant pressurizing pipeline 60 for pressurizing, and the propellant pressurizing pipeline 60 is a vertical pipeline and is connected with an engine pressurizing gas outlet and a propellant storage tank 40 pressurizing gas inlet.
As another embodiment of the present invention, the POGO vibration suppressing system further includes a liquid level detecting device 12 provided inside the containing chamber 11 for detecting a liquid level of the propellant inside the containing chamber 11.
As another embodiment of the present invention, the POGO vibration suppressing system further includes a discharge pipe 30 for discharging the surplus gas in the accommodation chamber 11. The discharge line 30 communicates with the receiving chamber 11, and the discharge opening of the discharge line 30 is located above the level of the highest point where the propellant reservoir delivery tube 50 communicates with the receiving chamber 11.
Preferably, the discharge pipeline 30 is provided with an emergency discharge valve 31 for controlling the on-off of the discharge pipeline.
As another embodiment of the invention, the gas injection pipeline 20 is provided with a stop valve 21 and a flow limiting device 22, and the stop valve 21 and the flow limiting device 22 are arranged on the gas injection pipeline 20 in series.
Preferably, the shut-off valve 21 is an electromagnetic shut-off valve.
Preferably, the restriction 22 is an orifice plate.
Example 2
A POGO vibration suppression method utilizes a POGO vibration suppression system to realize POGO vibration suppression.
As shown in fig. 1, the POGO vibration suppression system includes an accumulator 10, a gas injection line 20, a liquid level detection device 12, and a discharge line 30;
the pressure accumulator 10 is a sealed pressure container with a containing cavity 11 inside, a propellant storage tank conveying pipe 50 is communicated with the containing cavity 11, and the pressure accumulator 10 is configured to rely on the propellant conveyed to the containing cavity 11 by the propellant storage tank conveying pipe 50, and a gas pillow for inhibiting POGO vibration is formed at the upper part of the containing cavity 11;
The inlet end of the gas injection pipeline 20 is connected with the propellant pressurizing pipeline 60, and the outlet end of the gas injection pipeline 20 is communicated with the accommodating cavity 11 at the upper part of the pressure accumulator 10, the gas injection pipeline 20 is configured to realize the volume control of the gas pillow by filling the gasified propellant volume into the accommodating cavity 11, the gas injection pipeline 20 is provided with a stop valve 21 and a flow limiting device 22, and the stop valve 21 and the flow limiting device 22 are arranged on the gas injection pipeline 20 in series;
The liquid level detection device 12 is arranged inside the accommodating cavity 11 and is used for detecting the liquid level of the propellant inside the accommodating cavity 11;
The discharge pipeline 30 is communicated with the accommodating cavity 11, a discharge opening of the discharge pipeline 30 is positioned above a horizontal plane of the highest point of the communication position of the propellant storage tank conveying pipe 50 and the accommodating cavity 11, and an emergency discharge valve 31 for controlling the on-off of the discharge pipeline 30 is arranged on the discharge pipeline 30.
Further, the POGO vibration suppression system in this embodiment may further include all the components in embodiment 1, and the connection relationship and the positional relationship of each component are the same as those in embodiment 1, which is not described herein.
The POGO vibration suppression method comprises the following steps:
S1, propellant is filled in a propellant storage tank before rocket launching, and the propellant enters the accommodating cavity 11 through the propellant storage tank conveying pipe 50, and a gas cushion is formed at the upper part of the accommodating cavity 11.
And S2, detecting the liquid level of the propellant in the accommodating cavity 11 by a liquid level detection device 12 in the rocket flight process, and calculating the air pillow volume by the liquid level of the propellant.
Specifically, since the total height and the sectional area at each height in the housing chamber 11 are determined, the air pillow height can be determined by detecting the liquid level, and can be converted into the air pillow volume.
And S3, performing inflation control according to preset air pillow volumes required by different flight periods and corresponding liquid level upper and lower limit ranges, so as to further realize POGO vibration suppression.
Wherein, according to the required air pillow volume of different flight periods of preset and corresponding liquid level upper and lower limit scope, carry out inflation control, include:
the rocket power control system collects the liquid level height in the accommodating cavity 11 through the liquid level detection device 12;
When the volume of the air pillow in the accommodating cavity 11 is smaller, a stop valve 21 on the air injection pipeline 20 is opened to charge air into the accommodating cavity 11, and the stop valve 21 is closed after the liquid level is reduced to a lower limit range, so that the POGO inhibiting capacity is achieved;
When the liquid level in the accommodating cavity 11 is too low, the emergency discharge valve 31 is opened to discharge air so as to improve the liquid level of the propellant in the accommodating cavity 11 and ensure the safety of the engine.
Because when the liquid level in the accommodating cavity 11 is too low, the risk that gas in the accommodating cavity 11 enters the inlet of the engine pump possibly exists, an emergency exhaust device is arranged in the pressure accumulator 10, and the exhaust pipeline 30 is arranged in the POGO vibration suppression system, so that the emergency exhaust valve 31 can be opened for exhausting when the liquid level is too low, the propellant liquid level in the accommodating cavity 11 is improved, and the safety of the engine is ensured.
Spatially relative terms, such as "above," "upper" and "upper surface," "above" and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the process is carried out, the exemplary term "above" may be included. Upper and lower. Two orientations below. The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
It should be noted that the terms "first," "second," and the like in the description and the claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that embodiments of the application described herein may be implemented in sequences other than those illustrated or otherwise described herein.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, 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 POGO vibration suppression system comprises an accumulator (10) and a gas injection pipeline (20), and is characterized in that:
The pressure accumulator (10) is a sealed pressure container with a containing cavity (11) inside, the propellant storage tank conveying pipe (50) is communicated with the containing cavity (11), the pressure accumulator (10) is configured to convey propellant to the containing cavity (11) by means of the propellant storage tank conveying pipe (50), and a gas cushion for inhibiting POGO vibration is formed at the upper part of the containing cavity (11);
The inlet end of the gas injection pipeline (20) is connected with the propellant pressurizing pipeline (60), the outlet end of the gas injection pipeline (20) is communicated with the accommodating cavity (11) at the upper part of the pressure accumulator (10), and the gas injection pipeline (20) is configured to realize the volume control of the gas pillow by filling the gasified propellant volume into the accommodating cavity (11).
2. The POGO vibration suppression system of claim 1, further comprising a liquid level detection means (12) provided inside said housing chamber (11) for detecting a liquid level of a propellant inside said housing chamber (11).
3. The POGO vibration suppression system as claimed in claim 2, further comprising a discharge pipe (30) for discharging the surplus gas in the accommodation chamber (11).
4. A POGO vibration inhibiting system as claimed in claim 3, wherein said discharge line (30) is in communication with said housing chamber (11), and wherein said discharge line (30) discharge port is located above the level of the highest point where said propellant reservoir delivery tube (50) is in communication with said housing chamber (11).
5. The POGO vibration suppression system of claim 4, wherein said vent line (30) is provided with an emergency vent valve (31) for controlling the opening and closing thereof.
6. The POGO vibration suppression system of claim 5, wherein said gas injection line (20) has a shut-off valve (21) and a flow restrictor (22), said shut-off valve (21) and said flow restrictor (22) being serially disposed on said gas injection line (20).
7. The POGO vibration suppression system as claimed in claim 6, wherein said shut-off valve (21) is an electromagnetic shut-off valve.
8. The POGO vibration suppression system of claim 7, wherein said flow restriction means (22) is an orifice plate.
9. The POGO vibration suppression method is characterized in that the POGO vibration suppression is realized by a POGO vibration suppression system, wherein the POGO vibration suppression system comprises an accumulator (10), a gas injection pipeline (20), a liquid level detection device (12) and a discharge pipeline (30);
The pressure accumulator (10) is a sealed pressure container with a containing cavity (11) inside, the propellant storage tank conveying pipe (50) is communicated with the containing cavity (11), the pressure accumulator (10) is configured to convey propellant to the containing cavity (11) by means of the propellant storage tank conveying pipe (50), and a gas cushion for inhibiting POGO vibration is formed at the upper part of the containing cavity (11);
The inlet end of the gas injection pipeline (20) is connected with a propellant pressurizing pipeline (60), the outlet end of the gas injection pipeline (20) is communicated with the accommodating cavity (11) at the upper part of the pressure accumulator (10), the gas injection pipeline (20) is configured to realize the volume control of the gas pillow by filling the gasified propellant volume into the accommodating cavity (11), the gas injection pipeline (20) is provided with a stop valve (21) and a flow limiting device (22), and the stop valve (21) and the flow limiting device (22) are arranged on the gas injection pipeline (20) in series;
the liquid level detection device (12) is arranged in the accommodating cavity (11) and is used for detecting the liquid level of the propellant in the accommodating cavity (11);
The discharge pipeline (30) is communicated with the accommodating cavity (11), a discharge port of the discharge pipeline (30) is positioned above a horizontal plane of the highest point of the communication position of the propellant storage tank conveying pipe (50) and the accommodating cavity (11), and an emergency discharge valve (31) for controlling the on-off of the discharge pipeline (30) is arranged on the discharge pipeline (30);
the POGO vibration suppression method comprises the following steps:
Propellant is filled in a propellant storage tank (40) before rocket launching, the propellant enters a containing cavity (11) through a propellant storage tank conveying pipe (50), and a gas cushion is formed at the upper part of the containing cavity (11);
detecting the liquid level of the propellant in the accommodating cavity (11) through a liquid level detection device (12) in the rocket flight process, and calculating the air pillow volume through the liquid level of the propellant;
and (3) performing inflation control according to the preset air pillow volumes required by different flight periods and the corresponding upper and lower limit ranges of the liquid level, so as to further realize POGO vibration suppression.
10. The POGO vibration suppression method of claim 9, wherein said performing inflation control according to the preset air pillow volumes required for different flight periods and the corresponding upper and lower liquid level limit ranges comprises:
the rocket power control system collects the liquid level height in the accommodating cavity (11) through the liquid level detection device (12);
When the volume of the air pillow in the accommodating cavity (11) is smaller, a stop valve (21) on the air injection pipeline (20) is opened to charge air into the accommodating cavity (11), and the stop valve (21) is closed after the liquid level is reduced to a lower limit range so as to achieve the POGO inhibition capability;
When the liquid level in the accommodating cavity (11) is too low, the emergency discharge valve (31) is opened to discharge air so as to improve the liquid level of the propellant in the accommodating cavity (11) and ensure the safety of the engine.
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| CN202510140231.0A CN119826023B (en) | 2025-02-08 | 2025-02-08 | POGO vibration suppression system and POGO vibration suppression method |
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| CN202510140231.0A CN119826023B (en) | 2025-02-08 | 2025-02-08 | POGO vibration suppression system and POGO vibration suppression method |
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| US20220127019A1 (en) * | 2020-10-23 | 2022-04-28 | Arianegroup Gmbh | Rocket propulsion system, method, and spacecraft |
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| CN116816549A (en) * | 2023-06-28 | 2023-09-29 | 广州中科宇航探索技术有限公司 | Verification system and verification method for performance of liquid rocket booster conveying system |
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2025
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| CN101737199A (en) * | 2008-11-10 | 2010-06-16 | 北京航空航天大学 | Liquid propellant conveying system of blow-down rocket engine |
| KR20160144638A (en) * | 2015-06-09 | 2016-12-19 | 에이치앤피엔지니어링 (주) | Hydraulic servo actuators with cryogenic fluids |
| CN109322764A (en) * | 2018-10-17 | 2019-02-12 | 北京宇航系统工程研究所 | A low temperature liquid level controllable gas injection accumulator |
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| CN119826023B (en) | 2025-07-25 |
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