CN112377329B - Gas recovery type POGO suppressor for liquid rocket - Google Patents
Gas recovery type POGO suppressor for liquid rocket Download PDFInfo
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- CN112377329B CN112377329B CN202011188762.0A CN202011188762A CN112377329B CN 112377329 B CN112377329 B CN 112377329B CN 202011188762 A CN202011188762 A CN 202011188762A CN 112377329 B CN112377329 B CN 112377329B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/566—Control elements and safety devices, e.g. pressure relief valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The gas recovery type liquid rocket POGO suppressor is arranged between an engine propellant inlet and a propellant conveying pipe, and comprises a main body, an air inlet system, an exhaust system and a rocket central controller; the main body is communicated with a propellant storage tank of the liquid rocket through a propellant conveying pipe; the gas inlet system directly refers to gas of a gas cylinder of a liquid rocket pressurization system and outputs the gas to the main body; the exhaust system directly exhausts the gas in the main body into a propellant tank air pillow; the rocket central controller controls the air inlet system and the air outlet system, so that the air flow of the air inlet system is matched with the air flow of the air outlet system, and a constant volume air cavity is formed in the main body. The invention discloses a gas recovery type liquid rocket POGO suppressor, which solves the problems that the existing metal film box type POGO suppressor is small in volume, low in bearing capacity and incapable of working with variable energy.
Description
Technical Field
The invention relates to a liquid rocket POGO suppressor technology, in particular to a gas recovery type liquid rocket POGO suppressor.
Background
The POGO suppressor is a key device for suppressing the POGO effect (namely longitudinal coupling vibration) of a large liquid carrier rocket. The flexible gas cavity is generally arranged between a propellant conveying pipe and a propellant inlet of an engine, the natural frequency of a propellant conveying system is reduced, the natural frequency of the propellant conveying system is further separated from the natural frequency of an rocket body structure, the effect of restraining the POGO effect of a rocket is achieved, and the faults of load damage, astronaut discomfort, abnormal shutdown of the rocket engine, even rocket body damage and the like are avoided.
At present, the POGO suppressor of a liquid carrier rocket in China mainly uses a metal diaphragm capsule to realize flexible isolation of gas and liquid. However, the metal diaphragm box adopts a sheet welding or forming process, the production process is complex, the vibration and fatigue resistance is poor, the pressure bearing is low, and the use requirements of the POGO suppressor with large volume and high pressure bearing cannot be met. And the metal film box type POGO suppressor is usually in a fixed energy type, the energy in the flight process is constant, the design is usually customized for a certain rocket, and the product universality is not high.
Disclosure of Invention
The invention aims to provide a gas recovery type POGO (liquid rocket) suppressor, which solves the problems that the existing metal film box type POGO suppressor is small in volume, low in bearing capacity and incapable of working with variable energy.
In order to achieve the above object, the present invention provides a gas recovery type liquid rocket POGO suppressor, which is installed between an engine propellant inlet and a propellant conveying pipe, the gas recovery type liquid rocket POGO suppressor comprising a main body, an air intake system, an exhaust system and a rocket central controller; the main body is communicated with a propellant storage tank of the liquid rocket through a propellant conveying pipe; the gas inlet system directly refers to gas of a gas cylinder of a liquid rocket pressurization system and outputs the gas to the main body; the exhaust system directly exhausts the gas in the main body into a propellant tank air pillow; the rocket central controller controls the air inlet system and the air outlet system, so that the air flow of the air inlet system is matched with the air flow of the air outlet system, and a constant volume air cavity is formed in the main body.
The gas recovery type liquid rocket POGO suppressor is characterized in that the exhaust system comprises at least one liquid level pipe, and the liquid level pipe is arranged in the main body; the liquid level pipe is communicated with a propellant storage tank air pillow through an electromagnetic valve, and the rocket central controller controls the electromagnetic valve to be switched on and off; and the side wall of the liquid level pipe is provided with an exhaust hole.
The gas recovery type liquid rocket POGO suppressor comprises a gas recovery type liquid rocket POGO suppressor, wherein the gas exhaust system comprises more than two liquid level pipes, and each liquid level pipe is communicated with a propellant storage tank gas pillow through an electromagnetic valve; the exhaust holes of different liquid level pipes are different in installation height.
The gas recovery type liquid rocket POGO suppressor is characterized in that the exhaust holes are array holes arranged along the axial direction or waist-shaped holes arranged along the axial direction.
According to the gas recovery type liquid rocket POGO suppressor, due to the height difference of the rocket propellant liquid column and the flying overload, the pressure of the air cavity of the main body is greater than the pressure of the propellant storage tank air pillow, so that the gas in the main body is discharged into the propellant storage tank air pillow through the exhaust holes and is reused for pressurizing the rocket pressurizing system; the height of the air-liquid interface in the main body is determined by the installation height of the air vent, so that the volume of the air cavity in the main body is determined; the air inlet and exhaust flow of the exhaust system and the air inlet system are ensured to reach dynamic balance, so that the volume of the air cavity in the main body is kept constant.
In the gas recovery type POGO suppressor for the liquid rocket, when the pressure of a liquid cavity in the main body is lower than the pressure of an air cavity, a gas-liquid interface is reduced, the exhaust area of an exhaust hole in the air cavity of the main body is increased, the exhaust flow of an exhaust system is increased, the pressure of the air cavity of the main body is reduced, new balance is established with the pressure of the liquid cavity, and the volume stability of the air cavity in the main body is kept; when the pressure of the liquid cavity in the main body is higher than the pressure of the gas cavity, the gas-liquid interface rises, the exhaust area of the exhaust hole in the gas cavity of the main body is reduced, the exhaust flow of the exhaust system is reduced, the pressure of the gas cavity of the main body rises, new balance is established with the pressure of the liquid cavity, and the volume stability of the gas cavity in the main body is kept.
In the gas recovery type POGO suppressor for the liquid rocket, the rocket central controller changes the volume of the air cavity in the main body by controlling the working sequence of the liquid level pipes at different height positions.
The gas recovery type liquid rocket POGO suppressor comprises a main body, a gas recovery type liquid rocket POGO, a propellant flow channel and a gas recovery type liquid rocket POGO, wherein the main body comprises an annular cavity and the propellant flow channel; one end of the propellant flow channel is communicated with a propellant storage tank of the liquid rocket through a propellant conveying pipe, and the other end of the propellant flow channel is connected with a propellant inlet of the engine; the annular cavity is provided with a damping hole on the inner side wall, the damping hole is positioned at one end close to an engine propellant inlet, and the annular cavity is in propellant exchange with the propellant flow channel through the damping hole.
The gas recovery type liquid rocket POGO suppressor comprises a gas inlet system, a gas outlet system and a gas recovery type liquid rocket POGO suppressor, wherein the gas inlet system comprises a gas inlet electromagnetic valve, a pressure reducing valve, a filter, a throttling ring and a diffuser; the rocket central controller controls the air inlet electromagnetic valve to be communicated, and the gas in the gas cylinder of the liquid rocket pressurization system is output into the main body through the air inlet electromagnetic valve, the pressure reducing valve, the filter, the throttling ring and the diffuser, so that the gas with certain pressure and flow is continuously provided for the main body.
Compared with the prior art, the invention has the beneficial technical effects that:
according to the gas recovery type liquid rocket POGO suppressor, the central rocket controller controls the gas flow of the gas inlet system and the gas outlet system, so that a constant volume gas cavity is formed in the main body, gas and liquid surfaces are in free contact, and a gas-liquid isolating device is not needed, so that the large-volume and high-pressure-bearing design can be easily realized; the main body is a pure structural part, so that the manufacturing is simple and the strength is high;
according to the gas recovery type liquid rocket POGO suppressor, the gas in the gas cylinder group of the liquid rocket pressurization system is directly introduced into the gas inlet system, so that the independent arrangement of a gas source is avoided, and the weight and the cost are reduced; the exhaust system directly exhausts the gas in the main body into the gas pillow of the liquid rocket propellant storage tank, the gas is recycled for pressurizing the propellant storage tank, the recycling is realized, the waste is avoided, the gas of the rocket pressurizing system is not additionally consumed, and the gas is not exhausted out of the rocket body, so that the additional risk caused by the properties of low temperature, flammability, toxicity and the like of the exhausted gas is avoided;
the POGO inhibitor of the gas recovery type liquid rocket can expand the number of the liquid level pipes, is provided with a plurality of liquid level pipes with different heights, and a central controller of the rocket selectively controls the on-off of electromagnetic valves connected with the liquid level pipes with different heights, so that the volume and energy variable work of the POGO inhibitor in the flying process is realized, and the volume and energy variable requirements of the POGO inhibitor caused by the natural frequency change of the rocket in the flying process are met;
according to the gas recovery type liquid rocket POGO suppressor, the lower end of the side wall of the liquid level pipe is axially provided with the array holes or the waist-shaped holes as exhaust holes, the flow area of exhaust gas can be dynamically adjusted according to the position of a gas-liquid interface, the dynamic balance of the gas inlet flow and the exhaust flow is realized, and the volume stability of a main gas cavity of the POGO suppressor is further improved;
according to the gas recovery type liquid rocket POGO suppressor disclosed by the invention, the on-off time sequence of the air inlet electromagnetic valve and the exhaust electromagnetic valve is controlled by the rocket central controller, so that the POGO suppressor is controlled to be started only when the POGO suppressor needs to work.
Drawings
The gas recovery type liquid rocket POGO suppressor of the invention is given by the following examples and attached drawings.
Fig. 1 is a schematic diagram of a gas recovery liquid rocket POGO suppressor according to a preferred embodiment of the present invention.
FIG. 2 is a schematic diagram of the main body in the preferred embodiment of the present invention.
FIG. 3 is a schematic view of an air induction system in accordance with a preferred embodiment of the present invention.
FIG. 4 is a schematic view of an exhaust system in accordance with a preferred embodiment of the present invention.
FIG. 5 is a schematic view of the high level tube and the low level tube in the preferred embodiment of the present invention.
Detailed Description
The gas recovery liquid rocket POGO suppressor of the present invention will be described in further detail below with reference to fig. 1-5.
Fig. 1 is a schematic diagram of a gas recovery liquid rocket POGO suppressor according to a preferred embodiment of the present invention.
Referring to fig. 1, the gas recovery type liquid rocket POGO inhibitor of the present embodiment is installed between an engine propellant inlet and a propellant conveying pipe, and includes a main body 1, an air intake system 2, an exhaust system 3, and a rocket central controller 4;
the main body 1 is communicated with a propellant storage tank of the liquid rocket through a propellant conveying pipe;
the gas inlet system 2 directly refers to the gas of a liquid rocket pressurization system gas cylinder to be output to the main body 1;
the exhaust system 3 directly exhausts the gas in the main body 1 into a liquid rocket propellant tank air pillow;
the rocket central controller 4 controls the air inlet system 2 and the air outlet system 3, so that the air flow of the air inlet system 2 is matched with the air flow of the air outlet system 3, and a constant volume air cavity is formed in the main body 1.
According to the gas recovery type liquid rocket POGO suppressor, the gas flow of the gas inlet system 2 and the gas outlet system 3 is controlled by the rocket central controller 4, so that a constant volume gas cavity is formed in the main body 1, gas and liquid surfaces are in free contact, and a gas-liquid isolating device is not needed, so that the large-volume and high-pressure-bearing design can be easily realized; the gas inlet system 2 directly uses gas in a gas cylinder group of the liquid rocket pressurization system, so that a gas source is not arranged independently, and the weight and the cost are reduced; the exhaust system 3 directly exhausts the gas in the main body 1 into the gas pillow of the liquid rocket propellant storage tank, the gas is recycled for pressurizing the propellant storage tank, the gas is recycled, no waste is caused, the rocket pressurization system gas is not consumed additionally, and the gas is not exhausted outside the rocket body, so that additional risks caused by properties of low temperature, flammability, toxicity and the like of the exhausted gas are avoided.
FIG. 2 is a schematic diagram of the main body in the preferred embodiment of the present invention.
Referring to fig. 2, the main body 1 comprises an annular cavity 6 and a propellant flow channel 5, the propellant flow channel 5 is arranged in the center of the annular cavity 6, namely the annular cavity 6 surrounds the propellant flow channel 5, and the inner side wall of the annular cavity 6 forms a section of the propellant flow channel 5; one end of the propellant flow channel 5 is communicated with a propellant storage tank of the liquid rocket through a propellant conveying pipe, and the other end of the propellant flow channel 5 is connected with a propellant inlet of the engine; a damping hole 7 is formed in the inner side wall of the annular cavity 6, the damping hole 7 is located at one end close to an engine propellant inlet, and the annular cavity 6 is in propellant exchange with the propellant flow channel 5 through the damping hole 7; the annular cavity 6 is also provided with an air inlet and an air outlet which are respectively communicated with the air inlet system 2 and the exhaust system 3.
Preferably, the main body 1 can be manufactured by a machining and welding method, or a 3D printing method, and can be wound on the outer layer of the composite material to improve the bearing capacity and reduce the weight.
FIG. 3 is a schematic view of an air induction system in accordance with a preferred embodiment of the present invention.
Referring to fig. 3, the air intake system 2 includes a high pressure cylinder group 8, an air intake solenoid valve 9, a pressure reducing valve 10, a filter 11, a throttle ring 12, and a diffuser 13; the air inlet electromagnetic valve 9, the pressure reducing valve 10, the filter 11, the throttle washer 12 and the diffuser 13 are sequentially connected in series; the air inlet electromagnetic valve 9 is connected with the high-pressure air bottle group 8; the electrical interface of the air inlet electromagnetic valve 9 is connected with the rocket central controller 4.
The rocket central controller 4 controls the air inlet electromagnetic valve 9 to be communicated, and the high-pressure gas in the high-pressure gas cylinder group 8 is output into the annular cavity 6 through the air inlet electromagnetic valve 9, the pressure reducing valve 10, the filter 11, the throttle ring 12 and the diffuser 13, and the gas with certain pressure and flow is continuously provided for the annular cavity 6.
In this embodiment, the high-pressure gas cylinder group 8 directly utilizes the pressurizing gas cylinder group of the liquid rocket pressurizing system, and does not separately provide a gas source.
FIG. 4 is a schematic view of an exhaust system according to a preferred embodiment of the present invention; FIG. 5 is a schematic view of the high level tube and the low level tube in the preferred embodiment of the present invention.
Referring to fig. 4, the exhaust system 3 comprises a high level liquid level pipe 14, a low level liquid level pipe 15, a high level discharge electromagnetic valve 16, a low level discharge electromagnetic valve 17 and a propellant tank 18; the high-level discharge electromagnetic valve 16 is connected with the high-level liquid level pipe 14 in series, the high-level discharge electromagnetic valve 16 is connected with the propellant storage tank 18, the high-level liquid level pipe 14 is arranged in the annular cavity 6, and an electrical interface of the high-level discharge electromagnetic valve 16 is connected with the rocket central controller 4; the low-level discharge electromagnet 17 is connected with the low-level liquid level pipe 15 in series, the low-level discharge electromagnet 17 is connected with the propellant storage tank 18, the low-level liquid level pipe 15 is arranged in the annular cavity 6, and an electric interface of the low-level discharge electromagnet 17 is connected with the rocket central controller 4.
The rocket propellant liquid column height difference and the flight overload enable the air cavity pressure of the annular cavity 6 to be larger than the top air pillow pressure of the propellant storage tank 18, the exhaust system 3 utilizes the pressure difference between the air cavity of the annular cavity 6 and the air pillow of the propellant storage tank 18 to exhaust the gas in the annular cavity 6 into the air pillow of the propellant storage tank 18 in two ways, and the gas is not exhausted out of the rocket body, but is recovered and reused for pressurizing the rocket pressurizing system.
Referring to fig. 5, the lower side wall of the high level liquid level pipe 14 is provided with vent holes 19, and the vent holes 19 may be array holes arranged along the axial direction or kidney-shaped holes arranged along the axial direction. When the gas-liquid interface is positioned at different positions of the exhaust hole 19, the exhaust flow area can be dynamically adjusted, so that the exhaust flow of the exhaust system 3 can be adjusted; the installation height of the exhaust holes determines the height position of a gas-liquid interface, further determines the volume of the air cavity in the annular cavity 6, and POGO suppressors with different air cavity volumes and different energies can be designed by utilizing the installation height of the exhaust holes 19.
The side wall of the lower part of the low-level liquid level pipe 15 is provided with exhaust holes, and the exhaust holes can be array holes arranged along the axial direction or waist-shaped holes arranged along the axial direction.
The low-level liquid level pipe 15 and the high-level liquid level pipe 14 are similar in function and structure, only the installation height is different, the installation height of an exhaust hole of the low-level liquid level pipe 15 is lower, the height of a controlled gas-liquid interface is also lower, and the volume of a gas cavity in the annular cavity 6 is controlled to be larger.
Be equipped with two liquid level pipes in this embodiment, POGO inhibitor has variable volume, variable energy working ability in liquid rocket flight process. However, the invention does not limit the number of the liquid level pipes, and can only have one liquid level pipe or more than three liquid level pipes.
In this embodiment, a controller is not separately provided, and a central rocket controller is directly used, and the central rocket controller 4 controls the on-off time sequence of the air inlet solenoid valve 9, the high-level exhaust solenoid valve 16 and the low-level exhaust solenoid valve 17, so as to flexibly control the working time period of the POGO suppressor in the flight process.
The working principle of the gas recovery type liquid rocket POGO suppressor of the embodiment is as follows:
in the initial state, the annular cavity 6 is filled with liquid propellant; when the POGO inhibitor needs to work in rocket flight, the central controller 4 of the rocket controls the air inlet electromagnetic valve 9 to be electrified and opened, the air inlet system 2 inflates air into the annular cavity 6, the air pushes the propellant in the annular cavity 6 to enter the propellant flow channel 5 through the damping hole 7, and the annular cavity 6 is divided into an air cavity and a liquid cavity by a gas-liquid interface; when the gas-liquid interface in the annular cavity 6 descends to the position of the exhaust hole 19 of the high-level liquid level pipe 14, the rocket central controller 4 controls the high-level exhaust solenoid valve 16 to be powered on and opened, the pressure of the gas cavity of the annular cavity 6 is greater than the pressure of the top gas pillow of the propellant storage tank 18 due to the height difference of the rocket propellant liquid column and the flying overload, so that the gas in the annular cavity 6 is exhausted into the top gas pillow of the propellant storage tank 18 through the exhaust hole 19 of the high-level liquid level pipe 14 of the exhaust system 3, and the gas is reused for pressurizing the rocket pressurizing system; through the flow matching design, the air inlet and exhaust flow of the exhaust system 3 and the air inlet system 2 is ensured to reach dynamic balance, so that the volume of the air cavity in the annular cavity 6 is kept constant. The gas recovery formula liquid rocket POGO inhibitor of this embodiment passes through the annular and holds the gas flexibility in the chamber 6, reduces propellant conveying system's natural frequency, and then makes propellant conveying system's natural frequency and rocket body structure's natural frequency keep away from each other, reaches the effect of restraining rocket POGO effect.
When the liquid cavity pressure in the annular cavity 6 is lower than the air cavity pressure, the air-liquid interface is reduced, the exhaust area of the exhaust hole 19 of the high-level liquid level pipe 14 in the air cavity of the annular cavity 6 is increased, the exhaust flow of the exhaust system 3 is increased, the air cavity pressure of the annular cavity 6 is reduced, new balance is established with the liquid cavity pressure, and the volume of the air cavity in the annular cavity 6 is kept stable; when the liquid cavity pressure in the annular cavity 6 is higher than the air cavity pressure, the air-liquid interface rises, the exhaust area of the exhaust hole 19 of the high-level liquid level pipe 14 in the air cavity of the annular cavity 6 is reduced, the exhaust flow of the exhaust system 3 is reduced, the air cavity pressure of the annular cavity 6 rises, new balance is established with the liquid cavity pressure, and the volume stability of the air cavity in the annular cavity 6 is kept. The gas recovery type liquid rocket POGO suppressor can dynamically adjust the flow area of exhaust gas according to the gas-liquid interface position, realize the dynamic balance of the gas inflow and the gas outflow, and further improve the volume stability of a main body air cavity of the POGO suppressor.
When the natural frequency of the rocket changes in the flying process and the volume of the air cavity of the annular containing cavity 6 of the POGO inhibitor needs to be increased, the central controller 4 of the rocket controls the high-level discharge electromagnetic valve 16 to be powered off and closed, and controls the low-level discharge electromagnetic valve 17 to be powered on and opened at the same time, the air-liquid interface in the annular containing cavity 6 reestablishes balance near the main exhaust hole of the low-level liquid level pipe 15, so that the volume of the air cavity in the annular containing cavity 6 is increased, and the volume-variable and energy-variable work of the POGO inhibitor in the flying process is realized.
In this embodiment, the rocket central controller 4 can change the sequence of the two exhaust paths of the exhaust system 3 according to the requirement. Furthermore, the liquid level pipe is not limited in quantity, the liquid level pipe can be expanded, and the liquid level pipes at different height positions are arranged, so that various volume change requirements are met.
In conclusion, the gas recovery type POGO suppressor of the liquid rocket achieves the beneficial effects of gas recovery, volume change, energy change and the like.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (3)
1. The gas recovery type liquid rocket POGO suppressor is arranged between an engine propellant inlet and a propellant conveying pipe and is characterized by comprising a main body, an air inlet system, an exhaust system and a rocket central controller;
the main body is communicated with a propellant storage tank of the liquid rocket through a propellant conveying pipe;
the gas inlet system directly refers to gas of a gas cylinder of a liquid rocket pressurization system and outputs the gas to the main body;
the exhaust system directly exhausts the gas in the main body into a propellant tank air pillow;
the rocket central controller controls the air inlet system and the air outlet system to enable the air flow of the air inlet system to be matched with the air flow of the air outlet system, and a constant volume air cavity is formed in the main body;
due to the height difference of the rocket propellant liquid column and the flying overload, the pressure of the air cavity of the main body is greater than the pressure of the propellant storage tank air pillow, so that the gas in the main body is discharged into the propellant storage tank air pillow through the exhaust holes and is reused for pressurizing the rocket pressurizing system; the height of the air-liquid interface in the main body is determined by the installation height of the air vent, so that the volume of the air cavity in the main body is determined; the air inlet and exhaust flow of the exhaust system and the air inlet system are ensured to reach dynamic balance, so that the volume of the air cavity in the main body is kept constant;
the air inlet system comprises an air inlet electromagnetic valve, a pressure reducing valve, a filter, a throttling ring and a diffuser; the rocket central controller controls the air inlet electromagnetic valve to be communicated, and the gas in the gas cylinder of the liquid rocket pressurization system is output into the main body through the air inlet electromagnetic valve, the pressure reducing valve, the filter, the throttling ring and the diffuser, so that the gas with certain pressure and flow is continuously provided for the main body;
the exhaust system comprises at least one liquid level pipe, and the liquid level pipe is arranged in the main body; the liquid level pipe is communicated with a propellant storage tank air pillow through an electromagnetic valve, and the rocket central controller controls the electromagnetic valve to be switched on and off; the side wall of the liquid level pipe is provided with an exhaust hole;
the exhaust system comprises more than two liquid level pipes, and each liquid level pipe is communicated with the propellant storage tank air pillow through an electromagnetic valve; the exhaust holes of different liquid level pipes are different in installation height;
the rocket central controller changes the volume of the air cavity in the main body by controlling the working sequence of the liquid level pipes at different height positions.
2. The gas recovery liquid rocket POGO suppressor of claim 1 wherein said exhaust holes are axially arranged array holes or axially arranged kidney shaped holes;
when the pressure of the liquid cavity in the main body is lower than the pressure of the gas cavity, the gas-liquid interface is reduced, the exhaust area of the exhaust hole in the gas cavity of the main body is increased, the exhaust flow of the exhaust system is increased, the pressure of the gas cavity of the main body is reduced, new balance is established with the pressure of the liquid cavity, and the volume stability of the gas cavity in the main body is kept; when the pressure of the liquid cavity in the main body is higher than the pressure of the gas cavity, the gas-liquid interface rises, the exhaust area of the exhaust hole in the gas cavity of the main body is reduced, the exhaust flow of the exhaust system is reduced, the pressure of the gas cavity of the main body rises, new balance is established with the pressure of the liquid cavity, and the volume stability of the gas cavity in the main body is kept.
3. The gas recovery liquid rocket POGO suppressor of claim 1 wherein said body comprises an annular volume and a propellant flow channel, said propellant flow channel being centrally disposed in said annular volume; one end of the propellant flow channel is communicated with a propellant storage tank of the liquid rocket through a propellant conveying pipe, and the other end of the propellant flow channel is connected with a propellant inlet of the engine; the annular cavity is provided with a damping hole on the inner side wall, the damping hole is positioned at one end close to an engine propellant inlet, and the annular cavity is in propellant exchange with the propellant flow channel through the damping hole.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011188762.0A CN112377329B (en) | 2020-10-30 | 2020-10-30 | Gas recovery type POGO suppressor for liquid rocket |
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| CN202011188762.0A CN112377329B (en) | 2020-10-30 | 2020-10-30 | Gas recovery type POGO suppressor for liquid rocket |
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| CN112377329B true CN112377329B (en) | 2021-11-19 |
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