CN113719754B - Rocket liquid oxygen filling system and control method - Google Patents
Rocket liquid oxygen filling system and control method Download PDFInfo
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- CN113719754B CN113719754B CN202110988409.9A CN202110988409A CN113719754B CN 113719754 B CN113719754 B CN 113719754B CN 202110988409 A CN202110988409 A CN 202110988409A CN 113719754 B CN113719754 B CN 113719754B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D1/00—Pipe-line systems
- F17D1/08—Pipe-line systems for liquids or viscous products
- F17D1/082—Pipe-line systems for liquids or viscous products for cold fluids, e.g. liquefied gas
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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
- F02K9/425—Propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D3/00—Arrangements for supervising or controlling working operations
- F17D3/01—Arrangements for supervising or controlling working operations for controlling, signalling, or supervising the conveyance of a product
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Abstract
The invention relates to a rocket liquid oxygen filling system and a control method, wherein the filling system comprises an on-rod filling pipeline and an on-rod discharging pipeline, the on-rod filling pipeline is arranged along a Z-shaped launching tower swing rod, the front half section of the on-rod discharging pipeline is arranged along the front half section of the launching tower swing rod, and the rear half section of the on-rod discharging pipeline is connected with the rear half section of the launching tower swing rod through a sling; the front end of the filling pipeline on the rod is connected with a filling port of the rocket oxygen tank, the rear end of the filling pipeline on the rod is connected with a filling pipeline on the tower, the filling pipeline on the tower is connected with a ground filling pipeline, a first control valve is arranged on the filling pipeline on the tower, the front end of the discharging pipeline on the rod is connected with a discharging port of the rocket oxygen tank, the rear end of the discharging pipeline on the rod is connected with a discharging pipeline on the tower, and a gas-liquid separator is arranged on the discharging pipeline on the tower; the control method has the advantages of simple flow, safety, reliability and strong fault-tolerant capability.
Description
Technical Field
The invention relates to a rocket low-temperature medium filling device, in particular to a rocket liquid oxygen filling system and a control method.
Background
The liquid oxygen filling is an important component of a low-temperature medium filling system of a carrier rocket, and the main function of the liquid oxygen filling is to carry out precooling, filling and replenishment before injection of a rocket oxygen box in a specified launching procedure in a timely, quantitative and quality-guaranteeing manner. In order to ensure the quality of liquid oxygen and reduce heat leakage of pipelines, valves and pipelines in filling pipelines usually adopt a vacuum multilayer heat insulation form; in order to ensure safety and avoid forming liquid bags, the layout of the filling pipeline generally adopts a step height trend, namely, the elevation of a rocket filling port is higher than the height of a road sign on a pole, the elevation of a pipeline on a tower is higher than the elevation of an external pipeline, and the elevation of a pipeline in a reservoir area is higher; in order to ensure the universality of a launching system, a charging pipeline part on a launching tower is usually arranged in advance, but in order to enable the launching tower to be suitable for a carrier rocket with a relatively low liquid oxygen charging port, a Z-shaped swing rod structure is adopted in the field, and at the moment, if the charging pipeline is arranged in the traditional 'step-by-step height' direction, the charging pipeline on the launching tower needs to be modified, so that the universality of the launching tower is influenced, and the launching efficiency is influenced.
Disclosure of Invention
The invention aims to provide a rocket liquid oxygen filling system and a control method, wherein the system has the advantages of simple structure, low cost, good safety and high reliability, and the method has the advantages of simple flow, safety, reliability and strong fault-tolerant capability.
In order to solve the problems in the prior art, the rocket liquid oxygen filling system provided by the invention comprises an on-rod filling pipeline and an on-rod discharging pipeline, wherein the on-rod filling pipeline is arranged along a Z-shaped launching tower oscillating bar, the front half section of the on-rod discharging pipeline is arranged along the front half section of the launching tower oscillating bar, and the rear half section of the on-rod discharging pipeline is connected with the rear half section of the launching tower oscillating bar through a sling; the front end of a filling pipeline on the rod is connected with a filling port of a rocket oxygen tank through a hose and a filling connector, the rear end of the filling pipeline on the rod is connected with a filling pipeline on a tower with a six-interlayer launching tower through a hose and a flange, the filling pipeline on the tower is connected with a ground filling pipeline, a first control valve is arranged on the filling pipeline on the tower, the front end of a discharge pipeline on the rod is connected with a discharge port of the rocket oxygen tank through a hose and a discharge connector, the rear end of the discharge pipeline on the rod is connected with a discharge pipeline on a tower with a five-interlayer launching tower through a hose and a flange, and a gas-liquid separator is arranged on the discharge pipeline on the tower.
Further, the rocket liquid oxygen filling system is characterized in that a second control valve is arranged on the tower filling pipeline, the tower filling pipeline between the second control valve and the first control valve is connected with an oxygen discharging device through a hot oxygen discharging pipeline, and a third control valve is arranged on the hot oxygen discharging pipeline.
Further, the rocket liquid oxygen filling system is characterized in that a check valve and a butterfly valve are arranged on the tower upper discharge pipeline, the check valve is located on one side, away from the rod upper discharge pipeline, of the gas-liquid separator, and the butterfly valve is located between the gas-liquid separator and the check valve.
Further, the rocket liquid oxygen filling system is characterized in that the ground filling pipeline is connected with a liquid oxygen storage tank, the liquid oxygen storage tank is provided with a supercharger, and the ground filling pipeline is provided with a liquid oxygen pump.
Further, the rocket liquid oxygen filling system is characterized in that a low-temperature filter is arranged on a filling pipeline on the tower, the low-temperature filter is located on one side, opposite to the filling pipeline on the rod, of the second control valve, and the first control valve is located on one side, far away from the filling pipeline on the rod, of the second control valve.
Further, the rocket liquid oxygen filling system is characterized in that a temperature sensor T1 and a pressure sensor P1 are arranged on the filling pipeline on the tower, and a temperature sensor T1 and a pressure sensor P1 are arranged on one side of the filling pipeline on the opposite rod of the low-temperature filter.
Further, the rocket liquid oxygen filling system is characterized in that the tower upper discharge pipeline is correspondingly provided with a temperature sensor T2 and a temperature sensor T3 at two sides of the gas-liquid separator, and the tower upper discharge pipeline is also correspondingly provided with a pressure sensor P2 and a pressure sensor P3 at two sides of the gas-liquid separator.
Further, the rocket liquid oxygen filling system is characterized in that a pressure sensor P4 and a liquid level meter L1 are arranged on the gas-liquid separator.
Further, the rocket liquid oxygen filling system is characterized in that a pressure sensor P5 and a liquid level meter L2 are arranged on the rocket oxygen tank.
The invention provides a control method of the rocket liquid oxygen filling system, which comprises the following steps:
s1, opening the first control valve and the second control valve, and closing the third control valve to enable the liquid oxygen in the liquid oxygen storage tank to flow through the ground filling pipeline, the on-tower filling pipeline and the on-rod filling pipeline in sequence in an extrusion mode to enter the rocket oxygen tank;
s2, when the temperature of the filling pipeline on the tower or the filling pipeline on the rod is lower than a first temperature value, starting the liquid oxygen pump, and when the liquid oxygen in the rocket oxygen tank reaches an initial liquid level, stopping the liquid oxygen pump and closing the second control valve;
s3, when the temperature of the ground filling pipeline is higher than the second temperature value, opening a third control valve to enable the liquid oxygen in the liquid oxygen storage tank to flow through the ground filling pipeline, the tower filling pipeline and the hot oxygen discharge pipeline in sequence in an extrusion mode to enter an oxygen exhaust device; when the temperature of the ground filling pipeline is lower than a third temperature value, closing the third control valve;
s4, before the rocket is launched, opening a second control valve to enable liquid oxygen in the liquid oxygen storage tank to sequentially flow through a ground filling pipeline, an on-tower filling pipeline and an on-rod filling pipeline to enter a rocket oxygen tank in an extrusion mode, and closing the second control valve when the liquid oxygen in the rocket oxygen tank reaches a final liquid level;
and S5, when the rocket is launched, closing the first control valve, opening the second control valve and the third control valve, and enabling the filling connector to be in a pneumatic closing state when the filling connector falls off.
Compared with the prior art, the rocket liquid oxygen filling system and the control method have the following advantages: according to the invention, the on-pole filling pipeline and the on-pole discharging pipeline are arranged, so that the on-pole filling pipeline is arranged along the Z-shaped oscillating bar of the launching tower, the front half section of the on-pole discharging pipeline is arranged along the front half section of the oscillating bar of the launching tower, and the rear half section of the on-pole discharging pipeline is connected with the rear half section of the oscillating bar of the launching tower through the sling; the front end of a filling pipeline on the rod is connected with a filling port of a rocket oxygen tank through a hose and a filling connector, the rear end of the filling pipeline on the rod is connected with a filling pipeline on a tower with six interlayers of a launching tower through a hose and a flange, the filling pipeline on the tower is connected with a ground filling pipeline, a first control valve is arranged on the filling pipeline on the tower, meanwhile, the front end of a discharge pipeline on the rod is connected with a discharge port of the rocket oxygen tank through a hose and a discharge connector, the rear end of the discharge pipeline on the rod is connected with a discharge pipeline on the tower with five interlayers of the launching tower through a hose and a flange, and a gas-liquid separator is arranged on the discharge pipeline on the tower. Therefore, the rocket liquid oxygen filling system with simple structure, low cost, good safety and high reliability is formed. According to the invention, the filling pipeline on the rod is arranged along the Z-shaped oscillating rod of the launching tower, and the inverted U-shaped bent structure is formed by combining the filling pipeline on the tower, compared with the prior art, the 'step-by-step' arrangement mode is changed, on the basis of ensuring the safe filling of liquid oxygen, the filling pipeline on the tower does not need to be changed, the universality of the launching tower is ensured, and the launching efficiency of the rocket is improved; the front half section of the discharge pipeline on the rod is arranged along the front half section of the oscillating bar of the launching tower, the rear half section of the discharge pipeline on the rod is connected with the rear half section of the oscillating bar of the launching tower through the sling, and the discharge pipeline on the rod is connected with the discharge pipeline on the tower, so that oxygen precipitated in the filling pipeline and the rocket oxygen tank can be smoothly discharged, and the safety and the reliability of liquid oxygen filling are ensured. The control method of the rocket liquid oxygen filling system provided by the invention has the advantages of simple flow, safety, reliability and strong fault-tolerant capability.
The following describes a rocket liquid oxygen filling system and a control method in further detail with reference to the specific embodiments shown in the drawings.
Drawings
FIG. 1 is a schematic view of a rocket liquid oxygen injection system of the present invention;
FIG. 2 is a schematic diagram of an on-pole filling line and an on-pole venting line in a rocket liquid oxygen filling system of the present invention.
Detailed Description
First, it should be noted that, the directional terms such as up, down, left, right, front, rear, etc. described in the present invention are only described with reference to the accompanying drawings for easy understanding, and do not limit the technical solution and the claimed scope of the present invention.
Referring to fig. 1 and 2, an embodiment of a rocket liquid oxygen filling system according to the present invention includes an on-stick filling line 1 and an on-stick discharge line 2. The filling pipeline 1 on the rod is arranged along the Z-shaped launching tower swing rod 3, the front half section of the discharging pipeline 2 on the rod is arranged along the front half section of the launching tower swing rod 3, and the rear half section of the discharging pipeline 2 on the rod is connected with the rear half section of the launching tower swing rod 3 through a sling 4. The front end of a filling pipeline 1 on the rod is connected with a filling port of a rocket oxygen tank 5 through a hose and a filling connector, the rear end of the filling pipeline 1 on the rod is connected with a filling pipeline 6 on the tower with an interface arranged on a six-interlayer launching tower through a hose and a flange, the filling pipeline 6 on the tower is connected with a ground filling pipeline (not shown in the figure), and a first control valve 61 is arranged on the filling pipeline 6 on the tower. Meanwhile, the front end of the exhaust pipeline 2 on the rod is connected with the exhaust port of the rocket oxygen tank 5 through a hose and an exhaust connector, the rear end of the exhaust pipeline 2 on the rod is connected with an exhaust pipeline 7 on the launching tower with an interface arranged on the five-interlayer of the launching tower through a hose and a flange, and the exhaust pipeline 7 on the tower is provided with a gas-liquid separator 71.
The rocket liquid oxygen filling system with simple structure, low cost, good safety and high reliability is formed by the structural arrangement. According to the invention, the on-pole filling pipeline 1 is arranged along the Z-shaped swing rod 3 of the launching tower and is combined with the on-tower filling pipeline 6 to form the inverted U-shaped bent structure, compared with the prior art, the 'step-by-step' arrangement mode is changed, on the basis of ensuring the safe filling of liquid oxygen, the on-tower filling pipeline does not need to be changed, the universality of the launching tower is ensured, and the launching efficiency of the rocket is improved; the front half section of the discharge pipeline 2 on the rod is arranged along the front half section of the swing rod 3 of the launching tower, the rear half section of the discharge pipeline 2 on the rod is connected with the rear half section of the swing rod 3 of the launching tower through the sling 4, and the discharge pipeline 2 on the rod is connected with the discharge pipeline 7 on the tower, so that oxygen separated out in the filling pipeline and the rocket oxygen tank 5 can be smoothly discharged, and the safety and the reliability of liquid oxygen filling are ensured. It should be noted that, in practical application, the ground filling pipeline is connected with a liquid oxygen storage tank, the liquid oxygen storage tank is provided with a supercharger, and the ground filling pipeline is provided with a liquid oxygen pump; the launching tower and the launching tower swing link are components of the rocket launching pad, and the structure and arrangement thereof are well known to those skilled in the art and are not described herein again.
Preferably, the second control valve 62 is provided in the upper tower filling line 6, an oxygen discharge device (not shown) is connected to the upper tower filling line 6 between the second control valve 62 and the first control valve 61 via a hot oxygen discharge line 63, and a third control valve 64 is provided in the hot oxygen discharge line 63. The whole liquid oxygen filling process comprises the stages of precooling, large-flow filling, parking, supplementing and the like, wherein the precooling refers to carrying out small-flow liquid oxygen filling on a pipeline and the rocket oxygen tank so as to carry out precooling, the large-flow filling refers to carrying out large-flow liquid oxygen filling on the rocket oxygen tank so as to ensure the quality of liquid oxygen, the parking refers to stopping filling liquid oxygen into the rocket oxygen tank, and the supplementing refers to supplementing liquid oxygen into the rocket oxygen tank before the rocket is launched. According to the invention, the second control valve 62, the hot oxygen discharge pipeline 63 and the third control valve 64 are arranged, in the parking stage, the second control valve 62 is closed, the first control valve 61 and the third control valve 64 are opened, so that the liquid oxygen in the liquid oxygen storage tank sequentially flows through the ground filling pipeline, the tower filling pipeline 6 and the hot oxygen discharge pipeline 63 to enter the oxygen discharge device in an extrusion mode, the filling pipeline before the first control valve 61 can be kept at a relatively low temperature, the liquid oxygen entering the rocket oxygen tank in the pre-injection supplementing stage can meet the temperature requirement, and the safety and reliability are improved. It is noted that the oxygen exhaust apparatus is an existing apparatus, and its structure and arrangement are well known to those skilled in the art. Preferably, the present embodiment provides a check valve 72 and a butterfly valve 73 on the upper column discharge line 7, wherein the check valve 72 is located on the side of the gas-liquid separator 71 away from the upper column discharge line 2, and the butterfly valve 73 is located between the gas-liquid separator 71 and the check valve 72. The invention can separate gas and liquid of the discharged oxygen by arranging the gas-liquid separator 71, can avoid gas backflow by arranging the check valve 72, ensures the quality and the safety and the reliability of the liquid oxygen filling, and conveniently controls the discharge pressure by arranging the butterfly valve.
In this embodiment, the cryogenic filter 65 is disposed in the tower fill line 6, wherein the cryogenic filter 65 is disposed on a side of the second control valve 62 opposite the pole fill line 1, and the first control valve 61 is disposed on a side of the second control valve 62 away from the pole fill line 1. The filled liquid oxygen is filtered through the low-temperature filter 65, so that the quality of the liquid oxygen entering the rocket oxygen box 5 is ensured, and the safety reliability and the practicability are enhanced. In order to detect temperature, pressure and liquid level parameters and improve the convenience and accuracy of control, the temperature sensor T1 and the pressure sensor P1 are arranged on the tower filling pipeline 6, and the temperature sensor T1 and the pressure sensor P1 are positioned on one side of the low-temperature filter 65 opposite to the rod filling pipeline 1; a temperature sensor T2 and a temperature sensor T3 are provided on the upper discharge line 7 of the column on both sides of the gas-liquid separator 71, respectively, and a pressure sensor P2 and a pressure sensor P3 are provided on the upper discharge line 7 of the column on both sides of the gas-liquid separator 71, respectively. Meanwhile, a pressure sensor P4 and a liquid level meter L1 are provided on the gas-liquid separator 71; the rocket oxygen tank 5 is provided with a pressure sensor P5 and a liquid level meter L2.
Based on the same conception, the invention also provides a control method of the rocket liquid oxygen filling system, which comprises the following steps:
s1, opening the first control valve 61 and the second control valve 62, and closing the third control valve 64, so that the liquid oxygen in the liquid oxygen storage tank flows through the ground filling pipeline, the tower filling pipeline 6 and the pole filling pipeline 1 in sequence to enter the rocket oxygen tank 5 in a squeezing mode. Through the step, the precooling of the filling pipeline and the rocket oxygen tank is realized, and the safety and reliability of liquid oxygen filling are ensured.
And S2, when the temperature of the filling pipeline 6 on the tower or the filling pipeline 1 on the rod is lower than a first temperature value, starting the liquid oxygen pump, and when the liquid oxygen in the rocket oxygen tank 5 reaches an initial liquid level, stopping the liquid oxygen pump and closing the second control valve 62. After the pre-cooling stage, the liquid oxygen pump is started to fill the liquid oxygen with large flow, so that the filling efficiency is improved, and the quality of the liquid oxygen can be ensured. According to actual launching requirements, precooling and high-flow filling are generally carried out about 6 hours before launching.
S3, when the temperature of the ground filling pipeline is higher than the second temperature value, opening a third control valve 64 to enable the liquid oxygen in the liquid oxygen storage tank to flow through the ground filling pipeline, the tower filling pipeline 6 and the hot oxygen discharge pipeline 63 in sequence in an extrusion mode to enter an oxygen exhaust device; when the temperature of the surface charging line is below the third temperature value, third control valve 64 is closed. After the high-flow injection, the liquid oxygen enters a liquid oxygen parking stage, the ground injection pipeline can be kept below a second temperature value through the step, the liquid oxygen entering the rocket oxygen tank in the pre-injection supplementing stage is ensured to meet the temperature requirement, and the safety and reliability are improved.
S4, before the rocket is launched, the second control valve 62 is opened, so that the liquid oxygen in the liquid oxygen storage tank sequentially flows through the ground filling pipeline, the tower filling pipeline 6 and the pole filling pipeline 1 to enter the rocket oxygen tank 5 in an extrusion mode, and when the liquid oxygen in the rocket oxygen tank 5 reaches the final liquid level, the second control valve 62 is closed. The liquid oxygen amount in the rocket oxygen tank can be ensured to meet the launching requirement by adding before launching.
When the pre-injection is supplemented, a pipeline (an inverted U-shaped bent part) between the second control valve 62 and the filling connector is in a low-temperature gas state, and because the volume of the pipeline is smaller and far smaller than the pre-injection liquid oxygen supplement amount, the low-temperature gas can enter the rocket oxygen tank 5 under the extrusion pressure action of the liquid oxygen storage tank and can be smoothly discharged through the discharge pipeline 2 on the rod and the discharge pipeline 7 on the tower, and the air blockage phenomenon cannot be generated; and the liquid can be completely discharged before the rocket oxygen tank reaches the final value liquid level, so that no obvious influence on the temperature of the liquid oxygen entering the rocket is caused, and the safety and reliability are ensured.
S5, when the rocket is launched, the first control valve 61 is closed, the second control valve 62 and the third control valve 64 are opened, and the filling connector is in a pneumatic closing state when it is detached. After the liquid is supplemented before injection, liquid accumulation (liquid oxygen) possibly exists in the inverted U-shaped bent pipeline, and during the injection, the filling connector is in a pneumatic closing state, and the filling pipeline 1 on the rod is communicated with the hot oxygen discharge pipeline 63, so that the leakage or the spraying of the liquid oxygen can be effectively avoided, and the safety is enhanced.
It is to be noted that the filling and discharge connectors are prior art, the construction and operation of which are well known to those skilled in the art; the extrusion method is a method of transporting liquid oxygen by the pressure action of a liquid oxygen storage tank. The first temperature value, the second temperature value, the third temperature value, the initial liquid level and the final liquid level are set according to the specific rocket model and the oxygen tank volume, and in practical application, the first temperature value is set to 110K, the second temperature value is set to 84K, and the third temperature value is set to a certain temperature value lower than 84K according to requirements.
The control method of the rocket liquid oxygen filling system provided by the invention passes practical verification, the performance and the index of the control method meet the liquid oxygen filling requirement, and a reliable basis is provided for the design of other low-temperature medium filling pipelines.
The above examples are only for describing the preferred embodiments of the present invention, and do not limit the scope of the claimed invention, and various modifications made by those skilled in the art according to the technical solutions of the present invention should fall within the scope of the invention defined by the claims without departing from the design concept of the present invention.
Claims (10)
1. A rocket liquid oxygen filling system is characterized by comprising an on-rod filling pipeline (1) and an on-rod discharging pipeline (2), wherein the on-rod filling pipeline (1) is arranged along a Z-shaped launching tower swing rod (3), the front half section of the on-rod discharging pipeline (2) is arranged along the front half section of the launching tower swing rod (3), and the rear half section of the on-rod discharging pipeline (2) is connected with the rear half section of the launching tower swing rod (3) through a sling (4); the front end of a filling pipeline (1) on the rod is connected with a filling opening of a rocket oxygen tank (5) through a hose and a filling connector, the rear end of the filling pipeline (1) on the rod is connected with a filling pipeline (6) arranged on a tower of a six-sandwich of a launching tower through a hose and a flange, the filling pipeline (6) on the tower is connected with a ground filling pipeline, a first control valve (61) is arranged on the filling pipeline (6) on the tower, the front end of a discharge pipeline (2) on the rod is connected with a discharge opening of the rocket oxygen tank (5) through a hose and a discharge connector, the rear end of the discharge pipeline (2) on the rod is connected with a discharge pipeline (7) arranged on the tower of a five-sandwich of the launching tower through a hose and a flange, and a gas-liquid separator (71) is arranged on the discharge pipeline (7) on the tower.
2. A rocket liquid oxygen filling system according to claim 1, wherein said tower filling line (6) is provided with a second control valve (62), the tower filling line (6) between the second control valve (62) and the first control valve (61) is connected with an oxygen discharging device through a hot oxygen discharging line (63), and the hot oxygen discharging line (63) is provided with a third control valve (64).
3. A rocket liquid oxygen filling system according to claim 2 wherein said tower drain line (7) is provided with a check valve (72) and a butterfly valve (73), the check valve (72) being located on the side of the gas-liquid separator (71) remote from the rod drain line (2), the butterfly valve (73) being located between the gas-liquid separator (71) and the check valve (72).
4. A rocket liquid oxygen filling system according to claim 3 wherein said ground filling pipe is connected with a liquid oxygen storage tank, said liquid oxygen storage tank is provided with a pressure booster, and said ground filling pipe is provided with a liquid oxygen pump.
5. A rocket liquid oxygen filling system according to claim 4, wherein said tower filling line (6) is provided with a low temperature filter (65), said low temperature filter (65) is located at a side of the second control valve (62) opposite to the pole filling line (1), and said first control valve (61) is located at a side of the second control valve (62) away from the pole filling line (1).
6. A rocket liquid oxygen filling system according to claim 5, wherein said tower filling line (6) is provided with a temperature sensor T1 and a pressure sensor P1, and the temperature sensor T1 and the pressure sensor P1 are located on the side of the cryogenic filter (65) opposite to the rod filling line (1).
7. A rocket liquid oxygen filling system according to claim 4 wherein said tower upper discharge line (7) is provided with temperature sensor T2 and temperature sensor T3 on both sides of gas-liquid separator (71) respectively, and said tower upper discharge line (7) is further provided with pressure sensor P2 and pressure sensor P3 on both sides of gas-liquid separator (71) respectively.
8. A rocket liquid oxygen filling system according to claim 4 wherein said gas-liquid separator (71) is provided with a pressure sensor P4 and a liquid level meter L1.
9. A rocket liquid oxygen filling system according to claim 4 wherein said rocket oxygen tank (5) is equipped with a pressure sensor P5 and a liquid level meter L2.
10. A method of controlling a rocket liquid oxygen filling system as recited in claim 4, comprising the steps of:
s1, opening the first control valve (61) and the second control valve (62), closing the third control valve (64), and enabling the liquid oxygen in the liquid oxygen storage tank to sequentially flow through the ground filling pipeline, the tower filling pipeline (6) and the pole filling pipeline (1) to enter the rocket oxygen tank (5) in a squeezing mode;
s2, when the temperature of the tower charging pipeline (6) or the pole charging pipeline (1) is lower than a first temperature value, starting the liquid oxygen pump, and when the liquid oxygen in the rocket oxygen tank (5) reaches an initial liquid level, stopping the liquid oxygen pump and closing the second control valve (62);
s3, when the temperature of the ground filling pipeline is higher than the second temperature value, opening a third control valve (64) to enable the liquid oxygen in the liquid oxygen storage tank to flow through the ground filling pipeline, the tower filling pipeline (6) and the hot oxygen discharge pipeline (63) in sequence in an extrusion mode to enter an oxygen exhaust device; when the temperature of the ground filling pipeline is lower than a third temperature value, closing a third control valve (64);
s4, before the rocket is launched, opening a second control valve (62), enabling the liquid oxygen in the liquid oxygen storage tank to sequentially flow through a ground filling pipeline, an on-tower filling pipeline (6) and an on-rod filling pipeline (1) to enter a rocket oxygen tank (5) in an extrusion mode, and closing the second control valve (62) when the liquid oxygen in the rocket oxygen tank (5) reaches a final liquid level;
s5, when the rocket is launched, the first control valve (61) is closed, the second control valve (62) and the third control valve (64) are opened, and the filling connector is in a pneumatic closing state when falling off.
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| CN116045110A (en) * | 2022-12-29 | 2023-05-02 | 北京天兵科技有限公司 | Oxygen self-generating pressurizing pipeline adapter, pressurizing system and production method of adapter |
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| RU2225813C2 (en) * | 2002-02-04 | 2004-03-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П.Королева" | Method of filling oxidizer tank of rocket engine plant with liquid oxygen |
| CN105605838A (en) * | 2016-01-07 | 2016-05-25 | 北京航天发射技术研究所 | Carrier rocket liquid oxygen filling system |
| CN111006546A (en) * | 2019-11-05 | 2020-04-14 | 蓝箭航天空间科技股份有限公司 | Rocket erecting arm |
| CN112228765A (en) * | 2020-09-30 | 2021-01-15 | 西安交通大学 | Deep supercooling liquid oxygen filling and controlling system and method in low-temperature rocket launching field |
| CN112539679A (en) * | 2020-12-07 | 2021-03-23 | 北京航天发射技术研究所 | Heavy carrier rocket launching support system and use method |
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