CN112228765B - Deep supercooling liquid oxygen filling and controlling system and method in low-temperature rocket launching field - Google Patents

Deep supercooling liquid oxygen filling and controlling system and method in low-temperature rocket launching field Download PDF

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CN112228765B
CN112228765B CN202011065667.1A CN202011065667A CN112228765B CN 112228765 B CN112228765 B CN 112228765B CN 202011065667 A CN202011065667 A CN 202011065667A CN 112228765 B CN112228765 B CN 112228765B
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liquid oxygen
valve
storage tank
liquid
rocket
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CN112228765A (en
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谢福寿
孙强
夏斯琦
马原
王磊
厉彦忠
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Xian Jiaotong University
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Xian Jiaotong University
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C1/00—Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge
    • F17C1/12—Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge with provision for thermal insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F17C13/02—Special adaptations of indicating, measuring, or monitoring equipment
    • F17C13/025—Special adaptations of indicating, measuring, or monitoring equipment having the pressure as the parameter
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F17C13/02—Special adaptations of indicating, measuring, or monitoring equipment
    • F17C13/026—Special adaptations of indicating, measuring, or monitoring equipment having the temperature as the parameter
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F17C13/04—Arrangement or mounting of valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C5/00—Methods or apparatus for filling containers with liquefied, solidified, or compressed gases under pressures
    • F17C5/02—Methods or apparatus for filling containers with liquefied, solidified, or compressed gases under pressures for filling with liquefied gases
    • F17C5/04—Methods or apparatus for filling containers with liquefied, solidified, or compressed gases under pressures for filling with liquefied gases requiring the use of refrigeration, e.g. filling with helium or hydrogen
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    • F17C6/00—Methods and apparatus for filling vessels not under pressure with liquefied or solidified gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17D—PIPE-LINE SYSTEMS; PIPE-LINES
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    • F17D1/08—Pipe-line systems for liquids or viscous products
    • F17D1/14—Conveying liquids or viscous products by pumping
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    • F17D3/00—Arrangements for supervising or controlling working operations
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    • F17D—PIPE-LINE SYSTEMS; PIPE-LINES
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    • F17D—PIPE-LINE SYSTEMS; PIPE-LINES
    • F17D5/00—Protection or supervision of installations
    • F17D5/005—Protection or supervision of installations of gas pipelines, e.g. alarm
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    • F17C2203/00—Vessel construction, in particular walls or details thereof
    • F17C2203/03—Thermal insulations
    • F17C2203/0304—Thermal insulations by solid means
    • F17C2203/0329—Foam
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    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/01—Pure fluids
    • F17C2221/011—Oxygen
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    • F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
    • F17C2223/01—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the phase
    • F17C2223/0107—Single phase
    • F17C2223/013—Single phase liquid
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    • F17C2225/00—Handled fluid after transfer, i.e. state of fluid after transfer from the vessel
    • F17C2225/01—Handled fluid after transfer, i.e. state of fluid after transfer from the vessel characterised by the phase
    • F17C2225/0107—Single phase
    • F17C2225/013—Single phase liquid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2227/00—Transfer of fluids, i.e. method or means for transferring the fluid; Heat exchange with the fluid
    • F17C2227/01—Propulsion of the fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2227/00—Transfer of fluids, i.e. method or means for transferring the fluid; Heat exchange with the fluid
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    • F17C2227/0135—Pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2227/00—Transfer of fluids, i.e. method or means for transferring the fluid; Heat exchange with the fluid
    • F17C2227/03—Heat exchange with the fluid
    • F17C2227/0337—Heat exchange with the fluid by cooling
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    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2227/00—Transfer of fluids, i.e. method or means for transferring the fluid; Heat exchange with the fluid
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    • F17C2227/0367—Localisation of heat exchange
    • F17C2227/0388—Localisation of heat exchange separate
    • F17C2227/039—Localisation of heat exchange separate on the pipes
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    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2250/00—Accessories; Control means; Indicating, measuring or monitoring of parameters
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    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
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    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
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    • F17C2250/0631—Temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
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    • F17C2250/0689—Methods for controlling or regulating

Abstract

A deep supercooling liquid oxygen filling and control system and method in a low-temperature rocket launching field comprises a ground circulating liquid oxygen storage tank, a negative-pressure liquid nitrogen bath type heat exchanger and a rocket-mounted liquid oxygen storage tank; precooling an arrow storage box by using a combination of saturated liquid nitrogen and low-temperature helium gas before launching, and filling by adopting a large-flow filling mode after meeting the precooling requirement to realize the aim of quick filling; the cold helium gas technology is adopted to dynamically adjust the pressure of the rocket storage tank and maintain the large and supercooled liquid oxygen temperature, and meanwhile, the cold helium gas recycling technology is considered based on the low-temperature liquefaction separation method; the invention realizes the functions of obtaining deep supercooling of liquid oxygen, rapidly filling with large flow, falling off of a filling system in advance, micro-positive pressure adjustment and large supercooling degree maintenance of deep supercooling liquid oxygen of the rocket upper storage tank, cyclic utilization of helium and the like, and can provide effective reference for the deep supercooling of liquid oxygen, the filling process and the control mode of a low-temperature rocket launching field.

Description

Deep supercooling liquid oxygen filling and controlling system and method in low-temperature rocket launching field
Technical Field
The invention relates to the technical field of acquisition and filling of large supercooling degree of liquid oxygen, in particular to a system and a method for filling and controlling deep supercooling liquid oxygen in a low-temperature rocket launching field.
Background
Liquid oxygen is used as the most common low-temperature propellant, has the advantages of no toxicity, no pollution, high specific impulse and the like, is widely used as a propellant in large international carrier rockets at present, and most of the applied liquid oxygen propellant is still at the temperature close to the boiling point in the thermal state at present. In order to further improve the thermodynamic performance of liquid oxygen and increase the effective load of the rocket, supercooling means is often adopted to densify the rocket. The liquid oxygen is supercooled from a normal boiling point state (90K) to a temperature close to a triple point (56K), the density can be obviously improved by 13.8 percent, the obvious cooling of unit volume is increased by 77MJ, and the application value is considerable. From the thermodynamic perspective, the thermodynamic performance of the supercooled liquid oxygen can be obviously improved, but the cases of practical application of the supercooled liquid oxygen to low-temperature rockets as fuel at home and abroad are few, and only the American SpaceX falcon rocket and Soviet Union energy rocket report that 66K supercooled liquid oxygen is adopted as fuel. The three-son-level, 5-long-symbol and 7-long-symbol low-temperature rockets of China Long symbol No. 3 are supercooled by liquid nitrogen only in the supplementing stage, and the temperature of liquid oxygen entering the rockets is kept near 80K, so that the two-phase flow phenomenon in the liquid oxygen filling process is prevented, the fluctuation of a gas-liquid boiling interface is reduced after the liquid oxygen enters the rockets, the liquid level change in the liquid oxygen filling process is effectively controlled, but China has no case of applying full-supercooling liquid oxygen filling; meanwhile, a detailed deep supercooled liquid oxygen filling scheme is not seen in documents published and reported at home and abroad. Therefore, in order to accelerate the application of deep supercooled liquid oxygen in the low-temperature rocket in China, improve the effective load of the rocket and improve the reliability and fault tolerance of the rocket, a set of deep supercooled liquid oxygen rapid filling system and an actual control method need to be developed urgently.
When the normal boiling point liquid oxygen is used as fuel for filling a rocket storage tank in a launching field, the normal boiling point liquid oxygen usually undergoes the processes of precooling, large-flow filling, small-flow automatic replenishment, replenishment before injection and the like. However, for deep subcooled liquid oxygen priming, this set of priming procedures and control methods is completely inapplicable. The application of deep supercooled liquid oxygen at present has two technical difficulties: 1. precooling of the filling pipeline, the engine and the rocket storage tank by the deep supercooled liquid oxygen. When the liquid oxygen with the constant boiling point is filled, saturated liquid oxygen takes away heat of a filling pipeline and solid in the storage box through phase change heat absorption gasification, the temperature is gradually reduced to the state of the liquid oxygen with the constant boiling point, and gasified oxygen is discharged through a pipeline at the top of the storage box. However, for the deep supercooled liquid oxygen, if the filling pipeline, the engine and the rocket tank are precooled by adopting the method, the deep supercooled liquid oxygen can firstly release sensible heat, change from the supercooled state to the saturated state, then release latent heat, and change from the saturated state to the gaseous state. By adopting the precooling mode, after the deep supercooled liquid oxygen is filled into the rocket storage tank, the liquid oxygen with large supercooling degree can absorb the heat capacity of the solid to be greatly reduced, so that the densification of the deep supercooled liquid oxygen cannot be fully utilized. 2. How to always maintain the deep supercooled liquid oxygen storage tank in a micro-positive pressure environment. As is known, the saturation pressure corresponding to the liquid oxygen in the normal boiling point state is 1 atmosphere, so the liquid oxygen in the normal boiling point state is easy to maintain a micro-positive pressure state in the rocket storage tank, but for the deep super-cooled liquid oxygen, for example, the saturation pressure corresponding to the liquid oxygen of 55K is 179Pa, which is a typical negative pressure state, at this time, the external air of 1 atmosphere can easily enter the storage tank to pollute the liquid oxygen, so the solution of the deep super-cooled liquid oxygen negative pressure state is needed to maintain the micro-positive pressure environment all the time.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide a system and a method for filling and controlling deeply supercooled liquid oxygen in a low-temperature rocket launching site, wherein liquid oxygen is cyclically supercooled on the ground by using a negative-pressure liquid nitrogen bath type heat exchanger, a storage tank on a rocket is precooled successively by using the combination of saturated liquid nitrogen and low-temperature helium gas before launching, and after the precooling requirement is met, a large-flow filling mode is adopted for filling, so that the aim of quick filling is fulfilled; the cold helium gas technology is adopted to dynamically adjust the pressure of the rocket storage tank and maintain the large and super-cooled liquid oxygen temperature, and meanwhile, the cold helium gas recycling technology is considered.
In order to achieve the purpose, the invention adopts the following technical scheme:
a deep supercooling liquid oxygen filling and controlling system in a low-temperature rocket launching site comprises a ground circulating liquid oxygen storage tank 3, a negative-pressure liquid nitrogen bath type heat exchanger 17 and a rocket liquid oxygen storage tank 29; an inlet a of a ground circulating liquid oxygen storage tank 3 is connected with a pressurized gas cylinder 1 through a first valve 2, an outlet b of the ground circulating liquid oxygen storage tank 3 is provided with a first safety valve 5, an inlet c of the ground circulating liquid oxygen storage tank 3 is connected with an outlet g of a ground liquid oxygen tank truck 21 through a second valve 6, an outlet e of the ground circulating liquid oxygen storage tank 3 is connected with an inlet j of a negative pressure liquid nitrogen bath type heat exchanger 17 through a third valve 8, a second liquid oxygen pump 11 and an eleventh valve 12, an inlet f of the ground circulating liquid oxygen storage tank 3 is connected with an outlet of a first filter 10 through a first regulating valve 9, the ground circulating liquid oxygen storage tank 3 is connected with a temperature sensor 4, and the temperature sensor 4 is used for controlling the opening degree of the first regulating valve 9;
an outlet d of the ground circulating liquid oxygen storage tank 3 is connected with an inlet of the first flowmeter 40 through a fourth valve 7, a fifth valve 23, a first liquid oxygen pump 24 and a second filter 26, and branches of the fifth valve 23 and the first liquid oxygen pump 24 are connected with a branch of the sixth valve 25 in parallel;
an outlet g of the ground liquid oxygen tank wagon 21 is connected with pipelines between the fourth valve 7, the fifth valve 23 and the sixth valve 25 through a seventh valve 22;
an inlet p of the negative pressure liquid nitrogen bath type heat exchanger 17 is connected with a liquid nitrogen tank wagon 19 through a ninth valve 20, the liquid nitrogen tank wagon 19 is simultaneously connected with an inlet s of the rocket liquid oxygen storage tank 29 through a sixteenth valve 41 and a fourteenth valve 28, an outlet i of the negative pressure liquid nitrogen bath type heat exchanger 17 is connected with an inlet of an evacuating device 15 through an eighth valve 16, an inlet k of the negative pressure liquid nitrogen bath type heat exchanger 17 is connected with an outlet y of a helium storage tank 36 through a tenth valve 37, an outlet m of the negative pressure liquid nitrogen bath type heat exchanger 17 is connected with an inlet of a second flowmeter 13, and an outlet of the second flowmeter 13 is connected with an inlet of a first filter 10; an outlet n of the negative pressure liquid nitrogen bath type heat exchanger 17 is connected with an inlet of the gas-liquid separator 18, and the negative pressure liquid nitrogen bath type heat exchanger 17 is provided with a second safety valve 14;
an inlet t of the rocket-mounted liquid oxygen storage tank 29 is connected with a gas outlet of the gas-liquid separator 18 through a second regulating valve 30, an outlet v of the rocket-mounted liquid oxygen storage tank 29 is connected with an inlet of a compressor 34 through a third regulating valve 32, a pipeline between the third regulating valve 32 and the inlet of the compressor 34 is communicated with the atmosphere through a fifteenth valve 38, an outlet of the compressor 34 is connected with an inlet w of a helium storage tank 36 through a tenth valve 35, an inlet u of the rocket-mounted liquid oxygen storage tank 29 is connected with a pressure sensor 31, and the pressure sensor 31 controls the second regulating valve 30 and the third regulating valve 32 to be opened and closed; an inlet s of the supraarrow liquid oxygen storage tank 29 is connected with an outlet of the first flowmeter 40 through a fourteenth valve 28; an inlet r of the supraarrow liquid oxygen storage tank 29 is connected with a gas outlet of the gas-liquid separator 18 through a tenth valve 27; the rocket-borne liquid oxygen storage tank 29 is provided with a liquid level sensor 39, and the rocket-borne liquid oxygen storage tank 29 is provided with a third safety valve 33.
The connecting pipelines are high-vacuum multilayer heat insulation or polyurethane foaming heat insulation.
The first valve 2 is a normal temperature regulating valve.
The second valve 6, the third valve 8, the fourth valve 7, the fifth valve 23, the sixth valve 25, the seventh valve 22, the eighth valve 16, the ninth valve 20, the tenth valve 37, the eleventh valve 12, the twelfth valve 35, the thirteenth valve 27, the fourteenth valve 28, the fifteenth valve 38 and the sixteenth valve 41 are low-temperature stop valves.
The first regulating valve 9, the second regulating valve 30 and the third regulating valve 32 are low-temperature regulating valves.
The first safety valve 5, the second safety valve 14 and the third safety valve 33 are low-temperature safety angle valves.
The first liquid oxygen pump 24 and the second liquid oxygen pump 11 are low-temperature liquid pumps.
The first filter 10 and the second filter 26 are low-temperature fluid filters.
The first flowmeter 40 and the second flowmeter 13 are liquid flowmeters.
The gas-liquid separator 18 is a low-temperature gas-liquid separator.
The evacuating device 15 is a vacuum pump or an ejector with a rewarming device or a low-temperature vacuum pump without a rewarming device.
The pressurized gas cylinder 1 is a high-pressure helium cylinder.
The ground circulating liquid oxygen storage tank 3 is a high-vacuum multilayer heat-insulation low-temperature storage tank.
The negative pressure liquid nitrogen bath type heat exchanger 17 is a low temperature negative pressure air bath type heat exchanger, and the working medium is liquid nitrogen or liquid oxygen.
The rocket liquid oxygen storage tank 29 is a low-temperature storage tank or storage tank made of foam materials and insulated by heat.
The helium storage tank 36 is a low-temperature gas storage tank.
A method for utilizing a deep supercooling liquid oxygen filling and control system in a low-temperature rocket launching field comprises the following steps:
the first step is as follows: surface cycle subcooling to obtain subcooled liquid oxygen: opening a ninth valve 20, and injecting saturated liquid nitrogen under normal pressure from a liquid nitrogen tank wagon 19 into the shell side of the negative pressure liquid nitrogen bath type heat exchanger 17; opening an eighth valve 16, starting an evacuating device 15, evacuating and supercooling liquid nitrogen on the shell side of a negative pressure liquid nitrogen bath type heat exchanger 17 to reach a 64K temperature zone; working medium or liquid oxygen, and the liquid oxygen can be reduced to a 56K temperature zone through evacuation;
opening the second valve 6, and injecting saturated liquid oxygen under normal pressure into the ground circulating liquid oxygen storage tank 3 from the liquid oxygen tank wagon 21, wherein the temperature of the saturated liquid oxygen under normal pressure is 90.188K; the first regulating valve 9 is controlled by a signal of the temperature sensor 4, and the temperature sensor 4 monitors the liquid oxygen temperature in the ground circulating liquid oxygen storage tank 3 so as to regulate the liquid oxygen flow in the circulating loop and control the cold input into the ground circulating liquid oxygen storage tank 3; opening a third valve 8 and an eleventh valve 12, controlling a first regulating valve 9 to be opened by a temperature sensor 4, obtaining cold quantity by the liquid oxygen in the ground circulating liquid oxygen storage tank 3 through a negative pressure liquid nitrogen bath type heat exchanger 17, returning the liquid oxygen to the ground circulating liquid oxygen storage tank 3 after passing through a second flowmeter 13 and a first filter 10, mixing the liquid oxygen with the liquid oxygen in the ground circulating liquid oxygen storage tank 3, reducing the temperature of the liquid oxygen, and finally obtaining 66K of supercooled liquid oxygen in the ground liquid oxygen storage tank 3; if the working medium in the negative pressure liquid nitrogen bath type heat exchanger 17 is liquid oxygen, 56K of deep super-cooled liquid oxygen can be obtained in the ground circulating liquid oxygen storage tank 3;
and step two, gradually precooling the liquid oxygen storage tank 29 on the arrow: firstly, opening a sixteenth valve 41 and a fourteenth valve 28, enabling saturated liquid nitrogen to enter an arrow liquid oxygen storage tank 29, performing preliminary precooling on a filling pipeline and an arrow liquid oxygen storage tank 29, precooling the arrow liquid oxygen storage tank 29 to a 78K temperature zone through the preliminary precooling, and closing the sixteenth valve 41 and the fourteenth valve 28 after the preliminary precooling is completed;
opening a tenth valve 37 and a tenth valve 27, enabling helium in a helium storage tank 36 to obtain cold energy through a negative pressure liquid nitrogen bath type heat exchanger 17, enabling the cold energy to enter an arrow-top liquid oxygen storage tank 29 through a gas-liquid separator 18 from an inlet r, further pre-cooling a filling pipeline and the arrow-top liquid oxygen storage tank 29, pre-cooling the arrow-top liquid oxygen storage tank 29 to a 66K temperature zone, and if a working medium of the negative pressure liquid nitrogen bath type heat exchanger 17 is liquid oxygen, reducing the liquid oxygen to a 56K temperature zone through evacuation; helium from the overhead liquid oxygen storage tank 29 returns to a helium storage tank 36 through a third regulating valve 32, a compressor 34 and a twelfth valve 35 for circulation;
thirdly, carrying out rocket filling on the supercooled liquid oxygen: after precooling is finished, opening the first valve 2, the fourth valve 7, the sixth valve 25 and the fourteenth valve 28, closing the fifth valve 23, closing the first liquid oxygen pump 24, filling the supercooled liquid oxygen in the ground circulating liquid oxygen storage tank 3 into the rocket liquid oxygen storage tank 29 through the fourth valve 7, the sixth valve 25, the second filter 26, the first liquid oxygen pump 40 and the fourteenth valve 28 under the pressurization of the pressurization gas cylinder 1, and realizing extrusion filling; closing the sixth valve 25, opening the fifth valve 23, and starting the first liquid oxygen pump 24 to realize pumping type large-flow filling;
in the filling process, when the second regulating valve 30 is opened, the low-temperature helium gas passing through the gas-liquid separator 18 dynamically pressurizes the rocket liquid oxygen storage tank 29; when the third regulating valve 32 and the twelfth valve 35 are opened, the fifteenth valve 38 is closed, and the compressor 34 is started, the pressure of the on-arrow liquid oxygen storage tank 29 is controlled; the pressure sensor 31 controls the opening degree of the second regulating valve 30 and the third regulating valve 32, so that the pressure of the rocket-borne liquid oxygen storage tank 29 is regulated, and the micro-positive pressure in the rocket-borne liquid oxygen storage tank 29 is ensured;
the liquid level sensor 39 monitors the liquid level in the liquid oxygen storage tank 29 on the arrow, the filling is completed when the set liquid level is reached, and the fourth valve 7 and the first liquid oxygen pump 24 are closed after the filling is completed;
fourthly, the supercooling degree of the liquid oxygen in the liquid oxygen storage tank 29 on the arrow is maintained: opening a tenth valve 37, a tenth valve 27 and a twelfth valve 35, closing a fifteenth valve 38, controlling the opening degree of a third regulating valve 32 by a pressure sensor 31, starting a compressor 34, obtaining cold energy from helium in a helium storage tank 36 through a negative pressure liquid nitrogen bath type heat exchanger 17, injecting the cold energy into the rocket-mounted liquid oxygen storage tank 29 through an inlet r through a gas-liquid separator 18, realizing concentration difference supercooling through the pressure difference between the oxygen partial pressure in a helium bubble and the oxygen partial pressure in liquid oxygen, and maintaining the supercooling degree of the deep supercooled liquid oxygen in the rocket-mounted liquid oxygen storage tank 29; the helium-oxygen mixed gas returns to a helium storage tank 36 through a third regulating valve 32, a compressor 34 and a twelfth valve 35;
in the helium storage tank 36, the helium-oxygen mixture passes through the negative pressure liquid nitrogen bath type heat exchanger 17 due to different boiling point temperatures, the oxygen is liquefied again and separated in the gas-liquid separator 18, the liquid oxygen returns to the ground circulating liquid oxygen storage tank 3, and the pure low-temperature helium enters the rocket-mounted liquid oxygen storage tank 29 again to control the air pillow pressure and maintain the large supercooling degree of the deep supercooled liquid oxygen.
In the third step, the rocket liquid oxygen storage tank 29 is filled, the seventh valve 22, the gas-liquid separator 26 and the fourteenth valve 28 are opened through the liquid oxygen tank wagon 21, the fifth valve 23 and the first liquid oxygen pump 24 are started, and the pump-type large-flow filling function of the liquid oxygen with the normal boiling point at the current stage is realized; and starting the sixth valve 25 to realize the extrusion filling function of the normal boiling point liquid oxygen at the current stage.
The invention has the beneficial effects that:
the conventional supercooling-while-filling method has very high requirements on a subcooler, particularly the heat load requirement of a heat exchanger is very high, and if the liquid oxygen at the outlet of the heat exchanger reaches the target supercooling degree, the designed heat exchanger has larger volume and the whole system has poor maneuverability; meanwhile, the supercooling degree of the rocket storage tank can not be maintained by supercooling and filling at the same time, all propellants need to be discharged back to the ground storage tank if the rocket is delayed to launch after filling, the temperature of discharged liquid oxygen is different along with the delay time, and the load matching is difficult to realize during secondary supercooling; and the rapid filling cannot be realized while the filling is carried out under the supercooling condition.
In order to maintain the degree of supercooling of liquid oxygen after filling of the rocket storage tank, a scheme of firstly filling and then supercooling of cyclic supercooling is implemented on the rocket storage tank, however, the scheme needs to open the rocket storage tank unnecessarily, the original structure of the rocket storage tank is damaged, and the rocket storage tank can generate a negative pressure state due to the cyclic supercooling of the rocket storage tank, so that adverse effects are caused.
The invention provides a flow scheme and a filling sequence control mode for circularly supercooling liquid oxygen in a ground storage tank in combination with various conditions which can actually occur in a low-temperature rocket launching site, and performing large-flow quick filling on the premise that the low-temperature rocket needs to be launched, and has a supercooling degree maintaining function and a helium circulating recycling function during the parking period of deeply supercooled liquid oxygen in a rocket storage tank. The scheme of supercooling before filling can effectively overcome the defects of the two schemes (filling while supercooling and filling before supercooling).
Firstly, circulation supercooling is completed on the ground, the supercooling degree of the liquid oxygen in the ground circulation liquid oxygen storage tank 3 is not lost along with the prolonging of the parking time, the rapid filling can be completed in the expected filling time, only the heat insulation problem needs to be considered in the filling process, and the load matching of the heat exchanger does not need to be considered.
Secondly, the ground circulating liquid oxygen storage tank 3 does not need to be launched along with a carrier rocket, so that the limitation of volume and mass is not caused, and heat insulation measures and sealing measures can be better compared with the rocket-mounted liquid oxygen storage tank 29, so that the negative pressure stage which is difficult to avoid in the liquid oxygen supercooling stage is effectively overcome, the liquid oxygen pollution risk is reduced, and the risk of insufficient pressure bearing capacity of the storage tank is overcome.
The helium circulation loop is added again, so that the control of the whole system is more complete, and in the precooling stage, equipment such as a filling pipeline, an engine, an on-arrow liquid oxygen storage tank 29 and the like are precooled to a required temperature area by using low-temperature helium gas, and then deep supercooled liquid oxygen is filled; after filling, the difference between the oxygen partial pressure in helium bubbles and the oxygen partial pressure in liquid oxygen by injecting insoluble gas helium forms a concentration difference supercooling effect, and the supercooling degree in the liquid oxygen storage tank 29 on the rocket after filling is maintained; meanwhile, helium is injected from the top of the rocket-borne liquid oxygen storage tank 29, so that the effect of PID control and regulation on the air pillow pressure in the rocket-borne liquid oxygen storage tank 29 is achieved, the micro-positive pressure environment of the rocket-borne liquid oxygen storage tank 29 is maintained, and liquid oxygen pollution is avoided;
the deep supercooled liquid oxygen filling can directly avoid the technical problems that the fluctuation of a gas-liquid interface of the liquid oxygen storage tank 29 on an arrow is severe and the measurement of a liquid level meter is inaccurate when the normal boiling point liquid oxygen is filled. Because the liquid level of the liquid oxygen storage tank 29 on the arrow is not accurately measured, the constant boiling point liquid oxygen needs to be automatically supplemented with small flow after being filled to a certain liquid level by adopting large flow, so that the excessive filling of the liquid oxygen is prevented, the filling speed is reduced, the filling time is prolonged, and the problem can be avoided, so that the rapid filling is realized.
Finally, the invention also omits two processes of automatic replenishment and replenishment before injection of the liquid oxygen filling at the present stage, so that the low-temperature launching field filling system can fall off in advance. Compared with the scheme that the filling pipeline is separated from the rocket liquid oxygen storage tank only a few minutes before launching at the present stage, the method can control the separation-ahead time to be 60 minutes. The early falling provides sufficient checking and debugging time allowance, reduces the influence of accidents on launch of the carrier rocket, and improves the overall reliability of the rocket launching system.
Meanwhile, the invention considers the current situation that saturated liquid oxygen is still applied in a large scale at the present stage, can be simultaneously used for two situations of saturated liquid oxygen filling and supercooled liquid oxygen filling, and provides a powerful reference value for the transformation of the transmitting field.
Drawings
Fig. 1 is a schematic structural diagram of an embodiment of the present invention.
Detailed Description
The technical solution of the present invention is further explained with reference to the drawings and the embodiments.
Referring to fig. 1, a deep supercooled liquid oxygen filling and control system in a low-temperature rocket launching site comprises a ground circulating liquid oxygen storage tank 3, a negative-pressure liquid nitrogen bath type heat exchanger 17 and a rocket liquid oxygen storage tank 29; an inlet a of the ground circulating liquid oxygen storage tank 3 is connected with a pressurized gas cylinder 1 through a first valve 2, and when the first valve 2 is opened, pressurized gas pressurizes the ground circulating liquid oxygen storage tank 3; a first safety valve 5 is arranged at an outlet b of the ground circulating liquid oxygen storage tank 3 to prevent the ground circulating liquid oxygen storage tank 3 from being over-pressurized; an inlet c of the ground circulating liquid oxygen storage tank 3 is connected with an outlet g of the ground liquid oxygen tank wagon 21 through a second valve 6, and when a sixth valve is opened, saturated liquid oxygen in the ground liquid oxygen tank wagon 21 is injected into the ground circulating liquid oxygen storage tank 3; an outlet e of the ground circulating liquid oxygen storage tank 3 is connected with an inlet j of the negative pressure liquid nitrogen bath type heat exchanger 17 through a third valve 8, a second liquid oxygen pump 11 and an eleventh valve 12, an inlet f of the ground circulating liquid oxygen storage tank 3 is connected with an outlet of the first filter 10 through a first regulating valve 9, the ground circulating liquid oxygen storage tank 3 is connected with a temperature sensor 4, and the temperature sensor 4 is used for controlling the opening degree of the first regulating valve 9;
an outlet d of the ground circulating liquid oxygen storage tank 3 is connected with an inlet of the first flowmeter 40 through a fourth valve 7, a fifth valve 23, a first liquid oxygen pump 24 and a second filter 26, and branches of the fifth valve 23 and the first liquid oxygen pump 24 are connected with a branch of the sixth valve 25 in parallel;
an outlet g of the ground liquid oxygen tank wagon 21 is connected with pipelines between the fourth valve 7, the fifth valve 23 and the sixth valve 25 through a seventh valve 22;
an inlet p of the negative pressure liquid nitrogen bath type heat exchanger 17 is connected with a liquid nitrogen tank wagon 19 through a ninth valve 20, and when the ninth valve 20 is opened, saturated liquid nitrogen in the liquid nitrogen tank wagon 19 is injected into the shell side of the negative pressure liquid nitrogen bath type heat exchanger 17; the liquid nitrogen tank wagon is simultaneously connected with an inlet s of the liquid oxygen storage tank 29 on the arrow through a sixteenth valve 41 and a fourteenth valve 28, so that a precooling effect is achieved; an outlet i of the negative pressure liquid nitrogen bath type heat exchanger 17 is connected with an inlet of an evacuating device 15 through an eighth valve 16, when the eighth valve 16 is opened, the evacuating device 15 is started to evacuate and decompress shell side liquid nitrogen of the negative pressure liquid nitrogen bath type heat exchanger 17, and supercooled liquid nitrogen is prepared; an inlet k of the negative pressure liquid nitrogen bath type heat exchanger 17 is connected with an outlet y of the helium storage tank 36 through a tenth valve 37, and a helium pipeline is reduced to the same temperature as the supercooled liquid oxygen through the negative pressure liquid nitrogen bath type heat exchanger 17; an outlet m of the negative pressure liquid nitrogen bath type heat exchanger 17 is connected with an inlet of a second flowmeter 13, and an outlet of the second flowmeter 13 is connected with an inlet of the first filter 10; when the third valve 8 and the eleventh valve 12 are opened, the second liquid oxygen pump 11 is started, and the first filter 10 is started, liquid oxygen flows from the outlet e of the ground circulating liquid oxygen storage tank 3 through the third valve 8, the second liquid oxygen pump 11, the eleventh valve 12, the negative pressure liquid nitrogen bath type heat exchanger 17, the second flow meter 13, the first filter 10 and the first regulating valve 9 and returns to the ground circulating liquid oxygen storage tank 3 from the inlet f, so that the purpose of obtaining the deep super-cooled liquid oxygen is achieved; the temperature sensor 4 controls the first regulating valve 9 to regulate the liquid oxygen flow of the circulation loop and control the excessive cooling capacity;
an outlet n of the negative pressure liquid nitrogen bath type heat exchanger 17 is connected with an inlet of a gas-liquid separator 18, oxygen and helium in the pipeline are separated, liquid oxygen is recovered, and insoluble gas helium gas continuously circulates in the pipeline; the negative pressure liquid nitrogen bath type heat exchanger 17 is provided with a second safety valve 14 to prevent the negative pressure liquid nitrogen bath type heat exchanger 17 from being over-pressurized;
an inlet t of the rocket-borne liquid oxygen storage tank 29 is connected with a gas outlet of the gas-liquid separator 18 through a second regulating valve 30, and when the second regulating valve 30 is opened, the rocket-borne liquid oxygen storage tank 29 is pressurized by low-temperature helium gas obtained after liquid oxygen is separated by the gas-liquid separator 18; an outlet v of the rocket-mounted liquid oxygen storage tank 29 is connected with an inlet of a compressor 34 through a third regulating valve 32, a pipeline between the third regulating valve 32 and the inlet of the compressor 34 is communicated with the atmosphere through a fifteenth valve 38, an outlet of the compressor 34 is connected with an inlet w of a helium storage tank 36 through a tenth valve 35, the third regulating valve 32 and the twelfth valve 35 are opened, the fifteenth valve 38 is closed, and when the compressor 34 is started, the air pillow pressure of the rocket-mounted liquid oxygen storage tank 29 is controlled to maintain a certain pressure; the inlet u of the rocket liquid oxygen storage tank 29 is connected with a pressure sensor 31, the pressure sensor 31 controls the opening and closing of a second regulating valve 30 and a third regulating valve 32, the pressure control of the rocket liquid oxygen storage tank 29 is realized, and the micro-positive pressure in the rocket liquid oxygen storage tank 29 is maintained;
an inlet s of the rocket-mounted liquid oxygen storage tank 29 is connected with an outlet of the first flow meter 40 through the fourteenth valve 28, when the fourth valve 7, the fifth valve 23 and the fourteenth valve 28 are opened, the sixth valve 25 is closed, the first liquid oxygen pump 24 is started, and liquid oxygen after supercooling in the ground circulating liquid oxygen storage tank 3 is filled into the rocket-mounted liquid oxygen storage tank 29 through the fourth valve 7, the fifth valve 23, the first liquid oxygen pump 24, the second filter 26, the first flow meter 40 and the fourteenth valve 28 and enters a pump-pressure large-flow filling stage; when the fourth valve 7, the sixth valve 25 and the fourteenth valve 28 are opened and the fifth valve 23 is closed, the liquid oxygen after the supercooling in the ground circulating liquid oxygen storage tank 3 is filled into the rocket-mounted liquid oxygen storage tank 29 through the fourth valve 7, the sixth valve 25, the second filter 26, the first flow meter 40 and the fourteenth valve 28, so that the extrusion filling function is realized;
an inlet r of the rocket-borne liquid oxygen storage tank 29 is connected with a gas outlet of the gas-liquid separator 18 through a tenth three-valve 27, when the tenth three-valve 27 is opened, low-temperature helium gas after gas-liquid separation is injected into the rocket-borne liquid oxygen storage tank 29, and the rocket-borne liquid oxygen storage tank is used for precooling to a required temperature zone in a precooling stage; after the filling is finished, the supercooling degree of the deep supercooled liquid oxygen in the rocket-mounted liquid oxygen storage tank 29 and the micro-positive pressure environment of an air pillow area are maintained;
the rocket liquid oxygen storage tank 29 is provided with a liquid level sensor 39 for monitoring the liquid level of the rocket liquid oxygen storage tank 29; the rocket-borne liquid oxygen storage tank 29 is provided with a third safety valve 33 to prevent the rocket-borne liquid oxygen storage tank 29 from being over-pressurized.
The connecting pipelines are high-vacuum multilayer heat insulation or polyurethane foaming heat insulation.
The first valve 2 is a normal temperature regulating valve.
The second valve 6, the third valve 8, the fourth valve 7, the fifth valve 23, the sixth valve 25, the seventh valve 22, the eighth valve 16, the ninth valve 20, the tenth valve 37, the eleventh valve 12, the twelfth valve 35, the thirteenth valve 27, the fourteenth valve 28, the fifteenth valve 38 and the sixteenth valve 41 are low-temperature stop valves.
The first regulating valve 9, the second regulating valve 30 and the third regulating valve 32 are low-temperature regulating valves.
The first safety valve 5, the second safety valve 14 and the third safety valve 33 are low-temperature safety angle valves.
The first liquid oxygen pump 24 and the second liquid oxygen pump 11 are low-temperature liquid pumps.
The first filter 10 and the second filter 26 are low-temperature fluid filters.
The first flowmeter 40 and the second flowmeter 13 are liquid flowmeters.
The gas-liquid separator 18 is a low-temperature gas-liquid separator.
The evacuating device 15 is a vacuum pump or an ejector with a rewarming device or a low-temperature vacuum pump without a rewarming device.
The pressurized gas cylinder 1 is a high-pressure helium cylinder.
The ground circulating liquid oxygen storage tank 3 is a high-vacuum multilayer heat-insulation low-temperature storage tank.
The negative pressure liquid nitrogen bath type heat exchanger 17 is a low temperature negative pressure air bath type heat exchanger, and the working medium is liquid nitrogen or liquid oxygen.
The rocket liquid oxygen storage tank 29 is a low-temperature storage tank or storage tank made of foam materials and insulated by heat.
The helium storage tank 36 is a low-temperature gas storage tank.
A method for utilizing a deep supercooling liquid oxygen filling and control system in a low-temperature rocket launching field comprises the following steps:
first, surface cycle subcooling to obtain subcooled liquid oxygen: opening a ninth valve 20, and injecting saturated liquid nitrogen under normal pressure from a liquid nitrogen tank wagon 19 into the shell side of the negative pressure liquid nitrogen bath type heat exchanger 17; opening an eighth valve 16, starting an evacuating device 15, evacuating and supercooling liquid nitrogen on the shell side of a negative pressure liquid nitrogen bath type heat exchanger 17 to reach a 64K temperature zone; the working medium can also be liquid oxygen, and the liquid oxygen can be reduced to a 56K temperature zone through evacuation;
opening the second valve 6, and injecting saturated liquid oxygen under normal pressure into the ground circulating liquid oxygen storage tank 3 from the liquid oxygen tank wagon 21, wherein the temperature of the saturated liquid oxygen under normal pressure is 90.188K; the first regulating valve 9 is controlled by a signal of the temperature sensor 4, and the temperature sensor 4 monitors the liquid oxygen temperature in the ground circulating liquid oxygen storage tank 3 so as to regulate the liquid oxygen flow in the circulating loop and control the cold input into the ground circulating liquid oxygen storage tank 3; opening a third valve 8 and an eleventh valve 12, controlling a first regulating valve 9 to be opened by a temperature sensor 4, obtaining cold quantity by the liquid oxygen in the ground circulating liquid oxygen storage tank 3 through a negative pressure liquid nitrogen bath type heat exchanger 17, returning the liquid oxygen to the ground circulating liquid oxygen storage tank 3 after passing through a second flowmeter 13 and a first filter 10, mixing the liquid oxygen with the liquid oxygen in the ground circulating liquid oxygen storage tank 3, reducing the temperature of the liquid oxygen, achieving the purpose of circulating supercooling, and finally obtaining 66K supercooled liquid oxygen in the ground liquid oxygen storage tank 3; if the working medium in the negative pressure liquid nitrogen bath type heat exchanger 17 is liquid oxygen, 56K of deep super-cooled liquid oxygen can be obtained in the ground circulating liquid oxygen storage tank 3;
and step two, gradually precooling the liquid oxygen storage tank 29 on the arrow: firstly, opening a sixteenth valve 41 and a fourteenth valve 28, enabling saturated liquid nitrogen to enter an arrow liquid oxygen storage tank 29, performing preliminary precooling on a filling pipeline, the arrow liquid oxygen storage tank 29 and other equipment, wherein the preliminary precooling can precool the arrow liquid oxygen storage tank 29 to a 78K temperature zone, and closing the sixteenth valve 41 and the fourteenth valve 28 after the preliminary precooling is completed;
opening a tenth valve 37 and a tenth valve 27, obtaining cold energy from helium in a helium storage tank 36 through a negative pressure liquid nitrogen bath type heat exchanger 17, enabling the cold energy to enter an arrow-top liquid oxygen storage tank 29 through a gas-liquid separator 18 from an inlet r, further precooling equipment such as a filling pipeline and the arrow-top liquid oxygen storage tank 29, wherein the arrow-top liquid oxygen storage tank 29 can be precooled to a 66K temperature zone through the further precooling, and if a working medium of the negative pressure liquid nitrogen bath type heat exchanger 17 is liquid oxygen, the liquid oxygen can be reduced to a 56K temperature zone through evacuation, and the arrow-top liquid oxygen storage tank 29 can be precooled to a 56K temperature zone; helium from the overhead liquid oxygen storage tank 29 returns to a helium storage tank 36 through a third regulating valve 32, a compressor 34 and a twelfth valve 35 for circulation;
thirdly, carrying out rocket filling on the supercooled liquid oxygen: after the second step of precooling is completed, opening the first valve 2, the fourth valve 7, the sixth valve 25 and the fourteenth valve 28, closing the fifth valve 23, closing the first liquid oxygen pump 24, filling the supercooled liquid oxygen in the ground circulating liquid oxygen storage tank 3 into the rocket-mounted liquid oxygen storage tank 29 through the fourth valve 7, the sixth valve 25, the second filter 26, the first liquid oxygen pump 40 and the fourteenth valve 28 under the pressurization of the pressurization gas cylinder 1, and realizing extrusion filling; the sixth valve 25 is closed, the fifth valve 23 is opened, and the first liquid oxygen pump 24 is started, so that pumping type large-flow filling can be realized;
in the filling process, when the second regulating valve 30 is opened, the low-temperature helium gas passing through the gas-liquid separator 18 dynamically pressurizes the rocket liquid oxygen storage tank 29; when the third regulating valve 32 and the twelfth valve 35 are opened, the fifteenth valve 38 is closed, and the compressor 34 is started, the pressure of the on-arrow liquid oxygen storage tank 29 is controlled; the pressure sensor 31 controls the opening degree of the second regulating valve 30 and the third regulating valve 32, so that the pressure of the rocket-borne liquid oxygen storage tank 29 is regulated, and the micro-positive pressure in the rocket-borne liquid oxygen storage tank 29 is ensured;
the liquid level sensor 39 monitors the liquid level in the liquid oxygen storage tank 29 on the arrow, the filling is completed when the set liquid level is reached, and the fourth valve 7 and the first liquid oxygen pump 24 are closed after the filling is completed;
fourthly, the supercooling degree of the liquid oxygen in the liquid oxygen storage tank 29 on the arrow is maintained: opening a tenth valve 37, a tenth valve 27 and a twelfth valve 35, closing a fifteenth valve 38, controlling the opening degree of a third regulating valve 32 by a pressure sensor 31, starting a compressor 34, obtaining cold energy from helium in a helium storage tank 36 through a negative pressure liquid nitrogen bath type heat exchanger 17, injecting the cold energy into the rocket-mounted liquid oxygen storage tank 29 through an inlet r through a gas-liquid separator 18, realizing concentration difference supercooling through the pressure difference between the oxygen partial pressure in a helium bubble and the oxygen partial pressure in liquid oxygen, and maintaining the supercooling degree of the deep supercooled liquid oxygen in the rocket-mounted liquid oxygen storage tank 29; the helium-oxygen mixed gas returns to a helium storage tank 36 through a third regulating valve 32, a compressor 34 and a twelfth valve 35;
in the helium storage tank 36, the helium-oxygen mixture passes through the negative pressure liquid nitrogen bath type heat exchanger 17 due to different boiling point temperatures, the oxygen is liquefied again and separated in the gas-liquid separator 18, the liquid oxygen returns to the ground circulating liquid oxygen storage tank 3, and the pure low-temperature helium enters the rocket-mounted liquid oxygen storage tank 29 again to control the air pillow pressure and maintain the large supercooling degree of the deep supercooled liquid oxygen.
In the third step, the liquid oxygen storage tank 29 on the arrow is filled, and the seventh valve 22, the gas-liquid separator 26 and the fourteenth valve 28 are opened through the liquid oxygen tank wagon 21, and the fifth valve 23 and the first liquid oxygen pump 24 are started, so that the pumping type large-flow filling function of the liquid oxygen with the normal boiling point at the current stage is realized; and starting the sixth valve 25 to realize the extrusion filling function of the normal boiling point liquid oxygen at the current stage.
The invention provides a set of practical and feasible liquid oxygen deep supercooling and filling system and method for a launching field, and explains a detailed flow and a control mode. Through the analysis of the principle, the invention has the advantages that: load matching of the heat exchanger is not required to be considered, the design difficulty of the heat exchanger is reduced, and the overall volume and mass of the heat exchanger are also reduced; the helium is skillfully applied, so that the pressure in the storage tank can be adjusted, the supercooling degree of liquid oxygen in the storage tank on the rocket can be maintained, the emission delay time is effectively prolonged, the waste of helium can be reduced by the arranged helium circulation loop, and the helium can be recycled; the supercooling degree of the supercooled liquid oxygen can be maintained for a long time by a helium bubbling method; fourthly, after the deep supercooled liquid oxygen is firstly obtained on the ground, the aim of quickly filling the deep supercooled liquid oxygen in a large flow can be achieved; and fifthly, the replenishing stage of the conventional normal boiling point liquid oxygen filling system is cancelled, the filling system can fall off in advance, sufficient inspection and debugging time is provided, and the influence of accidents on launch of the carrier rocket is reduced. Meanwhile, the system is also suitable for filling saturated liquid oxygen and can be used for rocket launching sites using normal boiling point liquid oxygen as a boosting agent at the present stage.
The foregoing embodiments are merely illustrative of the principles and features of this invention, and the invention is not limited to the above embodiments, but rather, various changes and modifications can be made without departing from the spirit and scope of the invention, and all changes and modifications that can be directly derived or suggested to one skilled in the art from the disclosure of this invention are to be considered as within the scope of the invention.

Claims (10)

1. A deep supercooling liquid oxygen filling and controlling system in a low-temperature rocket launching site is characterized in that: comprises a ground circulating liquid oxygen storage tank (3), a negative pressure liquid nitrogen bath type heat exchanger (17) and an arrow liquid oxygen storage tank (29); an inlet a of a ground circulating liquid oxygen storage tank (3) is connected with a pressurized gas cylinder (1) through a first valve (2), an outlet b of the ground circulating liquid oxygen storage tank (3) is provided with a first safety valve (5), an inlet c of the ground circulating liquid oxygen storage tank (3) is connected with an outlet g of a ground liquid oxygen tank truck (21) through a second valve (6), an outlet e of the ground circulating liquid oxygen storage tank (3) is connected with an inlet j of a negative pressure liquid nitrogen bath type heat exchanger (17) through a third valve (8), a second liquid oxygen pump (11) and an eleventh valve (12), an inlet f of the ground circulating liquid oxygen storage tank (3) is connected with an outlet of a first filter (10) through a first regulating valve (9), the ground circulating liquid oxygen storage tank (3) is connected with a temperature sensor (4), and the temperature sensor (4) is used for controlling the opening degree of the first regulating valve (9);
an outlet d of the ground circulating liquid oxygen storage tank (3) is connected with an inlet of the first flowmeter (40) through a fourth valve (7), a fifth valve (23), a first liquid oxygen pump (24) and a second filter (26), and a branch of the fifth valve (23) and the first liquid oxygen pump (24) is connected with a branch of the sixth valve (25) in parallel;
an outlet g of the ground liquid oxygen tank truck (21) is connected with a fourth valve (7), a fifth valve (23) and a sixth valve (25) through a seventh valve (22);
an inlet p of the negative pressure liquid nitrogen bath type heat exchanger (17) is connected with a liquid nitrogen tank wagon (19) through a ninth valve (20), the liquid nitrogen tank wagon (19) is connected with an inlet s of an upper rocket liquid oxygen storage tank (29) through a sixteenth valve (41) and a fourteenth valve (28), an outlet i of the negative pressure liquid nitrogen bath type heat exchanger (17) is connected with an inlet of an evacuating device (15) through an eighth valve (16), an inlet k of the negative pressure liquid nitrogen bath type heat exchanger (17) is connected with an outlet y of a helium storage tank (36) through a tenth valve (37), an outlet m of the negative pressure liquid nitrogen bath type heat exchanger (17) is connected with an inlet of a second flowmeter (13), and an outlet of the second flowmeter (13) is connected with an inlet of a first filter (10); an outlet n of the negative pressure liquid nitrogen bath type heat exchanger (17) is connected with an inlet of the gas-liquid separator (18), and the negative pressure liquid nitrogen bath type heat exchanger (17) is provided with a second safety valve (14);
an inlet t of the rocket-mounted liquid oxygen storage tank (29) is connected with a gas outlet of the gas-liquid separator (18) through a second regulating valve (30), an outlet v of the rocket-mounted liquid oxygen storage tank (29) is connected with an inlet of a compressor (34) through a third regulating valve (32), a pipeline between the third regulating valve (32) and the inlet of the compressor (34) is communicated with the atmosphere through a fifteenth valve (38), an outlet of the compressor (34) is connected with an inlet w of a helium storage tank (36) through a tenth valve (35), an inlet u of the rocket-mounted liquid oxygen storage tank (29) is connected with a pressure sensor (31), and the pressure sensor (31) controls the second regulating valve (30) and the third regulating valve (32) to be opened and closed; an inlet s of the rocket liquid oxygen storage tank (29) is connected with an outlet of the first flowmeter (40) through a fourteenth valve (28); an inlet r of the rocket liquid oxygen storage tank (29) is connected with a gas outlet of the gas-liquid separator (18) through a tenth valve (27); the rocket liquid oxygen storage tank (29) is provided with a liquid level sensor (39); the rocket liquid oxygen storage tank (29) is provided with a third safety valve (33).
2. The system of claim 1 for deep subcooled liquid oxygen injection and control in a cryogenic rocket launch site, wherein: the connecting pipelines are high-vacuum multilayer heat insulation or polyurethane foaming heat insulation.
3. The system of claim 1 for deep subcooled liquid oxygen injection and control in a cryogenic rocket launch site, wherein: the first valve (2) is a normal temperature regulating valve; the second valve (6), the third valve (8), the fourth valve (7), the fifth valve (23), the sixth valve (25), the seventh valve (22), the eighth valve (16), the ninth valve (20), the tenth valve (37), the eleventh valve (12), the tenth valve (35), the tenth valve (27), the fourteenth valve (28), the fifteenth valve (38) and the sixteenth valve (41) are low-temperature stop valves;
the first regulating valve (9), the second regulating valve (30) and the third regulating valve (32) are low-temperature regulating valves with PID control;
the first safety valve (5), the second safety valve (14) and the third safety valve (33) are low-temperature safety angle valves;
the first liquid oxygen pump (24) and the second liquid oxygen pump (11) are low-temperature liquid pumps;
the first flowmeter (40) and the second flowmeter (13) are liquid flowmeters;
the first filter (10) and the second filter (26) are low-temperature fluid filters;
the helium storage tank (36) is a low-temperature gas storage tank.
4. The system of claim 1 for deep subcooled liquid oxygen injection and control in a cryogenic rocket launch site, wherein: the gas-liquid separator (18) is a low-temperature gas-liquid separator.
5. The system of claim 1 for deep subcooled liquid oxygen injection and control in a cryogenic rocket launch site, wherein: the evacuating device (15) is a vacuum pump or an ejector with a rewarming device or a low-temperature vacuum pump without a rewarming device.
6. The system of claim 1 for deep subcooled liquid oxygen injection and control in a cryogenic rocket launch site, wherein: the ground circulating liquid oxygen storage tank (3) is a high-vacuum multilayer heat-insulation low-temperature storage tank.
7. The system of claim 1 for deep subcooled liquid oxygen injection and control in a cryogenic rocket launch site, wherein: the negative pressure liquid nitrogen bath type heat exchanger (17) is a low-temperature negative pressure air bath type heat exchanger, and the working medium is liquid nitrogen or liquid oxygen.
8. The system of claim 1 for deep subcooled liquid oxygen injection and control in a cryogenic rocket launch site, wherein: the rocket-mounted liquid oxygen storage tank (29) is a low-temperature storage tank made of foam materials and insulated thermally, and has the functions of helium dynamic regulation pressure compensation and deep super-cooling liquid oxygen high supercooling degree maintenance.
9. The method of utilizing the system for deep subcooling liquid oxygen injection and control in a cryogenic rocket launch site of claim 1 wherein: the method comprises the following steps:
first, surface cycle subcooling to obtain subcooled liquid oxygen: opening a ninth valve (20), and injecting saturated liquid nitrogen under normal pressure from a liquid nitrogen tank wagon (19) into the shell side of the negative-pressure liquid nitrogen bath type heat exchanger (17); opening an eighth valve (16), starting an evacuating device (15), evacuating and supercooling liquid nitrogen on the shell side of the negative-pressure liquid nitrogen bath type heat exchanger (17) to reach a 64K temperature zone; working medium or liquid oxygen, and the liquid oxygen can be reduced to a 56K temperature zone through evacuation;
opening a second valve (6), and injecting saturated liquid oxygen under normal pressure into the ground circulating liquid oxygen storage tank (3) from the ground liquid oxygen tank truck (21), wherein the temperature of the saturated liquid oxygen under normal pressure is 90.188K; the first regulating valve (9) is controlled by a signal of the temperature sensor (4), and the temperature sensor (4) monitors the liquid oxygen temperature in the ground circulating liquid oxygen storage tank (3) so as to regulate the liquid oxygen flow in the circulating loop and control the cold input into the ground circulating liquid oxygen storage tank (3); opening a third valve (8) and an eleventh valve (12), controlling a first regulating valve (9) to be opened by a temperature sensor (4), obtaining cold quantity by liquid oxygen in the ground circulating liquid oxygen storage tank (3) through a negative pressure liquid nitrogen bath type heat exchanger (17), returning to the ground circulating liquid oxygen storage tank (3) after passing through a second flowmeter (13) and a first filter (10), mixing with the liquid oxygen in the ground circulating liquid oxygen storage tank (3), reducing the temperature of the liquid oxygen, and finally obtaining 66K of supercooled liquid oxygen in the ground circulating liquid oxygen storage tank (3); if the working medium in the negative pressure liquid nitrogen bath type heat exchanger (17) is liquid oxygen, 56K deep super-cooled liquid oxygen can be obtained in the ground circulating liquid oxygen storage tank (3);
step two, precooling the liquid oxygen storage tank (29) on the arrow step by step: firstly, opening a sixteenth valve (41) and a fourteenth valve (28), enabling saturated liquid nitrogen to enter an arrow liquid oxygen storage tank (29), performing preliminary precooling on a filling pipeline and arrow liquid oxygen storage tank (29), precooling the arrow liquid oxygen storage tank (29) to a 78K temperature zone through the preliminary precooling, and closing the sixteenth valve (41) and the fourteenth valve (28) after the preliminary precooling is completed;
opening a tenth valve (37) and a tenth valve (27), enabling helium in a helium storage tank (36) to obtain cold energy through a negative pressure liquid nitrogen bath type heat exchanger (17), enabling the cold energy to enter an arrow-mounted liquid oxygen storage tank (29) through a gas-liquid separator (18) from an inlet r, further pre-cooling a filling pipeline and the arrow-mounted liquid oxygen storage tank (29), further pre-cooling the arrow-mounted liquid oxygen storage tank (29) to a 66K temperature zone, if a working medium of the negative pressure liquid nitrogen bath type heat exchanger (17) is liquid oxygen, reducing the liquid oxygen to a 56K temperature zone through evacuation, and enabling the arrow-mounted liquid oxygen storage tank (29) to be pre-cooled to the 56K temperature zone; helium from the rocket liquid oxygen storage tank (29) returns to a helium storage tank (36) through a third regulating valve (32), a compressor (34) and a tenth valve (35) for circulation;
thirdly, carrying out rocket filling on the supercooled liquid oxygen: after the precooling is completed in the second step, opening the first valve (2), the fourth valve (7), the sixth valve (25) and the fourteenth valve (28), closing the fifth valve (23), closing the first liquid oxygen pump (24), filling the supercooled liquid oxygen in the ground circulating liquid oxygen storage tank (3) into the rocket-mounted liquid oxygen storage tank (29) through the fourth valve (7), the sixth valve (25), the second filter (26), the first liquid oxygen pump (24) and the fourteenth valve (28) under the pressurization of the pressurization gas cylinder (1), and realizing the extrusion filling; closing the sixth valve (25), opening the fifth valve (23), and starting the first liquid oxygen pump (24) to realize pumping type large-flow filling;
in the filling process, when the second regulating valve (30) is opened, the low-temperature helium gas passing through the gas-liquid separator (18) dynamically pressurizes the rocket upper liquid oxygen storage tank (29); when the compressor (34) is started, the pressure of the rocket liquid oxygen storage tank (29) is controlled; the pressure sensor (31) controls the opening degree of the second regulating valve (30) and the third regulating valve (32), so that the pressure of the rocket liquid oxygen storage tank (29) is regulated, and the micro-positive pressure in the rocket liquid oxygen storage tank (29) is ensured;
the liquid level sensor (39) monitors the liquid level in the rocket liquid oxygen storage tank (29), the filling is completed when the set liquid level is reached, and the fourth valve (7) and the first liquid oxygen pump (24) are closed after the filling is completed;
fourthly, maintaining the supercooling degree of the liquid oxygen in the rocket liquid oxygen storage tank (29): opening a tenth valve (37), a tenth valve (27) and a tenth valve (35), closing a fifteenth valve (38), controlling the opening of a third regulating valve (32) and starting a compressor (34) by a pressure sensor (31), obtaining cold quantity from helium in a helium storage tank (36) through a negative pressure liquid nitrogen bath type heat exchanger (17), injecting the cold quantity into the rocket-borne liquid oxygen storage tank (29) through a gas-liquid separator (18) from an inlet r, realizing concentration difference supercooling through the pressure difference between the oxygen partial pressure in a helium bubble and the oxygen partial pressure in liquid oxygen, and maintaining the supercooling degree of deep supercooling liquid oxygen in the rocket-borne liquid oxygen storage tank (29); the helium-oxygen mixed gas returns to a helium storage tank (36) through a third regulating valve (32), a compressor (34) and a tenth valve (35);
the helium-oxygen mixture in the helium storage tank (36) passes through the negative pressure liquid nitrogen bath type heat exchanger (17) due to different boiling point temperatures, oxygen is liquefied again and separated in the gas-liquid separator (18), liquid oxygen returns to the ground circulating liquid oxygen storage tank (3), and pure low-temperature helium enters the rocket-mounted liquid oxygen storage tank (29) again to control the pressure of the gas pillow and maintain the large supercooling degree of the deep supercooled liquid oxygen.
10. The method of claim 9, wherein: the third step is to fill the liquid oxygen storage tank on the arrow, and the seventh valve (22), the gas-liquid separator (18) and the fourteenth valve (28) are opened through the ground liquid oxygen tank truck (21), and the fifth valve (23) and the first liquid oxygen pump (24) are started to realize the pumping pressure type large-flow filling function of the liquid oxygen with the normal boiling point at the present stage; and starting the sixth valve (25) to realize the extrusion filling function of the normal boiling point liquid oxygen at the present stage.
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