CN110425415B - System and method for supplementing pressurized gas propelled by spacecraft in orbit - Google Patents

System and method for supplementing pressurized gas propelled by spacecraft in orbit Download PDF

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Publication number
CN110425415B
CN110425415B CN201910722224.6A CN201910722224A CN110425415B CN 110425415 B CN110425415 B CN 110425415B CN 201910722224 A CN201910722224 A CN 201910722224A CN 110425415 B CN110425415 B CN 110425415B
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Prior art keywords
gas
pipeline
receiving
output
cylinder
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CN201910722224.6A
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CN110425415A (en
Inventor
朱恩涌
何宇
朱枞鹏
廖建林
柏林厚
王岩
范高洁
李兴乾
吴冰
白良浩
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Beijing Space Technology Research and Test Center
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Beijing Space Technology Research and Test Center
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • 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
    • F17C13/04—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
    • F17C5/06—Methods or apparatus for filling containers with liquefied, solidified, or compressed gases under pressures for filling with compressed gases
    • 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
    • F17C2205/00—Vessel construction, in particular mounting arrangements, attachments or identifications means
    • F17C2205/03—Fluid connections, filters, valves, closure means or other attachments
    • F17C2205/0302—Fittings, valves, filters, or components in connection with the gas storage device
    • F17C2205/0323—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
    • F17C2227/00—Transfer of fluids, i.e. method or means for transferring the fluid; Heat exchange with the fluid
    • F17C2227/04—Methods for emptying or filling
    • 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
    • F17C2250/00—Accessories; Control means; Indicating, measuring or monitoring of parameters
    • F17C2250/04—Indicating or measuring of parameters as input values
    • F17C2250/0404—Parameters indicated or measured
    • F17C2250/043—Pressure
    • 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
    • F17C2265/00—Effects achieved by gas storage or gas handling
    • F17C2265/06—Fluid distribution
    • F17C2265/068—Distribution pipeline networks
    • 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
    • F17C2270/00—Applications
    • F17C2270/01—Applications for fluid transport or storage
    • F17C2270/0186—Applications for fluid transport or storage in the air or in space
    • F17C2270/0194—Applications for fluid transport or storage in the air or in space for use under microgravity conditions, e.g. space

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Pipeline Systems (AREA)

Abstract

The invention relates to an on-orbit replenishing system for pressurized gas propelled by a spacecraft, which comprises: the receiving assembly comprises a target gas cylinder and a receiving pipeline connected with the target gas cylinder; the gas supply assembly is used for supplementing gas to the target gas cylinder in the receiving assembly and comprises a gas supply gas cylinder and an output pipeline; one end of the output pipeline is connected with the gas supply cylinder, and the other end of the output pipeline is connected with the receiving pipeline; the output pipeline is provided with a pressure reduction module for carrying out pressure reduction treatment on the gas output by the gas supply cylinder; the receiving pipeline is provided with a pressurization module used for performing pressurization treatment on the gas output by the output pipeline. The invention can realize the supplement of gas from the low-pressure gas cylinder to the high-pressure gas cylinder, ensures that the gas pressure of the supplement pipeline between the devices is low, realizes the reliable connection and sealing, has low development difficulty of the gas path floating disconnector, has less gas discharged to the outside of the cabin, and reduces the waste of pressurized gas.

Description

System and method for supplementing pressurized gas propelled by spacecraft in orbit
Technical Field
The invention relates to the field of spaceflight, in particular to an on-orbit supplementing system and method for pressurized gas propelled by a spacecraft.
Background
The propellant on-track replenishing technology is a core technology of space station engineering and is a necessary technology for long-term operation of space stations. Russian has already realized the propellant filling in orbit since 1978, has successfully completed many times of on-orbit replenishment, and the United states started the research of on-orbit replenishment technology from the beginning of the last 80 th century, so that the technology has been fully developed and the on-orbit demonstration verification is successfully realized.
Common methods for on-track addition of propellants include pressurized gas reuse, pump delivery, venting, and pressure doubling. The pressurized gas reuse method does not need pressurized gas supplement, but is not suitable for supplementing a surface tension storage tank propulsion system. The replenishing storage tank of the pressure doubling method has large working pressure, low safety and poor adaptability. For surface tension tanks, only pump transfer and venting methods can be used. However, in both methods, additional pressurized gas is required.
The pressurized gas can be supplemented in a direct supplementing mode, namely, the pressurized gas provides a higher-pressure and larger-volume gas cylinder for the spacecraft, and the pressurized gas is connected with the supplemented gas cylinder through the gas circuit floating disconnect device and the pipeline to directly convey the high-pressure gas to the supplemented gas cylinder. The method has the defects that the pressure of the high-pressure gas cylinder which is provided by the pressurized gas and needs to be configured for the spacecraft is high, the volume is large, the gas pressure transmitted among the spacecrafts is high, and the difficulty in developing the high-pressure gas circuit floating disconnector is high.
Therefore, a gas replenishing system capable of replenishing a low-pressure gas cylinder to a high-pressure gas cylinder and reducing gas transmission pressure between spacecrafts is needed.
Disclosure of Invention
The invention aims to solve the problems and provides an on-orbit supplementing system and an on-orbit supplementing method for pressurized gas propelled by a spacecraft.
In order to achieve the purpose, the invention provides an on-orbit replenishment system and a replenishment method for pressurized gas propelled by a spacecraft, which comprises the following steps:
the receiving assembly comprises a target gas cylinder and a receiving pipeline connected with the target gas cylinder;
the gas supply assembly is used for supplementing gas to the target gas cylinder in the receiving assembly and comprises a gas supply gas cylinder and an output pipeline
One end of the output pipeline is connected with the gas supply cylinder, and the other end of the output pipeline is connected with the receiving pipeline;
the output pipeline is provided with a pressure reduction module for carrying out pressure reduction treatment on the gas output by the gas supply cylinder;
the receiving pipeline is provided with a pressurization module used for performing pressurization treatment on the gas output by the output pipeline.
According to one aspect of the invention, the receiving pipeline and the output pipeline are connected by a gas circuit floating disconnect;
the gas circuit floating disconnector comprises an active end and a passive end which can be matched and connected with the active end;
the active end is connected with the outlet end of the output pipeline, and the passive end is connected with the inlet end of the receiving pipeline.
According to one aspect of the invention, the system further comprises an exhaust line arranged on the receiving line or on the output line, the exhaust line being located between the pressure increasing module and the pressure reducing module.
According to an aspect of the invention, the exhaust line is arranged on the receiving line.
According to one aspect of the invention, a plurality of self-locking valves are arranged on the output pipeline and the receiving pipeline and used for controlling the gas flow in the pipelines;
the self-locking valves on the receiving pipeline are respectively arranged on the exhaust pipeline, between the target gas cylinder and the pressurization module and between the pressurization module and the connection point of the exhaust pipeline and the receiving pipeline;
and self-locking valves on the output pipeline are respectively arranged between the pressure reducing module and the gas path floating disconnector and between the pressure reducing module and the gas supply bottle.
According to one aspect of the invention, a plurality of sensors are also provided on the output line and the receiving line for monitoring line pressure;
the sensor on the output pipeline is respectively arranged close to the outlet of the gas supply cylinder and the outlet of the pressure reducing module;
and the sensors on the receiving pipeline are respectively arranged close to the inlet of the target gas cylinder, the passive end of the gas circuit floating disconnecting and connecting device and the inlet and the outlet of the pressurizing module.
According to one aspect of the present invention, a method of supplementing a pressurized gas of a supplementing system includes the steps of:
a. connecting the receiving assembly and the gas supply assembly;
b. the gas in the gas supply cylinder is led to a receiving pipeline after being decompressed;
c. the gas introduced into the receiving pipeline enters a target gas cylinder after being subjected to pressurization treatment;
d. and after the supplement is finished, discharging the gas in the pipelines at the two sides of the gas circuit floating disconnector from the exhaust pipeline.
According to an aspect of the present invention, in the step (a), the output line and the receiving line are connected by plugging the active end and the passive end of the gas path floating disconnect.
According to one aspect of the invention, in the step (b), the pipelines at two sides of the gas path floating disconnector are subjected to pressure-maintaining leak detection after the gas is led to the receiving pipeline.
According to one aspect of the invention, in the step (b), the self-locking valves on both sides of the pressure reduction module are closed to perform pressure maintaining leak detection on the pipelines on both sides of the gas path floating disconnector.
According to an aspect of the invention, in the step (d), the self-locking valves on both sides of the pressurizing module on the receiving pipeline and the self-locking valves on both sides of the depressurizing module on the output pipeline are closed in sequence, and the self-locking valve on the exhaust pipeline is opened to enable the gas in the pipelines on both sides of the gas circuit floating breaker to be exhausted from the exhaust pipeline.
According to one scheme of the invention, the gas output by the gas supply cylinder is firstly decompressed by the decompression module, so that the pressure of the high-pressure gas output by the gas cylinder is lower through the supplement pipeline, the reliable connection and sealing of a gas circuit are ensured, the development difficulty of the gas circuit floating disconnector is reduced, the gas discharged to the outside of the cabin is less, and the waste of pressurized gas is reduced. And the decompressed gas is pressurized by the pressurizing module to enter the target gas cylinder, so that the pressure of the decompressed gas is increased to be higher than that of the target gas cylinder again and is enough to enter the target gas cylinder. The arrangement also ensures that the air pressure of the air supply cylinder is not excessively high and the volume is not excessively large, thereby solving the problems of high pressure and large volume of the cylinder configured by pressurized air for the spacecraft in the prior art.
According to one scheme of the invention, the exhaust pipeline can exhaust gas of pipelines at two sides of the gas circuit floating disconnector after the completion of replenishment so as to ensure the safety when the active end and the passive end of the gas circuit floating disconnector are separated.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 schematically shows a block diagram of an in-orbit replenishment system for a spacecraft propulsion pressurized gas in accordance with an embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
Fig. 1 schematically shows a block diagram of an in-orbit replenishment system for a spacecraft propulsion pressurized gas in accordance with an embodiment of the present invention. As shown in fig. 1, the spacecraft propulsion pressurized gas on-orbit replenishment system of the present invention comprises a receiving module 1 and a gas supply module 2. The receiving assembly 1 is positioned on a pressurized gas receiving spacecraft, the gas supply assembly 2 is positioned on a pressurized gas providing spacecraft, and after the two spacecrafts are rigidly connected, the gas supply assembly 2 supplements gas to the receiving assembly 1.
According to one embodiment of the invention, the receiving assembly 1 comprises a target cylinder 101 and a receiving line 102. The target gas cylinder 101 is a high-pressure gas cylinder of a pressurized gas receiving-side spacecraft, is used for receiving supplemented pressurized gas, and is simultaneously used as a propulsion gas cylinder for receiving the pressurized gas spacecraft. The receiving pipe 102 is connected to the target gas cylinder 101 and also to the gas supply module 2, and is configured to receive the gas supplied from the gas supply module 2 and transfer the gas to the target gas cylinder 101.
According to one embodiment of the invention, the gas supply assembly 2 comprises a gas supply cylinder 201 and an output line 202. The gas supply cylinder 201 is a pressurized gas cylinder of a pressurized gas provider spacecraft, is used for supplying supplemented pressurized gas, and is also used as a propulsion gas cylinder for providing the pressurized gas spacecraft. The output pipeline 202 has one end connected to the gas cylinder 201 and the other end connected to the receiving pipeline 102.
According to one embodiment of the present invention, the receiving line 102 and the output line 202 are connected by a pneumatic floating disconnect a. The pneumatic floating disconnector A comprises an active end A1 and a passive end A2. The active end a1 is connected to the outlet end of the outlet line 202 and the passive end a2 is connected to the inlet end of the receiving line 102. The active end a1 and the passive end a2 can be connected or disconnected by plugging, so that the output pipeline 202 and the receiving pipeline 102 can be connected or disconnected.
According to an embodiment of the present invention, the output pipeline 202 is provided with a pressure reduction module 2021 for performing pressure reduction on the gas output from the gas cylinder 201, so as to reduce the high-pressure gas output from the gas cylinder 201 to a low-pressure gas of less than 1 MPa. The receiving pipeline 102 is provided with a pressurizing module 1021 for pressurizing the gas output by the output pipeline 202. Therefore, the high-pressure gas output by the gas supply cylinder 201 is decompressed firstly, then reaches the receiving component 1 through the gas path floating disconnector A, and then is charged into the target gas cylinder 101 after being subjected to gas pressurization, so that the gas pressure of a pipeline between devices is low, the development difficulty of the reliably connected and sealed gas path floating disconnector is low, the gas discharged to the outside of the cabin is small, and the waste of pressurized gas is reduced; and the gas pressure of the gas supply cylinder 201 is not required to be too high, and the volume is not required to be too large, so that the problems of high pressure and large volume of the gas cylinder configured by pressurizing gas for providing the spacecraft in the prior art are solved.
According to an embodiment of the invention, the gas exhaust pipeline 103 is further used for exhausting gas from pipelines on two sides of the gas circuit floating disconnector A after the completion of the supplement, so as to ensure the safety when the active end A1 and the passive end A2 of the gas circuit floating disconnector A are separated. The exhaust pipe 103 may be disposed on the receiving pipe 102 or the output pipe 202 as long as it is located between the pressurization module 1021 and the depressurization module 2021, and in the present invention, the exhaust pipe 103 is disposed on the receiving pipe 102.
In accordance with one embodiment of the present invention, the outlet line 202 and the receiving line 102 are provided with a plurality of latching valves, i.e., LVb1 through LVb5 in fig. 1, for controlling the flow of gas in the lines.
The latching valve LVb1 on the receiving line 102 is located between the target cylinder 101 and the pressure boost module 1021, and is used for controlling the outlet gas of the pressure boost module 1021 to enter the target cylinder 101; the self-locking valve LVb2 is located between the pressure boosting module 1021 and the connection point of the exhaust line 103 and the receiving line 102, and the gas output from the output line 202 passes through the self-locking valve LVb2 and then reaches the pressure boosting module 1021; self-locking valve LVb3 is disposed on exhaust line 103 for controlling the connection and disconnection of the line to vacuum.
The self-locking valve LVb4 on the output line 202 is located between the pressure reducing module 2021 and the pneumatic floating disconnect a, and is used for controlling the flow of additional gas into the receiving line 102; a latching valve LVb5 is located between the pressure reduction module 2021 and the supply gas cylinder 201 for controlling the flow of high pressure gas from the supply gas cylinder 201 into the pressure reduction module 2021.
In accordance with one embodiment of the present invention, a plurality of sensors for monitoring line pressure, i.e., PTb1 through PTb6 of fig. 1, are also provided on the output line 202 and the receiving line 102.
A sensor PTb1 on the receiving line 102 is provided near the inlet of the target gas cylinder 101 for monitoring the pressure state of the target gas cylinder 101; the sensor PTb2 and the sensor PTb3 are respectively disposed near the inlet and the outlet of the pressure boost module 1021, and are respectively used for monitoring the pressure of the gas pressurized by the pressure boost module 1021 and the pressure of the gas entering the pressure boost module 1021; a sensor PTb4 is provided near the passive end a2 of the pneumatic floating disconnect a for monitoring the pressure of the gas flowing into the receiving line 102.
A sensor PTb5 on the output line 202 is disposed near the outlet of the depressurization module 2021 for monitoring the gas pressure after depressurization by the depressurization module 2021; a sensor PTb6 is provided near the outlet of the supplied gas cylinder 201 for monitoring the pressure condition of the supplied gas cylinder 201.
The receiving and output lines 102 and 202 connect the propulsion tanks of each spacecraft in the positions shown in figure 1.
The pressurized gas supplementing method using the supplementing system of the invention comprises the following steps:
a. after the two spacecrafts are rigidly connected, the active end A1 and the passive end A2 of the plugging air path floating disconnector A connect the output pipeline 202 and the receiving pipeline 102, so that the receiving assembly 1 and the air supply assembly 2 are connected.
b. The self-locking valves LVb5 and LVb4 are opened in sequence, so that the gas in the gas supply cylinder 201 is decompressed by the decompression module 2021 and then led to the receiving pipeline 102. After the gas is led to the receiving pipeline 102, the self-locking valves LVb5 and LVb4 are closed, pressure maintaining and leakage detection are carried out on the pipelines on the two sides of the gas path floating disconnector a, and the two self-locking valves are opened again after the leakage detection is finished.
c. After the sealing state of the pipeline is confirmed to be good, the latching valve LVb2 is opened, additional gas enters the pressurizing module 1021, the pressurizing module 1021 is started to perform pressurizing treatment, the outlet pressure of the pressurizing module 1021 is monitored through the sensor PTb2, and when the PTb2 pressure value is larger than the target gas cylinder 101 pressure value (namely, the sensor PTb1 displays the pressure value), the latching valve LVb1 is opened to enable the gas to enter the target gas cylinder 101.
d. When the sensor PTb1 shows that the pressure of the target gas cylinder 101 meets the requirement (namely, the replenishment is completed), the self-locking valve LVb1 is closed, the pressurization module is closed, then the self-locking valves LVb2, LVb5 and LVb4 are sequentially closed, the self-locking valve LVb3 on the exhaust pipeline 103 is opened, so that the gas in the pipelines on the two sides of the gas circuit floating disconnector a is exhausted from the exhaust pipeline 103, when the sensor PTb4 shows that the pipelines reach a vacuum state, the self-locking valve LVb3 is closed, and the active end a1 and the passive end a2 of the gas circuit floating disconnector a are separated.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and it is apparent to those skilled in the art that various modifications and variations can be made in the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (11)

1. An in-orbit replenishment system for pressurized gas for propulsion of a spacecraft, comprising:
the receiving assembly (1) comprises a target gas cylinder (101) and a receiving pipeline (102) connected with the target gas cylinder (101);
the gas supply assembly (2) is used for supplementing gas to the target gas cylinder (101) in the receiving assembly (1) and comprises a gas supply cylinder (201) and an output pipeline (202);
one end of the output pipeline (202) is connected with the gas supply cylinder (201), and the other end of the output pipeline is connected with the receiving pipeline (102);
the device is characterized in that a pressure reduction module (2021) for carrying out pressure reduction treatment on the gas output by the gas supply cylinder (201) is arranged on the output pipeline (202);
the receiving pipeline (102) is provided with a pressurization module (1021) used for performing pressurization treatment on the gas output by the output pipeline (202).
2. The spacecraft propulsion pressurized gas in-orbit replenishment system of claim 1, wherein the receiving pipeline (102) and the output pipeline (202) are connected by a gas path floating disconnect (a);
the air path floating disconnector (A) comprises an active end (A1) and a passive end (A2) which can be matched and connected with the active end (A1);
the active end (A1) is connected with the outlet end of the output pipeline (202), and the passive end (A2) is connected with the inlet end of the receiving pipeline (102).
3. The spacecraft propulsion pressurized gas in-orbit replenishment system of claim 2, further comprising an exhaust line (103) disposed on the receiving line (102) or on the output line (202), the exhaust line (103) being located between the pressurization module (1021) and the depressurization module (2021).
4. A spacecraft propulsion pressurized gas in-orbit replenishment system according to claim 3, wherein the exhaust line (103) is provided on the receiving line (102).
5. The spacecraft propulsion pressurized gas in-orbit replenishment system of claim 4, wherein the output pipeline (202) and the receiving pipeline (102) are provided with a plurality of self-locking valves for controlling gas flow in the pipelines;
the self-locking valves on the receiving pipeline (102) are respectively arranged on the exhaust pipeline (103), between the target gas cylinder (101) and the pressurization module (1021) and between the pressurization module (1021) and the connection point of the exhaust pipeline (103) and the receiving pipeline (102);
the self-locking valves on the output pipeline (202) are respectively arranged between the pressure reducing module (2021) and the air path floating disconnector (A) and between the pressure reducing module (2021) and the air supply cylinder (201).
6. The spacecraft propulsion pressurized gas in-orbit replenishment system of claim 5, wherein the output line (202) and the receiving line (102) are further provided with a plurality of sensors for monitoring line pressure;
the sensors on the output pipeline (202) are respectively arranged close to the outlet of the gas supply cylinder (201) and the outlet of the pressure reducing module (2021);
and sensors on the receiving pipeline (102) are respectively arranged close to the inlet of the target gas cylinder (101), the passive end (A2) of the gas path floating disconnector (A) and the inlet and outlet of the pressurization module (1021).
7. A method of supplementing pressurized gas using the supplementing system as claimed in any one of claims 1 to 6, comprising the steps of:
a. connecting the receiving assembly (1) and the gas supply assembly (2);
b. the gas in the gas supply cylinder (201) is decompressed and then led to the receiving pipeline (102);
c. the gas introduced into the receiving pipeline (102) enters a target gas cylinder (101) after being subjected to pressurization treatment;
d. after the supplement is finished, the gas in the pipelines at the two sides of the gas circuit floating disconnector (A) is discharged from the gas discharge pipeline (103).
8. The method as claimed in claim 7, wherein in the step a, the output line (202) and the receiving line (102) are connected by plugging an active end (A1) and a passive end (A2) of the pneumatic floating disconnect (A).
9. The method for supplementing pressurized gas according to claim 8, wherein in the step b, pressure-maintaining leak detection is performed on the pipelines at both sides of the gas path floating breaker (A) after the gas is led to the receiving pipeline (102).
10. The method for supplementing pressurized gas according to claim 9, wherein in the step b, self-locking valves on both sides of the pressure reduction module (2021) are closed to perform pressure-maintaining leak detection on the pipelines on both sides of the gas path floating breaker (a).
11. The method for supplementing pressurized gas according to claim 10, wherein in step d, the self-locking valves on the receiving pipeline (102) at both sides of the pressurizing module (1021) and the self-locking valves on the output pipeline (202) at both sides of the depressurizing module (2021) are closed in sequence, and the self-locking valves on the exhaust pipeline (103) are opened to discharge the gas in the pipelines on both sides of the gas path floating disconnect-connection device (a) from the exhaust pipeline (103).
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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6488237B1 (en) * 2001-09-28 2002-12-03 The Boeing Company Propellant cross-feed system and method
CN106134390B (en) * 2012-06-18 2014-10-22 上海空间推进研究所 A kind of implementation method of space propulsion system
CN107762663A (en) * 2017-08-30 2018-03-06 上海空间推进研究所 It is a kind of to collect the space propulsion system for promoting and adding function integration
CN107867411A (en) * 2017-09-20 2018-04-03 上海空间推进研究所 A kind of full-automatic in-orbit supplementing device
CN108454885A (en) * 2017-12-19 2018-08-28 上海空间推进研究所 Spacecraft propellant is in-orbit to add system and implementation method and aircraft
CN109110161A (en) * 2018-08-07 2019-01-01 北京空间技术研制试验中心 The mission program design method added for spacecraft on-board propulsion agent
CN109606741A (en) * 2018-12-28 2019-04-12 北京空间技术研制试验中心 Spacecraft surface tension propellant tank propellant is in-orbit to add system

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2822193B1 (en) * 2001-03-16 2003-06-27 Snecma Moteurs LOW-PUSH CRYOTECHNIC PROPULSION MODULE
GB2484114A (en) * 2010-09-30 2012-04-04 Astrium Ltd System for the Recovery, Storage and Utilisation of Atmospheric Gas for Use as a Vehicle Propellant

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6488237B1 (en) * 2001-09-28 2002-12-03 The Boeing Company Propellant cross-feed system and method
CN106134390B (en) * 2012-06-18 2014-10-22 上海空间推进研究所 A kind of implementation method of space propulsion system
CN107762663A (en) * 2017-08-30 2018-03-06 上海空间推进研究所 It is a kind of to collect the space propulsion system for promoting and adding function integration
CN107867411A (en) * 2017-09-20 2018-04-03 上海空间推进研究所 A kind of full-automatic in-orbit supplementing device
CN108454885A (en) * 2017-12-19 2018-08-28 上海空间推进研究所 Spacecraft propellant is in-orbit to add system and implementation method and aircraft
CN109110161A (en) * 2018-08-07 2019-01-01 北京空间技术研制试验中心 The mission program design method added for spacecraft on-board propulsion agent
CN109606741A (en) * 2018-12-28 2019-04-12 北京空间技术研制试验中心 Spacecraft surface tension propellant tank propellant is in-orbit to add system

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