CN116044608A - Rail control pipeline of spacecraft propulsion system and propellant supply control method thereof - Google Patents

Rail control pipeline of spacecraft propulsion system and propellant supply control method thereof Download PDF

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Publication number
CN116044608A
CN116044608A CN202211549518.1A CN202211549518A CN116044608A CN 116044608 A CN116044608 A CN 116044608A CN 202211549518 A CN202211549518 A CN 202211549518A CN 116044608 A CN116044608 A CN 116044608A
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China
Prior art keywords
valve
pressure sensor
pressure
control pipeline
rail control
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CN202211549518.1A
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Chinese (zh)
Inventor
潘一力
孙迎霞
刘锋
汪卉
张毅
李群广
周一彬
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Shanghai Institute of Space Propulsion
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Shanghai Institute of Space Propulsion
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Priority to CN202211549518.1A priority Critical patent/CN116044608A/en
Publication of CN116044608A publication Critical patent/CN116044608A/en
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/56—Control
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/56—Control
    • F02K9/58—Propellant feed valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/30—Use of alternative fuels, e.g. biofuels

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Abstract

The invention relates to a spacecraft propulsion system rail control pipeline and a propellant management method thereof in the technical field of spacecraft propulsion. The invention judges through the on-off state of the valve of the propulsion track control pipeline, if the valve on-off fault problem occurs, adopts on-track compensation measures, ensures that the flow resistance of the oxidant and the flow resistance of the fuel track control pipeline are consistent as much as possible, reduces the mixing ratio precision of the fuel track control engine of the propulsion system caused by inconsistent on-off state of the valve of the oxidant and the fuel pipeline, ensures that the residual quantity of the propellant accords with the design expectation, and provides guarantee for realizing the on-track service life of the spacecraft.

Description

Rail control pipeline of spacecraft propulsion system and propellant supply control method thereof
Technical Field
The invention relates to the technical field of control of space engines, in particular to a spacecraft propulsion system rail control pipeline and a propellant supply control method thereof, and particularly relates to a method for judging the on-off state and fault handling of a parallel valve of the spacecraft propulsion system rail control pipeline.
Background
In recent years, with the continuous development of aerospace technology, high requirements are put on long service life of a spacecraft. The life of a spacecraft is largely determined by the remaining amount of propellant, which is greatly affected by the mixing ratio of the propulsion system. The mixing ratio is oxidant consumption/fuel consumption. Under the condition that the mixing ratio is greatly deviated, one propellant of the binary propulsion system is exhausted in advance, the other propellant is excessive and remains, and the spacecraft cannot complete long-service-life on-orbit tasks. The mixing ratio of the propulsion system is mainly determined by the mixing ratio of the track-controlled engine, so that the propulsion system needs to ensure that the mixing ratio of the track-controlled engine cannot deviate greatly. In order to ensure leakage of the rail-controlled engine after shutdown, a valve is added on a system rail-controlled pipeline, namely the upstream of the rail-controlled engine to realize sealed double-channel redundancy. In consideration of ensuring reliable communication of the rail control pipelines, 2 valves are generally arranged in parallel to conduct parallel redundancy management on the rail control pipelines. However, as the two valves are arranged on the oxidant and the fuel rail control pipeline, if the condition that at most one valve cannot be normally opened or closed in the oxidant and the fuel rail control pipeline occurs, the flow resistance of the rail control pipeline can be greatly influenced, the pressure at the inlet of the rail control engine can deviate from the rated value, and the mixing ratio of the rail control engine can deviate greatly. Therefore, it is necessary to design a method for determining the on-off state of the valve of the rail control pipeline on the rail and providing an on-rail compensation method for the generated fault condition.
Patent document CN112648110a (application number CN 202011552380.1) discloses a scheme for arranging parallel valves at the upstream of a spacecraft orbit control engine, so as to realize the system design of dual redundant sealing of engine valve and system valve. Patent document CN110989707a (application number: cn201911081695. X) discloses a method for realizing management of system line pressure by using line heating.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a spacecraft propulsion system rail control pipeline and a propellant supply control method thereof.
The invention provides a spacecraft propulsion system rail control pipeline, which comprises an oxidant storage tank, a fuel storage tank, a propulsion and control interaction device, a rail control engine, a valve, a heater, a temperature sensor, a pressure sensor, an oxidant rail control pipeline, a fuel rail control pipeline and a controller, wherein the fuel rail control pipeline is connected with the fuel storage tank;
the valve comprises a first valve, a second valve, a third valve and a fourth valve, the first valve, the second valve, the third valve and the fourth valve are respectively and electrically connected with the propulsion and control interaction device, the propulsion and control interaction device is used for controlling restarting and of the first valve, the second valve, the third valve and the fourth valve, the heater comprises a first heater and a second heater, the temperature sensor comprises an oxidant rail control pipeline temperature sensor and a second heater, and the pressure sensor comprises a first pressure sensor, a second pressure sensor, a third pressure sensor and a fourth pressure sensor;
the fuel rail control system comprises an oxidant storage tank, an oxidant rail control pipeline, a fuel sensor, a fuel tank and a fourth pressure sensor, wherein the oxidant storage tank is communicated with the rail control engine through an oxidant rail control pipeline;
the controller performs on-off control on the first valve and the second valve which are positioned on the oxidant rail control pipeline and the valves of the third valve and the fourth valve which are positioned on the fuel rail control pipeline according to the information of whether the fault valves exist or not, and propellant supply is performed in a mode that the on-off numbers of the valves on the oxidant rail control pipeline and the fuel rail control pipeline are consistent.
The invention also provides a spacecraft propulsion system propellant supply control method, which adopts the spacecraft propulsion system rail control pipeline and comprises the following steps:
s1, detecting the valve switch state: detecting whether a fault valve which cannot be normally opened and closed exists in the first valve and the second valve or not through opening and closing operations of the first valve and the second valve and heating operation of the first heater when the rail control pipeline is filled, and judging specific faults; detecting whether a fault valve which cannot be normally opened and closed exists in the third valve and the fourth valve or not through opening and closing operations of the third valve and the fourth valve and heating operations of the second heater, and judging specific faults; if the fault valve exists, the step S2 is carried out, and if the fault valve does not exist, the step S3 is directly carried out;
s2, fault valve processing: after the step S1, the controller sends an instruction to reset the fault valve, then the step S1 is used for detecting again, if the fault of the fault valve still cannot be relieved, the propulsion and control interaction device is restarted, then the controller continues to reset the instruction sent by the fault valve, the step S1 is used for detecting again, and then the step S3 is carried out in a state that the fault is eliminated or the fault still exists;
s3, propellant supply control: the controller performs on-off control on the first valve and the second valve which are positioned on the oxidant rail control pipeline and the valves of the third valve and the fourth valve which are positioned on the fuel rail control pipeline according to the information of whether the fault valves exist or not, and propellant supply is performed in a mode that the on-off numbers of the valves on the oxidant rail control pipeline and the fuel rail control pipeline are consistent.
In some embodiments, in step S1, the operation steps for determining that the opening states and the closing states of the first valve and the second valve are all good are: firstly, opening the first valve, wherein the pressure values of the first pressure sensor and the second pressure sensor are the same, then opening the second valve and closing the first valve, heating the oxidant rail control pipeline to a set value through the first heater, keeping the pressure values of the second pressure sensor and the first pressure sensor consistent in the heating process, and then closing the second valve and the first heater, wherein the pressure value of the second pressure sensor gradually drops to a preset value;
in some embodiments, in step S1, the operation steps for determining that the open states and the closed states of the third valve and the fourth valve are all good are: firstly, opening the third valve, wherein the pressure values of the third pressure sensor and the fourth pressure sensor are the same, then opening the fourth valve and closing the third valve, heating the fuel rail control pipeline to a set value through the second heater, keeping the pressure values of the fourth pressure sensor and the third pressure sensor consistent in the heating process, and then closing the fourth valve and the second heater, wherein the pressure value of the fourth pressure sensor gradually drops to a preset value.
In some embodiments, in step S1, the operation steps for determining that the first valve cannot be opened normally and the second valve can be opened and closed normally are as follows: firstly, opening the first valve, wherein the pressure value of the second pressure sensor is unchanged, then opening the second valve, wherein the pressure value of the second pressure sensor is changed to be the same as the pressure value of the first pressure sensor, then closing the first valve, heating the oxidant rail control pipeline to a set value through the first heater, keeping the pressure values of the second pressure sensor and the first pressure sensor consistent in the heating process, and finally closing the second valve and the first heater, wherein the pressure value of the second pressure sensor slowly drops to a preset value;
in some embodiments, in step S1, the operation steps for determining that the third valve cannot be opened normally and the fourth valve can be opened and closed normally are as follows: firstly, opening the third valve, wherein the pressure value of the third pressure sensor is unchanged, then opening the fourth valve, the pressure value of the fourth pressure sensor is changed to be the same as the pressure value of the third pressure sensor, then closing the third valve, heating the fuel rail control pipeline to a set value through the second heater, keeping the pressure values of the fourth pressure sensor and the third pressure sensor consistent in the heating process, and finally closing the fourth valve and the second heater, wherein the pressure value of the fourth pressure sensor slowly drops to a preset value;
in some embodiments, in step S1, the operation steps for determining that the second valve cannot be normally opened and the first valve can be normally opened and closed are as follows: and opening the first valve, wherein the pressure value of the first pressure sensor is the same as that of the second pressure sensor, then opening the second valve and closing the first valve, heating the oxidant rail-controlled pipeline to a set value through the first heater, rapidly increasing the pressure value of the second pressure sensor in the heating process, and immediately opening the first valve, wherein the pressure value of the second pressure sensor is reduced to be the same as that of the first pressure sensor.
In some embodiments, in step S1, the operation steps for determining that the fourth valve cannot be normally opened and the third valve can be normally opened and closed are as follows: and opening the third valve, wherein the pressure value of the third pressure sensor is the same as that of the fourth pressure sensor, then opening the fourth valve and closing the third valve, heating the fuel rail control pipeline to a set value through the second heater, rapidly increasing the pressure value of the fourth pressure sensor in the heating process, and immediately opening the third valve, wherein the pressure value of the fourth pressure sensor is reduced to be the same as that of the third pressure sensor.
In some embodiments, in step S1, the operation step of determining that one of the first valve and the second valve cannot be normally closed is: opening the first valve, wherein the pressure value of the first pressure sensor is the same as that of the second pressure sensor, then opening the second valve and closing the first valve, heating the oxidant rail control pipeline to a set value through the first heater, keeping the pressure value of the second pressure sensor and the pressure value of the first pressure sensor consistent in the heating process, and then closing the second valve, wherein the pressure value of the second pressure sensor is the same as that of the first pressure sensor;
in some embodiments, in step S1, the operation step of determining that one of the third valve and the fourth valve cannot be normally closed is: and opening the third valve, wherein the pressure values of the third pressure sensor and the fourth pressure sensor are the same, then opening the fourth valve and closing the third valve, heating the fuel rail control pipeline to a set value through the second heater, keeping the pressure values of the fourth pressure sensor and the third pressure sensor consistent in the heating process, and then closing the fourth valve, wherein the pressure value of the fourth pressure sensor is kept the same as that of the third pressure sensor.
Compared with the prior art, the invention has the following beneficial effects:
the invention judges through the on-off state of the valve of the propulsion track control pipeline, if the valve on-off fault problem occurs, adopts on-track compensation measures, ensures that the flow resistance of the oxidant and the flow resistance of the fuel track control pipeline are consistent as much as possible, reduces the mixing ratio precision of the fuel track control engine of the propulsion system caused by inconsistent on-off state of the valve of the oxidant and the fuel pipeline, ensures that the residual quantity of the propellant accords with the design expectation, and provides guarantee for realizing the on-track service life of the spacecraft.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of a rail control piping system of the spacecraft propulsion system of the present invention;
FIG. 2 is a flow chart of a method of controlling the supply of propellant to a propulsion system of a spacecraft.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
Example 1
The embodiment provides a spacecraft propulsion system rail control pipeline, which comprises an oxidant storage tank 1, a fuel storage tank 2, a propulsion and control interaction device 3, a rail control engine 4, a valve 5, a heater 6, a temperature sensor 7, a pressure sensor 8, an oxidant rail control pipeline, a fuel rail control pipeline and a controller 11, as shown in fig. 1. The valve 5 comprises a first valve 51, a second valve 52, a third valve 53 and a fourth valve 54. The first valve 51, the second valve 52, the third valve 53 and the fourth valve 54 are electrically connected to the propulsion and control interface 3, respectively, and the propulsion and control interface 3 is configured to control the restarting of the first valve 51, the second valve 52, the third valve 53 and the fourth valve 54. The heater 6 includes a first heater 61 and a second heater 62. The temperature sensor 7 includes an oxidizer rail temperature sensor 71 and a second heater 72. The pressure sensor 8 includes a first pressure sensor 81, a second pressure sensor 82, a third pressure sensor 83, and a fourth pressure sensor 84.
The oxidant storage tank 1 is communicated with the rail-controlled engine 4 through an oxidant rail-controlled pipeline. The pipeline of the oxidant rail control pipeline is controlled by switching on and off the pipeline through a first valve 51 and a second valve 52 which are arranged in parallel. A first pressure sensor 81 is mounted at the propellant outlet of the oxidizer reservoir 1. A second pressure sensor 82 is mounted in the oxidant rail proximate the propellant inlet of the rail engine 4. The first heater 61 is attached to the outer peripheral surface of the oxidizer rail pipe for heat-treating it. The first temperature sensor 71 is connected to the oxidizer rail for detecting the heated temperature thereof.
The fuel tank 2 communicates with the rail engine 4 via a fuel rail. The pipeline of the fuel rail control pipeline is controlled by switching the pipeline through a third valve 53 and a fourth valve 54 which are arranged in parallel. A third pressure sensor 83 is mounted at the propellant outlet of the fuel tank 2. A fourth pressure sensor 84 is mounted in the fuel rail proximate the propellant inlet of the rail engine 4. A second heater 62 is attached to a location face of the fuel rail for heat treating it. A second temperature sensor 72 is connected to the fuel rail for detecting the heated temperature of the detector.
The controller 11 performs on-off control of the first valve 51 and the second valve 52 located on the oxidizer rail and the third valve 53 and the fourth valve 54 located on the fuel rail according to the information of whether the failed valve exists, and performs propellant supply in such a manner that the on-off numbers of the valves on the oxidizer rail and the fuel rail are consistent, so as to ensure that flow resistances of the oxidizer and the fuel line are balanced as much as possible, and perform rail transfer. The fault judging method of the first valve 51, the second valve 52, the third valve 53 and the fourth valve 54 mainly comprises the steps of opening and closing the valves and respectively heating the oxidizer rail control pipeline and the fuel rail control pipeline when the rail control pipeline is filled, and judging the correctness of valve opening and closing according to the pressure change in the pipeline.
The on-off states of two groups of valves which are arranged in parallel and positioned on the oxidant rail control pipeline and the fuel rail control pipeline are detected, and the working conditions of the valves are detected and judged to be three conditions by taking a first valve 51 and a second valve 52 on the oxidant rail control pipeline as examples: the first working condition is that the opening and closing states of the first valve 51 and the second valve 52 are both in a normal state; the second working condition is that one of the first valve 51 and the second valve 52 cannot be normally opened; the third condition is that one of the first valve 51 and the second valve 52 cannot be normally closed. Correspondingly, the third valve 53 and the fourth valve 54 on the fuel rail are also in the three conditions described above. The second working condition and the third working condition are fault working conditions, and the fault working conditions refer to that at most 1 valve in any one of the oxidant rail control pipeline and the fuel rail control pipeline fails.
The detection and judgment method of the first working condition comprises the following steps:
for the oxidizer rail control pipeline, the operation steps for judging that the opening state and the closing state of the first valve 51 and the second valve 52 are normal are as follows: when the rail control pipeline is filled, the first valve 51 is firstly opened, the pressure values of the first pressure sensor 81 and the second pressure sensor 82 are the same, then the second valve 52 is opened, the first valve 51 is closed, the oxidant rail control pipeline is heated to a set value through the first heater 61, the pressure values of the second pressure sensor 82 and the first pressure sensor 81 are kept consistent in the heating process, then the second valve 52 and the first heater 61 are closed, and the pressure value of the second pressure sensor 82 is gradually reduced to a preset value.
For the fuel rail control pipeline, the operation steps for judging that the opening state and the closing state of the third valve 53 and the fourth valve 54 are normal are as follows: when the rail control pipeline is filled, the third valve 53 is firstly opened, the pressure values of the third pressure sensor 83 and the fourth pressure sensor 84 are the same, then the fourth valve 54 is opened and the third valve 53 is closed, the fuel rail control pipeline is heated to a set value through the second heater 62, the pressure values of the fourth pressure sensor 84 and the third pressure sensor 83 are kept consistent in the heating process, then the fourth valve 54 and the second heater 62 are closed, and the pressure value of the fourth pressure sensor 84 is gradually reduced to a preset value.
The detection and judgment method of the second working condition comprises the following steps:
for the oxidizer rail control pipeline, the operation steps for judging that the first valve 51 can not be normally opened and the second valve 52 can be normally opened and closed are as follows: first valve 51 is opened, the pressure value of second pressure sensor 82 is unchanged, then second valve 52 is opened, the pressure value of second pressure sensor 82 is changed to be the same as the pressure value of first pressure sensor 81, first valve 51 is closed, the oxidant rail control pipeline is heated to a set value through first heater 61, the pressure value of second pressure sensor 82 and first pressure sensor 81 in the heating process is kept consistent, finally second valve 52 and first heater 6 are closed, and the pressure value of second pressure sensor 82 is slowly reduced to a preset value.
The operation steps for determining that the second valve 52 cannot be normally opened and the first valve 51 can be normally opened and closed are as follows: the first valve 51 is opened, the pressure value of the first pressure sensor 81 is the same as that of the second pressure sensor 82, then the second valve 52 is opened and the first valve 51 is closed, the oxidant rail is heated to a set value by the first heater 61, the pressure value of the second pressure sensor 82 is rapidly increased in the heating process, then the first valve 51 is immediately opened, and the pressure value of the second pressure sensor 82 is reduced to be the same as that of the first pressure sensor 81.
For the fuel rail, the operation steps for determining that the third valve 53 cannot be normally opened and the fourth valve 54 can be normally opened and closed are as follows: firstly, the third valve 53 is opened, the pressure value of the third pressure sensor 83 is unchanged, then the fourth valve 54 is opened, the pressure value of the fourth pressure sensor 84 is changed to be the same as the pressure value of the third pressure sensor 83, then the third valve 53 is closed, the fuel rail control pipeline is heated to a set value through the second heater 62, the pressure values of the fourth pressure sensor 84 and the third pressure sensor 83 are kept consistent in the heating process, and finally the fourth valve 54 and the second heater 62 are closed, and the pressure value of the fourth pressure sensor 84 is slowly reduced to a preset value.
The operation steps for determining that the fourth valve 54 cannot be normally opened and the third valve 53 can be normally opened and closed are as follows: the third valve 53 is opened, the third pressure sensor 83 is the same as the fourth pressure sensor 84 in pressure value, then the fourth valve 54 is opened and the third valve 53 is closed, the fuel rail is heated to a set value by the second heater 62, the pressure value of the fourth pressure sensor 84 is rapidly increased during heating, then the third valve 53 is immediately opened, and the pressure value of the fourth pressure sensor 84 is reduced to be the same as the third pressure sensor 83.
The third working condition judging method comprises the following steps:
for the oxidizer rail control pipeline, the operation steps for judging that one of the first valve 51 and the second valve 52 cannot be normally closed are as follows: the first valve 51 is opened, the pressure value of the first pressure sensor 81 is the same as that of the second pressure sensor 82, then the second valve 52 is opened and the first valve 51 is closed, the oxidant rail control pipeline is heated to a set value through the first heater 61, the pressure value of the second pressure sensor 82 and the pressure value of the first pressure sensor 81 are kept consistent in the heating process, then the second valve 52 is closed, and the pressure value of the second pressure sensor 82 is kept the same as that of the first pressure sensor 81.
For the fuel rail, the operation steps for determining that one of the third valve 53 and the fourth valve 54 cannot be normally closed are as follows: the third valve 53 is opened, the pressure value of the third pressure sensor 83 is the same as that of the fourth pressure sensor 84, then the fourth valve 54 is opened and the third valve 53 is closed, the fuel rail control pipeline is heated to a set value by the second heater 62, the pressure values of the fourth pressure sensor 84 and the third pressure sensor 83 are kept consistent during heating, then the fourth valve 54 is closed, and the pressure value of the fourth pressure sensor 84 is kept the same as that of the third pressure sensor 83.
Example 2
The embodiment 2 provides a propellant supply control method for a spacecraft propulsion system rail control engine, which is formed by adopting the spacecraft propulsion system rail control pipeline of the embodiment 1. As shown in fig. 2, the valve on-off state determination and fault handling method according to the present embodiment is performed according to a flowchart, and it is described that, for simplifying the text in the drawing, the valve 1 represents the first valve 51, the valve 2 represents the second valve 52, the valve 3 represents the third valve 53, and the valve 4 represents the fourth valve 54. The method comprises the following steps:
s1, detecting the valve switch state: during the rail-controlled line filling, by the opening and closing operations of the first valve 51 and the second valve 52 and the heating operation of the first heater 61, whether or not there is a malfunctioning valve that cannot be normally opened and closed in both the first valve 51 and the second valve 52 is detected, and a specific malfunction is determined. By the opening and closing operations of the third valve 53 and the fourth valve 54, and the heating operation of the second heater 62, it is detected whether there is a defective valve that cannot be normally opened and closed in both the third valve 53 and the fourth valve 54, and it is determined that a specific failure. If the valve has a fault, the step S2 is carried out, and if the valve has no fault, the step S3 is directly carried out. The detection and judgment of the opening state and the closing state of the first valve 51 and the second valve 52 on the oxidizer rail 9 and the third valve 53 and the fourth valve 54 on the fuel rail 10 are performed by the detection judgment method in embodiment 1, and are not described in detail.
S2, fault valve processing: after the step S1, the controller 11 sends an instruction to reset the faulty valve, and then the step S1 performs a re-detection and determination, if the fault of the faulty valve cannot be relieved, the pushing and controlling interaction device 3 is restarted, then the controller 11 continues to perform a resetting process on the faulty valve sending an instruction, and the step S1 performs a re-detection and determination again, and then the step S3 is entered in a state where the fault is eliminated or the fault still exists.
S3, propellant supply control: the controller 11 performs on-off control of the valves of the first valve 51 and the second valve 52 located on the oxidizer rail and the third valve 53 and the fourth valve 54 located on the fuel rail based on information about whether or not there is a defective valve, and performs propellant supply control in such a manner that the number of on-off valves on the oxidizer rail and the fuel rail is identical.
Specifically, the method comprises the following steps:
(1) If the first valve 51 or the second valve 52 cannot be opened and the third valve 53 or the fourth valve 54 cannot be opened, the rail transfer is performed while maintaining the second valve 52 or the first valve 51, the fourth valve 54 or the third valve 53 in the opened state.
(2) If the first valve 51 or the second valve 52 cannot be opened and the third valve 53 and the fourth valve 54 are normal, the rail transfer is performed while keeping one of the valve 2 or the first valve 1 open and one of the third valve 53 and the fourth valve 54 open.
(3) If the first valve 51 or the second valve 52 cannot be opened and one of the third valve 53 and the fourth valve 54 cannot be closed, the second valve 52 or the first valve 1 is kept open and one of the third valve 53 and the fourth valve 54 is kept open for rail transfer.
(4) If the first valve 51 and the second valve 52 are normal and the third valve 53 or the fourth valve 54 cannot be opened, the rail is changed under the condition that one of the first valve 51 and the second valve 52 is opened and the fourth valve 55 or the third valve 53 is opened.
(5) One of the first valve 51 and the second valve 52 cannot be closed, and the third valve 53 or the fourth valve 54 cannot be opened: the rail change is performed while one of the first valve 51 and the second valve 52 is kept open and the fourth valve 55 or the third valve 53 is kept open.
(6) One of the first valve 51 and the second valve 52 cannot be closed, and the third valve 53 and the fourth valve 54 are normal, so that the rail transfer is performed under the condition that 4 valves are simultaneously opened.
(7) If one of the first valve 51 and the second valve 52 is normal and one of the third valve 53 and the fourth valve 54 cannot be closed, the rail transfer is performed while keeping the 4 valves open at the same time.
According to the technical scheme provided by the embodiment, the method for judging the switch state of the parallel valve and disposing the fault mainly detects through a method for comprehensively combining valve switch, pipeline heating and pressure parameter change, and judges and obtains normal working conditions and fault working conditions. The on-orbit compensation treatment is carried out aiming at the fault working condition, after the compensation measures are taken, the mixing ratio precision of the on-orbit control engine is ensured to be not influenced as much as possible, the flow resistance difference of the on-orbit control pipeline caused by inconsistent opening and closing states of the valve of the fuel-orbit control pipeline and the oxidant of the spacecraft propulsion system is overcome, the mixing ratio deviation of the on-orbit control engine is further caused, the on-orbit service life of the spacecraft is finally influenced, and the long-term on-orbit service life of the spacecraft is ensured.
The method for judging the on-off state of the through valve has passed through a corresponding flight experiment, and can combine the judgment of the fault working condition and the method for disposing faults on-orbit in the subsequent flight application, so that the quantity of the switching valves of the oxidant and the fuel pipeline can be ensured to be consistent, the flow resistance of the oxidant and the fuel rail control pipeline can be ensured to be consistent as much as possible, the mixing ratio precision of the rail control engine of the propulsion system is further ensured, the residual quantity of the propellant accords with the design expectation, and the guarantee is provided for realizing the on-orbit service life of the spacecraft.
In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.

Claims (10)

1. The spacecraft propulsion system rail control pipeline is characterized by comprising an oxidant storage tank (1), a fuel storage tank (2), a propulsion and control interaction device (3), a rail control engine (4), a valve (5), a heater (6), a temperature sensor (7), a pressure sensor (8), an oxidant rail control pipeline, a fuel rail control pipeline and a controller (11);
the valve (5) comprises a first valve (51), a second valve (52), a third valve (53) and a fourth valve (54), the first valve (51), the second valve (52), the third valve (53) and the fourth valve (54) are respectively electrically connected with the propulsion and control interactor (3), the propulsion and control interactor (3) is used for controlling the restarting and of the first valve (51), the second valve (52), the third valve (53) and the fourth valve (54), the heater (6) comprises a first heater (61) and a second heater (62), the temperature sensor (7) comprises an oxidant rail temperature sensor (71) and a second heater (72), and the pressure sensor (8) comprises a first pressure sensor (81), a second pressure sensor (82), a third pressure sensor (83) and a fourth pressure sensor (84);
the oxidant storage tank (1) is communicated with the rail control engine (4) through the oxidant rail control pipeline, the oxidant rail control pipeline is controlled to be switched by the first valve (51) and the second valve (52) which are arranged in parallel, the fuel storage tank (2) is communicated with the rail control engine (4) through the fuel rail control pipeline, the fuel rail control pipeline is controlled to be switched by the third valve (53) and the fourth valve (54) which are arranged in parallel, the first heater (61) is attached to the oxidant rail control pipeline and used for heating, the second heater (62) is attached to the fuel rail control pipeline and used for heating, the oxidant rail control pipeline temperature sensor (71) is arranged on the oxidant rail control pipeline and used for detecting temperature, the fuel rail control pipeline temperature sensor (72) is arranged on the fuel rail control pipeline and used for detecting temperature, the first pressure sensor (81) is arranged at an outlet of the oxidant storage tank (1), the second pressure sensor (82) is arranged at the inlet of the engine (4), and the second pressure sensor (82) is arranged at the inlet of the fuel rail control engine (4);
the controller (11) performs on-off control on the valves of the first valve (51) and the second valve (52) which are positioned on the oxidant rail control pipeline and the third valve (53) and the fourth valve (54) which are positioned on the fuel rail control pipeline according to the information of whether the fault valve exists or not, and propellant supply is performed in a mode that the valve on-off numbers of the oxidant rail control pipeline and the valve on the fuel rail control pipeline are consistent.
2. A method for controlling the supply of propellant in a propulsion system of a spacecraft, comprising the steps of:
s1, detecting the valve switch state: detecting whether a faulty valve which cannot be normally opened and closed exists in the first valve (51) and the second valve (52) or not through opening and closing operations of the first valve (51) and the second valve (52) and heating operations of the first heater (61) when the rail control pipeline is filled, and judging specific faults; detecting whether there is a failed valve which cannot be normally opened and closed in both the third valve (53) and the fourth valve (54) by opening and closing operations of the third valve (53) and the fourth valve (54) and heating operations of the second heater (62), and determining a specific failure; if the fault valve exists, the step S2 is carried out, and if the fault valve does not exist, the step S3 is directly carried out;
s2, fault valve processing: after the step S1, the controller (11) sends an instruction to reset the fault valve, then the step S1 is used for detecting again, if the fault of the fault valve still cannot be relieved, the propulsion and control interaction device (3) is restarted, then the controller (11) continues to send the instruction to reset the fault valve, the step S1 is used for detecting again, and then the step S3 is started in a state that the fault is eliminated or the fault still exists;
s3, propellant supply control: the controller (11) performs on-off control on the valves of the first valve (51) and the second valve (52) which are positioned on the oxidant rail control pipeline and the third valve (53) and the fourth valve (54) which are positioned on the fuel rail control pipeline according to the information of whether the fault valve exists or not, and propellant supply is performed in a mode that the valve on-off numbers of the oxidant rail control pipeline and the valve on the fuel rail control pipeline are consistent.
3. The spacecraft propulsion system propellant supply control method of claim 2, wherein in step S1, the operation step of determining that the open state and the closed state of the first valve (51) and the second valve (52) are both intact is: firstly, the first valve (51) is opened, the pressure values of the first pressure sensor (81) and the second pressure sensor (82) are the same, then the second valve (52) is opened and the first valve (51) is closed, the oxidant rail control pipeline is heated to a set value through the first heater (61), the pressure values of the second pressure sensor (82) and the first pressure sensor (81) are kept consistent in the heating process, then the second valve (52) and the first heater (61) are closed, and the pressure value of the second pressure sensor (82) is gradually reduced to the preset value.
4. The spacecraft propulsion system propellant supply control method of claim 2, wherein in step S1, the operation step of determining that the open state and the closed state of the third valve (53) and the fourth valve (54) are both intact is: firstly, the third valve (53) is opened, the pressure values of the third pressure sensor (83) and the fourth pressure sensor (84) are the same, then the fourth valve (54) is opened and the third valve (53) is closed, the fuel rail control pipeline is heated to a set value through the second heater (62), the pressure values of the fourth pressure sensor (84) and the third pressure sensor (83) are kept consistent in the heating process, then the fourth valve (54) and the second heater (62) are closed, and the pressure value of the fourth pressure sensor (84) is gradually reduced to the preset value.
5. The spacecraft propulsion system propellant supply control method according to claim 2, wherein in step S1, the operation step of determining that the first valve (51) cannot be normally opened and the second valve (52) can be normally opened and closed is: firstly, the first valve (51) is opened, the pressure value of the second pressure sensor (82) is unchanged, then the second valve (52) is opened, the pressure value of the second pressure sensor (82) is changed to be the same as the pressure value of the first pressure sensor (81), then the first valve (51) is closed, the oxidant rail-controlled pipeline is heated to a set value through the first heater (61), the pressure values of the second pressure sensor (82) and the first pressure sensor (81) are kept consistent in the heating process, finally, the second valve (52) and the first heater (6) are closed, and the pressure value of the second pressure sensor (82) is slowly reduced to a preset value.
6. The spacecraft propulsion system propellant supply control method according to claim 2, wherein in step S1, the operation step of determining that the third valve (53) cannot be normally opened and the fourth valve (54) can be normally opened and closed is: firstly, the third valve (53) is opened, the pressure value of the third pressure sensor (83) is unchanged, then the fourth valve (54) is opened, the pressure value of the fourth pressure sensor (84) is changed to be the same as the pressure value of the third pressure sensor (83), then the third valve (53) is closed, the fuel rail control pipeline is heated to a set value through the second heater (62), the pressure value of the fourth pressure sensor (84) and the pressure value of the third pressure sensor (83) are kept consistent in the heating process, finally, the fourth valve (54) and the second heater (62) are closed, and the pressure value of the fourth pressure sensor (84) is slowly reduced to a preset value.
7. The spacecraft propulsion system propellant supply control method according to claim 2, wherein in step S1, the operation step of determining that the second valve (52) cannot be normally opened and the first valve (51) can be normally opened and closed is: opening the first valve (51), wherein the pressure value of the first pressure sensor (81) is the same as that of the second pressure sensor (82), then opening the second valve (52) and closing the first valve (51), heating the oxidant rail control pipeline to a set value through the first heater (61), rapidly increasing the pressure value of the second pressure sensor (82) in the heating process, and immediately opening the first valve (51), wherein the pressure value of the second pressure sensor (82) is reduced to be the same as that of the first pressure sensor (81).
8. The spacecraft propulsion system propellant supply control method according to claim 2, wherein in step S1, the operation step of determining that the fourth valve (54) cannot be normally opened and the third valve (53) can be normally opened and closed is: opening the third valve (53), wherein the pressure value of the third pressure sensor (83) is the same as that of the fourth pressure sensor (84), then opening the fourth valve (54) and closing the third valve (53), heating the fuel rail control pipeline to a set value through the second heater (62), rapidly increasing the pressure value of the fourth pressure sensor (84) in the heating process, and immediately opening the third valve (53), wherein the pressure value of the fourth pressure sensor (84) is reduced to be the same as that of the third pressure sensor (83).
9. The spacecraft propulsion system propellant supply control method of claim 2, wherein in step S1, the operation step of determining that one of the first valve (51) and the second valve (52) cannot be normally closed is: opening the first valve (51), wherein the pressure value of the first pressure sensor (81) is the same as that of the second pressure sensor (82), then opening the second valve (52) and closing the first valve (51), heating the oxidant rail control pipeline to a set value through the first heater (61), keeping the pressure value of the second pressure sensor (82) and the pressure value of the first pressure sensor (81) consistent in the heating process, closing the second valve (52), and keeping the pressure value of the second pressure sensor (82) in the first pressure sensor (81) the same.
10. The spacecraft propulsion system propellant supply control method of claim 2, wherein in step S1, the operation step of determining that one of the third valve (53) and the fourth valve (54) cannot be normally closed is: opening the third valve (53), wherein the pressure value of the third pressure sensor (83) is the same as that of the fourth pressure sensor (84), then opening the fourth valve (54) and closing the third valve (53), heating the fuel rail control pipeline to a set value through the second heater (62), keeping the pressure value of the fourth pressure sensor (84) and the pressure value of the third pressure sensor (83) consistent in the heating process, and then closing the fourth valve (54), wherein the pressure value of the fourth pressure sensor (84) is kept the same as that of the third pressure sensor (83).
CN202211549518.1A 2022-12-05 2022-12-05 Rail control pipeline of spacecraft propulsion system and propellant supply control method thereof Pending CN116044608A (en)

Priority Applications (1)

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CN202211549518.1A CN116044608A (en) 2022-12-05 2022-12-05 Rail control pipeline of spacecraft propulsion system and propellant supply control method thereof

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CN202211549518.1A CN116044608A (en) 2022-12-05 2022-12-05 Rail control pipeline of spacecraft propulsion system and propellant supply control method thereof

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