CN111071487B - On-orbit autonomous management method and system for planetary probe propulsion system - Google Patents
On-orbit autonomous management method and system for planetary probe propulsion system Download PDFInfo
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Abstract
The invention provides an on-orbit autonomous management method and system for a planetary probe propulsion system, which comprise the following steps: the propulsion management unit collects working parameters of the propulsion system in real time and judges and identifies the failure mode of the propulsion system according to a set pressure or temperature threshold; completing the function of corresponding fault mode autonomous management through the identified fault mode; the failure modes of the propulsion system comprise the judgment and identification of failure modes of rail feeding control pipeline overpressure, attitude control pipeline overpressure, pressure reducing valve overpressure, propulsion system underpressure and thruster leakage; the functions of the autonomous management comprise rail control pipeline pressure relief autonomous management, attitude control pipeline pressure relief autonomous management, pressure reducing valve overpressure autonomous management, propulsion system underpressure autonomous management and thruster leakage autonomous management. The invention solves the problems of five main propulsion system failure modes and long-distance deep space detection instruction time delay, and provides guarantee for the high-reliability work of the long-distance planetary probe propulsion system.
Description
Technical Field
The invention relates to a method for on-orbit autonomous management, in particular to an on-orbit autonomous management method and a system for a planetary probe propulsion system, and more particularly to an on-orbit autonomous management method for a long-distance planetary probe propulsion system.
Background
The deep space exploration career is a must of international aerospace strong countries, long-distance planet exploration is one of important development directions of future deep space exploration tasks, and in recent years, exploration tasks such as mars, venus, water stars, wooden stars, comets, asteroids and the like are developed in the United states, Russia, Europe and Japan. Compared with the traditional lunar exploration task, the long-distance planetary exploration task has two special points, one of which is that the on-orbit flight time is long (the foreign Mars exploration flight time is more than 6 months to 1 year, and the Rosemata planetary detector flies on-orbit and even exceeds 10 years), and the on-orbit processing measures are provided for the long-term flight working reliability of the detector propulsion system, especially for the on-orbit processing measures of the fault modes of gas circuit, liquid circuit, engine pipeline pressure management, thruster leakage and the like of the long-term working of the propulsion system; the second problem is that the distance between the detector and the earth is far, so that the instruction delay is long, great difficulty is brought to earth interaction, and the above fault modes can not be interfered by the earth instruction and cannot be identified and processed in time, so that the task of the detector fails. At home and abroad, earth detectors and earth orbit satellite propulsion systems adopt ground interpretation remote measurement parameters (such as pressure, temperature and the like) for on-orbit fault management, manual analysis and identification are carried out, then instructions are injected for fault treatment, the problem of long time period exists, and the requirement of long-distance planetary detection cannot be met, so that a novel on-orbit autonomous management method must be designed specifically for on-orbit main fault modes of the propulsion subsystems.
The autonomous management failures related to the propulsion system are mainly: (1) rail control pipeline overpressure, (2) attitude control pipeline overpressure, (3) pressure reducing valve overpressure, (4) propulsion system underpressure, (5) thruster leakage, and the like. The overpressure of the rail control pipeline and the attitude control pipeline is mainly caused by the fact that after a rail attitude control engine finishes rail change work, an upstream self-locking valve is closed, the downstream of the self-locking valve and the inlet of the engine form a section of closed pipeline, and the pressure of a propellant in the closed pipeline can be increased along with the heat back immersion after the engine is shut down and the temperature change of the sun orientation in the flight process, so that potential danger is caused to a propulsion subsystem. The overpressure failure of the pressure reducing valve mainly refers to static pressure climbing of the pressure reducing valve, namely, the locking capacity of the pressure reducing valve is limited under the pressure of 30MPa or more in a high-pressure gas path, the situation that the pressure cannot meet the requirement that the pressure is always kept within a reasonable pressure range (generally about 1.8-1.9 MPa) in the long-time flight process can not occur, the underpressure failure of a propulsion system mainly aims at the pressure falling working process, a self-locking valve of an upstream high-pressure gas path module is closed, the gas path is cut off, the work is completed only by means of the air cushion pressure of a storage box, if an engine consumes too much propellant, the downstream pressure of the pressure reducing valve can be reduced, and the overpressure and underpressure problems can cause the. The leakage of the thruster is mainly the leakage of a solenoid valve at the head part of the thruster, so that the propellant in a propellant pipeline can continuously flow out through the leaked thruster, and the intuitive expression is that under the vacuum environment, the temperature of the head part of an engine can obviously drop (generally drops to-10 ℃) due to the throttling action, and the smooth execution of the attitude and orbit control task of a propulsion system can be influenced by the leakage of the thruster. Aiming at the fault modes, a novel on-orbit autonomous management method is developed and applied on a long-distance deep space probe, which is very necessary.
Patent document CN110071541A (application number: 201910268264.8) discloses a fully autonomous on-track management method for a deep space probe lithium ion battery pack, which includes a battery working and storage mode in a normal mode and a battery working and storage mode in the case of a single failure in the full-life working cycle of the lithium ion battery pack. In the on-track storage stage of the lithium ion storage battery pack, whether the storage battery pack is abnormal or not needs to be judged, if the battery is normal, whether the voltage of the storage battery pack is lower than a threshold value or not is judged, if the voltage of the storage battery pack is lower than the threshold value, the battery is charged, and if not, the original state is maintained. The lithium ion storage battery pack firstly judges whether the storage battery pack is abnormal or not in a charging management stage, if the battery is normal, whether the storage battery pack meets charging conditions or not is judged, if the battery meets the charging conditions, the battery is charged, otherwise, whether the charging ending conditions are met or not is judged, if the charging ending conditions are met, a charging disconnection instruction is sent to the battery to end charging, and if the charging ending conditions are not met, the original state is maintained.
Disclosure of Invention
In view of the deficiencies in the prior art, it is an object of the present invention to provide an on-orbit autonomous management method for a long-range planetary probe propulsion system.
According to the invention, the on-orbit autonomous management method for the long-distance planetary probe propulsion system comprises the following steps:
an identification step: the propulsion management unit collects working parameters of the propulsion system in real time and judges and identifies the failure mode of the propulsion system according to a pressure or temperature threshold value set by the propulsion management unit;
an autonomous management step: the propulsion system completes the function of corresponding fault mode autonomous management through the identified fault mode of the propulsion system;
the working parameters of the propulsion system comprise propulsion rail control pipeline pressure, attitude control pipeline pressure, pressure at the downstream of a pressure reducing valve, pressure at the downstream of a storage tank and head temperature of an attitude control thruster;
the failure modes of the propulsion system comprise the judgment and identification of failure modes of rail feeding control pipeline overpressure, attitude control pipeline overpressure, pressure reducing valve overpressure, propulsion system underpressure and thruster leakage;
the autonomous management function comprises rail control pipeline pressure relief autonomous management, attitude control pipeline pressure relief autonomous management, pressure reducing valve overpressure autonomous management, propulsion system underpressure autonomous management and thruster leakage autonomous management; and according to the autonomous management, the method comprises the steps of carrying out on-off control and/or attitude control thruster reconfiguration on a gas path valve and a liquid path valve of a propulsion system pipeline.
Preferably, the determining and identifying of the propulsion rail control line overpressure comprises: the readings of the oxidant rail control pipeline pressure sensor and the readings of the fuel rail control pipeline pressure sensor are both larger than a set threshold value in a sampling period of continuous preset values.
The judgment and identification of the overpressure of the attitude control pipeline comprise the following steps: the readings of the pressure sensors of the oxidant pipeline and the pressure sensor of the fuel pipeline of the main thruster and the backup thruster are both larger than a set threshold value in a continuous preset value sampling period.
The judgment and identification of the overpressure of the pressure reducing valve comprise the following steps: the readings of the pressure sensor at the downstream of the pressure reducing valve are all larger than a set threshold value in the sampling period of the continuous preset value.
The judging and identifying of the propulsion system under-pressure comprises the following steps: the sampling periods of the continuous preset values are all smaller than the set threshold value.
The judging and identifying of the thruster leakage comprises the following steps: the readings of the temperature sensor at the head of the attitude control thruster are lower than a set threshold value in a continuous preset value sampling period.
Preferably, rail accuse pipeline pressure release is from main management, appearance accuse pipeline pressure release is from main management including: and opening a liquid path valve at the upstream of the oxidant and fuel path to promote the high-temperature and high-pressure propellant to flow to the propellant storage tank, further reducing the pressure and temperature of the propulsion pipeline, and closing the liquid path valve of the oxidant and fuel path after the preset time.
The pressure relief valve overpressure autonomous management comprises: closing the high-pressure gas path management valve at the upstream of the pressure reducing valve, cutting off the high-pressure gas source, and opening the gas path management valve at the downstream of the pressure reducing valve to enable the gas to flow to the storage tank, so as to further reduce the pressure at the downstream of the pressure reducing valve, and closing the high-pressure gas path management valve and the low-pressure gas path management valve after reaching the preset time.
The propulsion system under-voltage autonomous management comprises: and opening the high-pressure air path management valve and the low-pressure air path management valve, pressurizing the storage tank, and closing the high-pressure air path management valve and the low-pressure air path management valve after the preset time is reached.
Preferably, the thruster leak autonomous management comprises: on-orbit real-time grouping management is carried out, when leakage occurs in a main thrust unit, an oxidant of a main attitude control thruster and a fuel pipeline self-locking valve are automatically closed, and only a backup thruster is adopted for working;
when the backup thruster unit leaks, the oxidant pipeline and the fuel self-locking valve of the backup attitude control thruster are automatically closed, and only the backup thruster is adopted for working;
when a plurality of leakage faults occur in the main attitude control thruster and the backup thruster simultaneously, the oxidant of the main attitude control thruster and the self-locking valve of the fuel pipeline are automatically closed, and only the backup thruster is adopted for working.
Preferably, the rail control pipeline pressure relief autonomous management, the attitude control pipeline pressure relief autonomous management, the pressure reducing valve overpressure autonomous management and the propulsion system underpressure autonomous management have an autonomous failure exit mode; the respective main management method comprises the steps of repeatedly judging the data of the pressure sensor, executing the autonomous management function again when the pressure cannot be recovered to be normal after the autonomous management function is executed, and independently quitting the autonomous management function when the pressure cannot be recovered to be normal.
According to the present invention there is provided an on-orbit autonomous management system for a planetary probe propulsion system, comprising:
an identification module: the propulsion management unit collects working parameters of the propulsion system in real time and judges and identifies the failure mode of the propulsion system according to a pressure or temperature threshold value set by the propulsion management unit;
an autonomous management module: the propulsion system completes the function of corresponding fault mode autonomous management through the identified fault mode of the propulsion system;
the working parameters of the propulsion system comprise propulsion rail control pipeline pressure, attitude control pipeline pressure, pressure at the downstream of a pressure reducing valve, pressure at the downstream of a storage tank and head temperature of an attitude control thruster;
the failure modes of the propulsion system comprise the judgment and identification of failure modes of rail feeding control pipeline overpressure, attitude control pipeline overpressure, pressure reducing valve overpressure, propulsion system underpressure and thruster leakage;
the autonomous management function comprises rail control pipeline pressure relief autonomous management, attitude control pipeline pressure relief autonomous management, pressure reducing valve overpressure autonomous management, propulsion system underpressure autonomous management and thruster leakage autonomous management; and according to the autonomous management, the method comprises the steps of carrying out on-off control and/or attitude control thruster reconfiguration on a gas path valve and a liquid path valve of a propulsion system pipeline.
Preferably, the determining and identifying of the propulsion rail control line overpressure comprises: the readings of the oxidant rail control pipeline pressure sensor and the readings of the fuel rail control pipeline pressure sensor are both larger than a set threshold value in a sampling period of continuous preset values.
The judgment and identification of the overpressure of the attitude control pipeline comprise the following steps: the readings of the pressure sensors of the oxidant pipelines and the pressure sensors of the fuel pipelines of the main thruster and the backup thruster are both larger than a set threshold value in a sampling period of continuous preset values;
the judgment and identification of the overpressure of the pressure reducing valve comprise the following steps: the readings of the pressure sensor at the downstream of the pressure reducing valve are all larger than a set threshold value in the sampling period of the continuous preset value.
The judging and identifying of the propulsion system under-pressure comprises the following steps: the readings of any set value number in the readings of the pressure sensor at the downstream of the storage tank are smaller than the set threshold value in the sampling period of the continuous preset value.
The judging and identifying of the thruster leakage comprises the following steps: the readings of the temperature sensor at the head of the attitude control thruster are lower than a set threshold value in a continuous preset value sampling period.
Preferably, rail accuse pipeline pressure release is from main management, appearance accuse pipeline pressure release is from main management including: and opening a liquid path valve at the upstream of the oxidant and fuel path to promote the high-temperature and high-pressure propellant to flow to the propellant storage tank, further reducing the pressure and temperature of the propulsion pipeline, and closing the liquid path valve of the oxidant and fuel path after the preset time.
The pressure relief valve overpressure autonomous management comprises: closing the high-pressure gas path management valve at the upstream of the pressure reducing valve, cutting off the high-pressure gas source, and opening the gas path management valve at the downstream of the pressure reducing valve to enable the gas to flow to the storage tank, so as to further reduce the pressure at the downstream of the pressure reducing valve, and closing the high-pressure gas path management valve and the low-pressure gas path management valve after reaching the preset time.
The propulsion system under-voltage autonomous management comprises: and opening the high-pressure air path management valve and the low-pressure air path management valve, pressurizing the storage tank, and closing the high-pressure air path management valve and the low-pressure air path management valve after the preset time is reached.
Preferably, the thruster leak autonomous management comprises: on-orbit real-time grouping management is carried out, when leakage occurs in a main thrust unit, an oxidant of a main attitude control thruster and a fuel pipeline self-locking valve are automatically closed, and only a backup thruster is adopted for working;
when the backup thruster unit leaks, the oxidant pipeline and the fuel self-locking valve of the backup attitude control thruster are automatically closed, and only the backup thruster is adopted for working;
when a plurality of leakage faults occur in the main attitude control thruster and the backup thruster simultaneously, the oxidant of the main attitude control thruster and the self-locking valve of the fuel pipeline are automatically closed, and only the backup thruster is adopted for working.
Preferably, the rail control pipeline pressure relief autonomous management, the attitude control pipeline pressure relief autonomous management, the pressure reducing valve overpressure autonomous management and the propulsion system underpressure autonomous management have an autonomous failure exit mode; the respective main management method comprises the steps of repeatedly judging the data of the pressure sensor, executing the autonomous management function again when the pressure cannot be recovered to be normal after the autonomous management function is executed, and independently quitting the autonomous management function when the pressure cannot be recovered to be normal.
Compared with the prior art, the invention has the following beneficial effects:
1. the five main on-orbit fault modes of the propulsion system are processed immediately through autonomous fault recognition and judgment on the propulsion system, so that the problem of difficult interaction among the propulsion system and the propulsion system caused by long time delay is solved;
2. the autonomous management program has a fault exit mechanism, and provides safety guarantee for the high-reliability work of the propulsion system;
3. the pressure and temperature judgment basis can be corrected according to experience, and the flexibility of an autonomous management control scheme is guaranteed.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a system schematic of a long range planetary exploration propulsion system.
Wherein, the device comprises a gas cylinder 1, a pressure reducing valve 2, an oxidant storage tank 3, a fuel storage tank 4, a rail-controlled engine 5, a main attitude control thruster unit 6 and a main attitude control thruster unit 7.
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 invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The technical problem to be solved by the invention is as follows: the method mainly comprises five management measures of rail control pipeline independent pressure relief, attitude control pipeline independent pressure relief, pressure reducing valve overpressure independent management, propulsion system underpressure independent management and thruster leakage independent management, realizes on-board real-time handling of a main on-rail fault mode of the propulsion system, has a safety mode of timely quitting faults, and ensures the reliability and safety of the long-distance planetary detector.
The technical solution of the invention is as follows: the pressure and temperature parameters are collected through the propulsion management unit, the fault mode is automatically identified and judged on the track, and a disposal instruction is automatically sent.
According to the invention, the on-orbit autonomous management method for the long-distance planetary probe propulsion system comprises the following steps:
an identification step: the propulsion management unit collects working parameters of the propulsion system in real time and judges and identifies the failure mode of the propulsion system according to a pressure or temperature threshold value set by the propulsion management unit;
an autonomous management step: the propulsion system completes the function of corresponding fault mode autonomous management through the identified fault mode of the propulsion system;
the propulsion management unit is a GNC and a data management system;
the working parameters of the propulsion system comprise propulsion rail control pipeline pressure, attitude control pipeline pressure, pressure at the downstream of a pressure reducing valve, pressure at the downstream of a storage tank and head temperature of an attitude control thruster;
the failure modes of the propulsion system comprise the judgment and identification of the failure modes of overpressure of a propulsion rail control pipeline, overpressure of an attitude control pipeline, overpressure of a pressure reducing valve, underpressure of the propulsion system and leakage of a thruster;
the autonomous management function comprises rail control pipeline pressure relief autonomous management, attitude control pipeline pressure relief autonomous management, pressure reducing valve overpressure autonomous management, propulsion system underpressure autonomous management and thruster leakage autonomous management; according to the fault management scheme set by the program, the on-off control of the gas circuit and liquid circuit valves of the pipeline of the propulsion system and the recombination of the attitude control thrusters are carried out, and the high-reliability working requirement of the propulsion system is met.
Specifically, the judging and identifying of the rail inlet control pipeline overpressure includes: the readings of the oxidant rail control pipeline pressure sensor and the fuel rail control pipeline pressure sensor are all larger than a set threshold value in three continuous sampling periods.
The judgment and identification of the overpressure of the attitude control pipeline comprise the following steps: readings of the pressure sensors of the oxidant pipeline and the fuel pipeline of the main thruster and the backup thruster are respectively greater than a set threshold value in three continuous sampling periods.
The judgment and identification of the overpressure of the pressure reducing valve comprise the following steps: the reading of the pressure sensor at the downstream of the pressure reducing valve is larger than the set threshold value in three continuous sampling periods.
The judging and identifying of the propulsion system under-pressure comprises the following steps: the pressure sensor reading (any 3 or 4) downstream of the tank is less than the set threshold for three consecutive sampling periods.
The judging and identifying of the thruster leakage comprises the following steps: the readings of the temperature sensor at the head of the attitude control thruster are lower than a set threshold value in three continuous sampling periods.
Specifically, rail accuse pipeline pressure release is from main management, appearance accuse pipeline pressure release is from main management including: and opening a liquid path valve at the upstream of the oxidant and fuel path to promote the high-temperature and high-pressure propellant to flow to the propellant storage tank, further reducing the pressure and temperature of the propulsion pipeline, and closing the liquid path valve of the oxidant and fuel path after the preset time.
The pressure relief valve overpressure autonomous management comprises: closing the high-pressure gas path management valve at the upstream of the pressure reducing valve, cutting off the high-pressure gas source, and opening the gas path management valve at the downstream of the pressure reducing valve to enable the gas to flow to the storage tank, so as to further reduce the pressure at the downstream of the pressure reducing valve, and closing the high-pressure gas path management valve and the low-pressure gas path management valve after reaching the preset time.
The propulsion system under-voltage autonomous management comprises: and opening the high-pressure air path management valve and the low-pressure air path management valve, pressurizing the storage tank, and closing the high-pressure air path management valve and the low-pressure air path management valve after the preset time is reached.
Specifically, the thruster leakage autonomous management comprises: on-orbit real-time grouping management is carried out, when leakage occurs in a main thrust unit, an oxidant of a main attitude control thruster and a fuel pipeline self-locking valve are automatically closed, and only a backup thruster is adopted for working;
when the backup thruster unit leaks, the oxidant pipeline and the fuel self-locking valve of the backup attitude control thruster are automatically closed, and only the backup thruster is adopted for working;
when a plurality of leakage faults occur in the main attitude control thruster and the backup thruster simultaneously, the oxidant of the main attitude control thruster and the self-locking valve of the fuel pipeline are automatically closed, and only the backup thruster is adopted for working.
Specifically, the rail control pipeline pressure relief autonomous management, the attitude control pipeline pressure relief autonomous management, the pressure reducing valve overpressure autonomous management and the propulsion system underpressure autonomous management have an autonomous failure exit mode; the respective main management method comprises the steps of repeatedly judging the data of the pressure sensor, executing the autonomous management function again when the pressure cannot be recovered to be normal after the autonomous management function is executed, and independently quitting the autonomous management function when the pressure cannot be recovered to be normal.
According to the invention, an on-orbit autonomous management system for a long-distance planetary probe propulsion system is provided, comprising:
an identification module: the propulsion management unit collects working parameters of the propulsion system in real time and judges and identifies the failure mode of the propulsion system according to a pressure or temperature threshold value set by the propulsion management unit;
an autonomous management module: the propulsion system completes the function of corresponding fault mode autonomous management through the identified fault mode of the propulsion system;
the propulsion management unit is a GNC and a data management system;
the working parameters of the propulsion system comprise propulsion rail control pipeline pressure, attitude control pipeline pressure, pressure at the downstream of a pressure reducing valve, pressure at the downstream of a storage tank and head temperature of an attitude control thruster;
the failure modes of the propulsion system comprise the judgment and identification of the failure modes of overpressure of a propulsion rail control pipeline, overpressure of an attitude control pipeline, overpressure of a pressure reducing valve, underpressure of the propulsion system and leakage of a thruster;
the autonomous management function comprises rail control pipeline pressure relief autonomous management, attitude control pipeline pressure relief autonomous management, pressure reducing valve overpressure autonomous management, propulsion system underpressure autonomous management and thruster leakage autonomous management; according to the fault management scheme set by the program, the on-off control of the gas circuit and liquid circuit valves of the pipeline of the propulsion system and the recombination of the attitude control thrusters are carried out, and the high-reliability working requirement of the propulsion system is met.
Specifically, the judging and identifying of the rail inlet control pipeline overpressure includes: the readings of the oxidant rail control pipeline pressure sensor and the fuel rail control pipeline pressure sensor are all larger than a set threshold value in three continuous sampling periods.
The judgment and identification of the overpressure of the attitude control pipeline comprise the following steps: readings of the pressure sensors of the oxidant pipeline and the fuel pipeline of the main thruster and the backup thruster are respectively greater than a set threshold value in three continuous sampling periods.
The judgment and identification of the overpressure of the pressure reducing valve comprise the following steps: the reading of the pressure sensor at the downstream of the pressure reducing valve is larger than the set threshold value in three continuous sampling periods.
The judging and identifying of the propulsion system under-pressure comprises the following steps: the pressure sensor reading (any 3 or 4) downstream of the tank is less than the set threshold for three consecutive sampling periods.
The judging and identifying of the thruster leakage comprises the following steps: the readings of the temperature sensor at the head of the attitude control thruster are lower than a set threshold value in three continuous sampling periods.
Specifically, rail accuse pipeline pressure release is from main management, appearance accuse pipeline pressure release is from main management including: and opening a liquid path valve at the upstream of the oxidant and fuel path to promote the high-temperature and high-pressure propellant to flow to the propellant storage tank, further reducing the pressure and temperature of the propulsion pipeline, and closing the liquid path valve of the oxidant and fuel path after the preset time.
The pressure relief valve overpressure autonomous management comprises: closing the high-pressure gas path management valve at the upstream of the pressure reducing valve, cutting off the high-pressure gas source, and opening the gas path management valve at the downstream of the pressure reducing valve to enable the gas to flow to the storage tank, so as to further reduce the pressure at the downstream of the pressure reducing valve, and closing the high-pressure gas path management valve and the low-pressure gas path management valve after reaching the preset time.
The propulsion system under-voltage autonomous management comprises: and opening the high-pressure air path management valve and the low-pressure air path management valve, pressurizing the storage tank, and closing the high-pressure air path management valve and the low-pressure air path management valve after the preset time is reached.
Specifically, the thruster leakage autonomous management comprises: on-orbit real-time grouping management is carried out, when leakage occurs in a main thrust unit, an oxidant of a main attitude control thruster and a fuel pipeline self-locking valve are automatically closed, and only a backup thruster is adopted for working;
when the backup thruster unit leaks, the oxidant pipeline and the fuel self-locking valve of the backup attitude control thruster are automatically closed, and only the backup thruster is adopted for working;
when a plurality of leakage faults occur in the main attitude control thruster and the backup thruster simultaneously, the oxidant of the main attitude control thruster and the self-locking valve of the fuel pipeline are automatically closed, and only the backup thruster is adopted for working.
Specifically, the rail control pipeline pressure relief autonomous management, the attitude control pipeline pressure relief autonomous management, the pressure reducing valve overpressure autonomous management and the propulsion system underpressure autonomous management have an autonomous failure exit mode; the respective main management method comprises the steps of repeatedly judging the data of the pressure sensor, executing the autonomous management function again when the pressure cannot be recovered to be normal after the autonomous management function is executed, and independently quitting the autonomous management function when the pressure cannot be recovered to be normal.
The present invention is further described in detail by the following preferred examples:
(1) the method comprises the following steps of automatically decompressing the rail control pipeline: the propulsion management unit collects data of pressure sensors of an oxidant and a fuel rail control pipeline of the propulsion system, judges overpressure according to the upper limit of the pressure of the rail control pipeline, which can work reliably, of the propulsion system, and sends an opening instruction of a self-locking valve of the oxidant rail control pipeline and the fuel rail control pipeline to perform autonomous pressure relief after the upper limit of the pressure of the rail control pipeline of the propulsion system is exceeded. The rail control pipeline automatic pressure relief program also has a fault exit function, namely the function can be automatically judged and exited if the rail fails.
(2) The automatic pressure relief step of the attitude control pipeline comprises the following steps: the propulsion management unit collects data of pressure sensors of an oxidant and a fuel attitude control pipeline of the propulsion system, judges overpressure according to the upper limit of the pressure of the attitude control pipeline which can work reliably of the propulsion system, and sends opening instructions of self-locking valves of the oxidant attitude control pipeline and the fuel attitude control pipeline to perform autonomous pressure relief after the upper limit of the pressure of the attitude control pipeline of the propulsion system is exceeded. The automatic pressure relief program of the attitude control pipeline also has a fault exit function, namely the function can be automatically judged and exited if the fault occurs on the track.
(3) The pressure reducing valve overpressure automatic management method comprises the following steps: the method comprises the steps that a propulsion management unit collects data of a pressure sensor at the downstream of a pressure reducing valve of a propulsion system, overpressure judgment is carried out according to the static pressure climbing upper limit of the pressure reducing valve which can reliably work in the propulsion system, and when the data exceed the upper limit of the downstream pressure of the pressure reducing valve of the propulsion system, an opening instruction of a self-locking valve of a downstream gas path of the pressure reducing valve is sent to carry out autonomous. The overpressure automatic management program of the pressure reducing valve also has a fault exit function, namely the function can be automatically judged and exited if an on-track fault occurs.
(4) The propulsion system undervoltage autonomous management method comprises the following steps: the propulsion management unit collects data of a pressure sensor at the downstream of a storage tank of the propulsion system, performs under-pressure judgment according to the lower limit of system pressure at which the propulsion system can reliably work, and sends an opening instruction of a self-locking valve of an upstream gas path of the storage tank to perform system pressure compensation after the pressure is lower than the lower limit of the pressure at which the propulsion system can reliably work. The undervoltage autonomous management program of the propulsion system also has a fault exit function, namely the function can be automatically judged and exited if an on-track fault occurs.
(5) The self-management of the thruster leakage comprises the following steps: the method comprises the steps that a propulsion management unit collects data of a temperature sensor at the head of an attitude control thruster of a propulsion system, judges the leakage fault of the thruster according to the lower limit of the temperature of the head of the thrust system after the attitude control thruster leaks, closes a fault thruster and a liquid path self-locking valve at the upper stream of the group of thrusters when the temperature is lower than the lower limit of the temperature of the thruster, and switches to a backup attitude control thruster unit to perform subsequent tasks. The self-management program for the leakage of the thruster also has a fault exit function, namely the function can be automatically judged and exited if the fault occurs on the track.
As shown in figure 1, the long-distance deep space probe propulsion system comprises a gas cylinder 1, a pressure reducing valve 2, an oxidant storage tank 3, a fuel storage tank 4, a rail-controlled engine 5, a main attitude control thruster unit 6, a main attitude control thruster unit 7, a high-pressure gas path module self-locking valve LV1, a low-pressure gas path module oxidant path self-locking valve LV3, a low-pressure gas path module fuel path self-locking valve LV4, a main attitude control thruster oxidant path self-locking valve LV5, a main attitude control thruster fuel path self-locking valve LV6, an oxidant rail control line self-locking valve LV7, a fuel rail control line self-locking valve 8, a backup attitude control thruster oxidant line self-locking thrust valve LV9, a backup attitude control thruster fuel path self-locking valve LV10, a high-pressure sensor P1, a pressure sensor P2 downstream of the pressure reducing valve, a pressure sensor P3 downstream of the 1# oxidant storage tank, a pressure sensor P5 downstream of the 2# oxidant storage tank, The system comprises a No. 1 oxidant storage tank downstream pressure sensor P4, a No. 2 oxidant storage tank downstream pressure sensor P6, an oxidant rail control pipeline pressure sensor P7, a fuel rail control pipeline pressure sensor P8, a main attitude control thruster oxidant pipeline pressure sensor P9, a main attitude control thruster fuel pipeline pressure sensor P10, a backup attitude control thruster oxidant pipeline pressure sensor P11, a backup attitude control thruster fuel pipeline pressure sensor P12, main thruster unit head temperature sensors TA 1-TAN, backup thruster unit head temperature sensors TB 1-TBn and the like. Reasonable ranges for the propulsion system pressure and temperature parameters should be: the downstream pressure of the pressure reducing valve is 1.8-1.9 MPa, the pressure of the rail control pipeline and the attitude control pipeline is 1.5-1.8 MPa, the pressure of a storage tank of the propulsion system is 1.8MPa, and the working temperature of the attitude control thruster is more than 0 ℃.
Rail-controlled pipeline pressure relief autonomous management embodiment 1
(1) The method comprises the following steps that a propulsion management unit collects readings of an oxidant rail control pipeline pressure sensor P7 or a fuel rail control pipeline pressure sensor P8 of a propulsion system in real time, and fault identification and judgment are carried out according to an autonomous management program;
(2) when the pressure sensor P7 of the oxidant rail control pipeline exceeds the set threshold value by 2.8MPa for the first time (three continuous sampling periods all exceed the set threshold value, the value is verified by on-orbit test data of satellites, ChangE and the like, and can also be subjected to upper note modification according to on-orbit actual conditions, and the following threshold values are also the same), the valve LV7 of the oxidant rail control pipeline is opened, and the valve LV7 is closed after 5 s; when the fuel rail control pipeline pressure sensor P8 exceeds the set threshold value for the first time by 2.8MPa (three continuous sampling periods all exceed the set threshold value, and can carry out injection modification according to the on-rail condition), the fuel rail control pipeline valve LV8 is opened, and the valve LV8 is closed after 5 s;
(3) through on-satellite autonomous judgment: if P7 and P8 still exceed the set pressure threshold after step (2) is performed, step (2) is performed again;
(4) through on-satellite autonomous judgment: and (4) if the pressure values P7 and P8 still exceed the set pressure threshold value after the step (3) is implemented, judging that the rail control pipeline pressure sensors P7 and P8 are failed, and automatically quitting the pressure relief function of the rail control pipeline on the satellite.
Attitude control pipeline pressure relief autonomous management embodiment 2
(1) When the main set works, the propulsion management unit collects readings of an oxidant pipeline pressure sensor P9 and a fuel pipeline pressure sensor P10 of a main attitude control thruster of the propulsion system in real time and carries out fault identification and judgment according to an autonomous management program;
(2) when the pressure sensor P9 of the oxidant pipeline of the main attitude control thruster exceeds the set threshold value of 2.8MPa for the first time (three continuous sampling periods all exceed the set threshold value), opening the self-locking valve LV5 of the oxidant pipeline of the main attitude control thruster, and closing the valve LV5 after 10 s; when the pressure sensor P10 of the fuel pipeline of the main attitude control thruster exceeds the set threshold value for the first time by 2.8MPa (three continuous sampling periods all exceed the set threshold value), opening the self-locking valve LV6 of the fuel pipeline of the main attitude control thruster, and closing the valve LV6 after 10 s;
(3) through on-satellite autonomous judgment: if P9 and P10 still exceed the set pressure threshold after step (2) is performed, step (2) is performed again.
(4) Through on-satellite autonomous judgment: and (4) if the pressure sensors P9 and P10 still exceed the set pressure threshold after the step (3) is implemented, judging that the pressure sensors P9 and P10 of the oxidant pipeline of the main attitude control thruster are out of service, and automatically exiting the pressure relief autonomous management function of the attitude control pipeline on the satellite.
(5) When the working unit is a backup unit, the propulsion management unit collects readings of an oxidant pipeline pressure sensor P11 and a fuel pipeline pressure sensor P12 of a backup attitude control thruster of the propulsion system in real time and carries out fault identification and judgment according to an autonomous management program;
(6) when the pressure sensor P11 of the oxidant pipeline of the backup attitude control thruster exceeds the set threshold value of 2.8MPa for the first time (three continuous sampling periods all exceed the set threshold value), opening the self-locking valve LV9 of the oxidant pipeline of the backup attitude control thruster, and closing the valve LV9 after 10 s; when the pressure sensor P12 of the fuel pipeline of the backup attitude control thruster exceeds the set threshold value for the first time by 2.8MPa (three continuous sampling periods all exceed the set threshold value), opening the self-locking valve LV10 of the fuel pipeline of the backup attitude control thruster, and closing the valve LV10 after 10 s;
(7) through on-satellite autonomous judgment: if P11 and P12 still exceed the set pressure threshold after step (6) is performed, step (6) is performed again.
(8) Through on-satellite autonomous judgment: and (4) if the pressure sensors P11 and P12 still exceed the set pressure threshold after the step (7) is implemented, judging that the pressure sensors P11 and P12 of the oxidant pipeline of the backup attitude control thruster fail, and automatically exiting the pressure relief autonomous management function of the attitude control pipeline on the satellite.
Pressure relief valve overpressure autonomous management embodiment 3
(1) The propulsion management unit collects readings of a pressure sensor P2 at the downstream of a pressure reducing valve of the propulsion system in real time and carries out fault identification and judgment according to an autonomous management program;
(2) when the reading of the downstream outlet pressure sensor P2 of the reducing valve is more than 2.2MPa (three continuous sampling periods), closing the high-pressure self-locking valve LV1 of the high-pressure gas circuit module, cutting off the supply of the upstream high-pressure gas, simultaneously opening the oxidant self-locking valve LV3 and the fuel self-locking valve LV4 of the low-pressure gas circuit module, closing the small-flow self-locking valves LV3 and LV4 of the gas circuit after 200s, and completing the pressure balance of the low-pressure gas circuit.
(3) Through on-satellite autonomous judgment: if P2 still exceeds the set pressure threshold after step (2) is performed, step (2) is performed again.
(4) Through on-satellite autonomous judgment: and (4) if the pressure P2 still exceeds the set pressure threshold after the step (3) is carried out, judging that the pressure sensor P2 downstream of the pressure reducing valve fails, and automatically exiting the overpressure self-management function of the pressure reducing valve on the satellite.
Propulsion system undervoltage autonomous management embodiment 4
(1) The propulsion management unit collects readings of pressure sensors P3, PZ4, PZ5 and PZ6 of the oxidant storage tank and the fuel storage tank in real time and carries out fault identification and judgment according to an autonomous management program;
(2) when the readings of any 3 or 4 of the pressure sensors P3-P6 at the downstream outlet of the storage tank are lower than 1.7MPa (three continuous sampling periods), the high-pressure self-locking valve LV1 and the self-locking valves LV3 and LV4 are opened to pressurize the storage tank, and after 200s, the high-pressure self-locking valve LV1 and the self-locking valves LV3 and LV4 are closed.
(3) Through on-satellite autonomous judgment: if (any 3 or 4) of the P3-P6 are still lower than the set pressure threshold after the step (2) is performed, the step (2) is executed again.
(4) Through on-satellite autonomous judgment: if any 3 or 4 of the pressure sensors P3-P6 are still lower than the set pressure threshold after the step (3) is implemented, judging that at least 3 of the pressure sensors P3-P6 at the downstream of the storage tank fail, and automatically quitting the function of the undervoltage autonomous management of the propulsion system on the satellite.
Thruster leak autonomous management example 5
(1) The method comprises the steps that a propulsion management unit autonomously interprets readings of TA 1-TAN and TB 1-TBn of a head temperature sensor of a main thruster unit of the propulsion system, which are acquired in real time on the satellite, and if one or more values of TA 1-TAN or TA 1-TANTB 1-TBn are lower than-10 ℃ (in three continuous sampling periods), the corresponding thruster is judged to be leaked, and then the propulsion management unit autonomously recombines the thruster unit according to the judgment;
(2) if one or more of the main attitude control thrusters (A1-An) has a fault, the self-locking valve LV5 of the oxidant pipeline of the main attitude control thrusters and the self-locking valve LV6 of the fuel pipeline of the main attitude control thrusters are automatically closed, and only the backup thrusters (B1-Bn) are adopted for working;
(3) if one or more backup thrusters (B1-Bn) have faults, the self-locking valve LV9 of the oxidant pipeline of the backup attitude control thruster and the self-locking valve LV10 of the fuel pipeline of the backup attitude control thruster are automatically closed, and only the backup thrusters (A1-An) are adopted for working;
(4) if a plurality of leakage faults occur in the main share thruster and the backup thruster (A1-An and B1-Bn), the self-locking valve LV5 of the oxidant pipeline of the main share attitude control thruster and the self-locking valve LV6 of the fuel pipeline of the main share attitude control thruster are automatically closed, and the backup thrusters (B1-Bn) are only adopted for working.
In the description of the present application, it is to 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 those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
Those skilled in the art will appreciate that, in addition to implementing the systems, apparatus, and various modules thereof provided by the present invention in purely computer readable program code, the same procedures can be implemented entirely by logically programming method steps such that the systems, apparatus, and various modules thereof are provided in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system, the device and the modules thereof provided by the present invention can be considered as a hardware component, and the modules included in the system, the device and the modules thereof for implementing various programs can also be considered as structures in the hardware component; modules for performing various functions may also be considered to be both software programs for performing the methods and structures within hardware components.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. An on-orbit autonomous management method for a planetary probe propulsion system, comprising:
an identification step: the propulsion management unit collects working parameters of the propulsion system in real time and judges and identifies the failure mode of the propulsion system according to a pressure or temperature threshold value set by the propulsion management unit;
an autonomous management step: the propulsion system completes corresponding fault mode autonomous management through the identified fault mode of the propulsion system;
the working parameters of the propulsion system comprise propulsion rail control pipeline pressure, attitude control pipeline pressure, pressure at the downstream of a pressure reducing valve, pressure at the downstream of a storage tank and head temperature of an attitude control thruster;
the failure modes of the propulsion system comprise the judgment and identification of the failure modes of overpressure of a propulsion rail control pipeline, overpressure of an attitude control pipeline, overpressure of a pressure reducing valve, underpressure of the propulsion system and leakage of a thruster;
the automatic management comprises rail control pipeline pressure relief automatic management, attitude control pipeline pressure relief automatic management, pressure reducing valve overpressure automatic management, propulsion system underpressure automatic management and thruster leakage automatic management; and according to the autonomous management, the method comprises the steps of carrying out on-off control and/or attitude control thruster reconfiguration on a gas path valve and a liquid path valve of a propulsion system pipeline.
2. The method of claim 1, wherein the determining and identifying of propulsion orbit management overpressure comprises: the readings of the oxidant rail control pipeline pressure sensor and the readings of the fuel rail control pipeline pressure sensor are both larger than a set threshold value in a sampling period of continuous preset values;
the judgment and identification of the overpressure of the attitude control pipeline comprise the following steps: the readings of the pressure sensors of the oxidant pipelines and the pressure sensors of the fuel pipelines of the main thruster and the backup thruster are both larger than a set threshold value in a sampling period of continuous preset values;
the judgment and identification of the overpressure of the pressure reducing valve comprise the following steps: the readings of the downstream pressure sensor of the pressure reducing valve are all larger than a set threshold value in the sampling period of the continuous preset value;
the judging and identifying of the propulsion system under-pressure comprises the following steps: the number of readings of any set value in the readings of the pressure sensor at the downstream of the storage tank is smaller than a set threshold value in a continuous preset value sampling period;
the judging and identifying of the thruster leakage comprises the following steps: the readings of the temperature sensor at the head of the attitude control thruster are lower than a set threshold value in a continuous preset value sampling period.
3. The on-orbit autonomous management method for a planetary probe propulsion system according to claim 1, wherein the on-orbit autonomous management of pressure relief of the on-orbit pipeline and the self-management of pressure relief of the attitude control pipeline comprise: opening liquid path valves at the upstream of the oxidant and fuel paths to promote the high-temperature and high-pressure propellant to flow to a propellant storage tank, further reducing the pressure and temperature of a propelling pipeline, and closing the liquid path valves of the oxidant and fuel paths after reaching preset time;
the pressure relief valve overpressure autonomous management comprises: closing a high-pressure gas path management valve at the upstream of the pressure reducing valve, cutting off a high-pressure gas source, and opening a gas path management valve at the downstream of the pressure reducing valve to enable gas to flow to a storage tank so as to reduce the pressure at the downstream of the pressure reducing valve, and closing the high-pressure gas path management valve and the low-pressure gas path management valve after a preset time is reached;
the propulsion system under-voltage autonomous management comprises: and opening the high-pressure air path management valve and the low-pressure air path management valve, pressurizing the storage tank, and closing the high-pressure air path management valve and the low-pressure air path management valve after the preset time is reached.
4. The on-orbit autonomous management method for a planetary probe propulsion system according to claim 1, wherein the thruster leak autonomous management comprises: on-orbit real-time grouping management is carried out, when leakage occurs in a main thrust unit, an oxidant of a main attitude control thruster and a fuel pipeline self-locking valve are automatically closed, and only a backup thruster is adopted for working;
when the backup thruster unit leaks, the oxidant pipeline and the fuel self-locking valve of the backup attitude control thruster are automatically closed, and only the backup thruster is adopted for working;
when a plurality of leakage faults occur in the main attitude control thruster and the backup thruster simultaneously, the oxidant of the main attitude control thruster and the self-locking valve of the fuel pipeline are automatically closed, and only the backup thruster is adopted for working.
5. The on-orbit autonomous management method for the planetary probe propulsion system according to claim 1, wherein the on-orbit autonomous management of pressure relief of the orbit control pipeline, the autonomous management of pressure relief of the attitude control pipeline, the autonomous management of overpressure of the pressure relief valve, and the autonomous management of undervoltage of the propulsion system have an autonomous failure exit mode; the respective main management method comprises the steps of repeatedly judging the data of the pressure sensor, executing the autonomous management again when the pressure can not be recovered to be normal after the autonomous management is executed, and independently quitting the autonomous management when the pressure can not be recovered to be normal.
6. An on-orbit autonomous management system for a planetary probe propulsion system, comprising:
an identification module: the propulsion management unit collects working parameters of the propulsion system in real time and judges and identifies the failure mode of the propulsion system according to a pressure or temperature threshold value set by the propulsion management unit;
an autonomous management module: the propulsion system completes corresponding fault mode autonomous management through the identified fault mode of the propulsion system;
the working parameters of the propulsion system comprise propulsion rail control pipeline pressure, attitude control pipeline pressure, pressure at the downstream of a pressure reducing valve, pressure at the downstream of a storage tank and head temperature of an attitude control thruster;
the failure modes of the propulsion system comprise the judgment and identification of the failure modes of overpressure of a propulsion rail control pipeline, overpressure of an attitude control pipeline, overpressure of a pressure reducing valve, underpressure of the propulsion system and leakage of a thruster;
the automatic management comprises rail control pipeline pressure relief automatic management, attitude control pipeline pressure relief automatic management, pressure reducing valve overpressure automatic management, propulsion system underpressure automatic management and thruster leakage automatic management; and according to the autonomous management, the method comprises the steps of carrying out on-off control and/or attitude control thruster reconfiguration on a gas path valve and a liquid path valve of a propulsion system pipeline.
7. An on-orbit autonomous management system for a planetary probe propulsion system according to claim 6, characterized in that the determination and identification of the on-orbit control piping overpressure comprises: the readings of the oxidant rail control pipeline pressure sensor and the readings of the fuel rail control pipeline pressure sensor are both larger than a set threshold value in a sampling period of continuous preset values;
the judgment and identification of the overpressure of the attitude control pipeline comprise the following steps: the readings of the pressure sensors of the oxidant pipelines and the pressure sensors of the fuel pipelines of the main thruster and the backup thruster are both larger than a set threshold value in a sampling period of continuous preset values;
the judgment and identification of the overpressure of the pressure reducing valve comprise the following steps: the readings of the downstream pressure sensor of the pressure reducing valve are all larger than a set threshold value in the sampling period of the continuous preset value;
the judging and identifying of the propulsion system under-pressure comprises the following steps: the number of readings of any set value in the readings of the pressure sensor at the downstream of the storage tank is smaller than a set threshold value in a continuous preset value sampling period;
the judging and identifying of the thruster leakage comprises the following steps: the readings of the temperature sensor at the head of the attitude control thruster are lower than a set threshold value in a continuous preset value sampling period.
8. An on-orbit autonomous management system for a planetary probe propulsion system according to claim 6, wherein the on-orbit and attitude control pipeline pressure relief autonomous management comprises: opening liquid path valves at the upstream of the oxidant and fuel paths to promote the high-temperature and high-pressure propellant to flow to a propellant storage tank, further reducing the pressure and temperature of a propelling pipeline, and closing the liquid path valves of the oxidant and fuel paths after reaching preset time;
the pressure relief valve overpressure autonomous management comprises: closing a high-pressure gas path management valve at the upstream of the pressure reducing valve, cutting off a high-pressure gas source, and opening a gas path management valve at the downstream of the pressure reducing valve to enable gas to flow to a storage tank so as to reduce the pressure at the downstream of the pressure reducing valve, and closing the high-pressure gas path management valve and the low-pressure gas path management valve after a preset time is reached;
the propulsion system under-voltage autonomous management comprises: and opening the high-pressure air path management valve and the low-pressure air path management valve, pressurizing the storage tank, and closing the high-pressure air path management valve and the low-pressure air path management valve after the preset time is reached.
9. An on-orbit autonomous management system for a planetary probe propulsion system according to claim 6, wherein the thruster leak autonomous management comprises: on-orbit real-time grouping management is carried out, when leakage occurs in a main thrust unit, an oxidant of a main attitude control thruster and a fuel pipeline self-locking valve are automatically closed, and only a backup thruster is adopted for working;
when the backup thruster unit leaks, the oxidant pipeline and the fuel self-locking valve of the backup attitude control thruster are automatically closed, and only the backup thruster is adopted for working;
when a plurality of leakage faults occur in the main attitude control thruster and the backup thruster simultaneously, the oxidant of the main attitude control thruster and the self-locking valve of the fuel pipeline are automatically closed, and only the backup thruster is adopted for working.
10. The on-orbit autonomous management system for a planetary probe propulsion system according to claim 6, wherein the on-orbit autonomous management of pressure relief of the orbit control pipeline, the autonomous management of pressure relief of the attitude control pipeline, the autonomous management of overpressure of the pressure relief valve, and the autonomous management of undervoltage of the propulsion system have an autonomous failure exit mode; the respective main management method comprises the steps of repeatedly judging the data of the pressure sensor, executing the autonomous management again when the pressure can not be recovered to be normal after the autonomous management is executed, and independently quitting the autonomous management when the pressure can not be recovered to be normal.
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| CN112693632B (en) * | 2020-12-25 | 2021-09-21 | 上海空间推进研究所 | Method and system for adjusting and compensating on-orbit performance of spacecraft propulsion system |
| CN112983679B (en) * | 2021-05-06 | 2021-08-17 | 星河动力(北京)空间科技有限公司 | Carrier rocket upper-stage propulsion system and carrier rocket |
| CN113790912B (en) * | 2021-08-19 | 2024-03-19 | 上海卫星工程研究所 | Spacecraft propulsion system attitude and orbit control pipeline overpressure autonomous management test method and system |
| CN114291297B (en) * | 2021-12-20 | 2023-05-16 | 上海空间推进研究所 | Lunar surface launching aircraft propulsion system |
| CN114455102A (en) * | 2022-01-25 | 2022-05-10 | 上海卫星工程研究所 | On-orbit leakage autonomous processing method and system for deep space probe double-component thruster |
| CN114625153B (en) * | 2022-03-07 | 2023-02-03 | 中国西安卫星测控中心 | Satellite orbit control process evaluation method based on variable temperature and attitude and orbit control ratio characteristics |
| CN116754138B (en) * | 2023-08-21 | 2023-11-03 | 东方空间技术(山东)有限公司 | Leakage detection method of final-repair attitude control power system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104564574A (en) * | 2013-10-10 | 2015-04-29 | 波音公司 | Methods and systems for estimation of propellant transfer in an ion propulsion system |
| US9522746B1 (en) * | 2015-08-27 | 2016-12-20 | The Boeing Company | Attitude slew methodology for space vehicles using gimbaled low-thrust propulsion subsystem |
| CN106428649A (en) * | 2016-10-26 | 2017-02-22 | 中国运载火箭技术研究院 | Automatic support system for reusable carriers |
| CN108408083A (en) * | 2018-03-02 | 2018-08-17 | 北京空间技术研制试验中心 | Manned spacecraft risk prevention system method in orbit |
| CN109307598A (en) * | 2018-11-11 | 2019-02-05 | 上海空间推进研究所 | Fault identification pulse operation engine propellant flow rate bimodulus measurement method and device |
| CN109630317A (en) * | 2018-12-06 | 2019-04-16 | 上海空间推进研究所 | Rail attitude control integration space propulsion system based on electrodynamic pump |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9115662B1 (en) * | 2009-07-10 | 2015-08-25 | The Boeing Company | Health-adaptive reaction control system |
-
2019
- 2019-12-20 CN CN201911330189.XA patent/CN111071487B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104564574A (en) * | 2013-10-10 | 2015-04-29 | 波音公司 | Methods and systems for estimation of propellant transfer in an ion propulsion system |
| US9522746B1 (en) * | 2015-08-27 | 2016-12-20 | The Boeing Company | Attitude slew methodology for space vehicles using gimbaled low-thrust propulsion subsystem |
| CN106428649A (en) * | 2016-10-26 | 2017-02-22 | 中国运载火箭技术研究院 | Automatic support system for reusable carriers |
| CN108408083A (en) * | 2018-03-02 | 2018-08-17 | 北京空间技术研制试验中心 | Manned spacecraft risk prevention system method in orbit |
| CN109307598A (en) * | 2018-11-11 | 2019-02-05 | 上海空间推进研究所 | Fault identification pulse operation engine propellant flow rate bimodulus measurement method and device |
| CN109630317A (en) * | 2018-12-06 | 2019-04-16 | 上海空间推进研究所 | Rail attitude control integration space propulsion system based on electrodynamic pump |
Non-Patent Citations (2)
| Title |
|---|
| 空间推进系统故障诊断与自主管理技术研究;彭小辉;《国防科学技术大学硕士论文》;20091101;全文 * |
| 空间推进系统故障诊断专家系统研究;张纯良等;《航空动力学报》;20041030;全文 * |
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