An on-orbit intelligent propulsion method and device of an ion thruster, a storage medium and a terminal

Abstract

The application relates to an on-orbit intelligent propulsion method and device of an ion thruster, a storage medium and a terminal. The method comprises the following steps: collecting test fault data and key characteristic parameters of the ion thruster; establishing an adaptive triggering mechanism of the ion thruster according to the test fault data; performing index deviation judgment on the ion thruster according to the key characteristic parameters; if the index deviation judgment is passed, performing key performance change judgment and beam current change judgment on the ion thruster according to the key characteristic parameters to obtain a judgment result of the ion thruster; and adjusting the running state of the ion thruster according to the judgment result and the adaptive triggering mechanism. The application establishes the adaptive triggering mechanism of the ion thruster, and realizes the on-orbit intelligent propulsion function of the ion thruster.

Description

Technical Field

[0001] The present invention relates to the field of aerospace propulsion technology, and more specifically, to an on-orbit intelligent propulsion method, device, storage medium and terminal for an ion thruster. Background Art

[0002] At present, the working mechanism of ion thrusters in various countries around the world during their in-orbit operation is completely subject to the external environment or internal factors, and ion thrusters do not have the ability to self-regulate.

[0003] For future deep space exploration missions, when spacecraft are orbiting far from Earth, the transmission of control commands will take several hours. In the event of a spacecraft deviating from its orbit or approaching a collision with an unknown celestial body, real-time communication will be impossible. In such cases, the spacecraft lacks intelligent propulsion capabilities and cannot adjust thrust vectors in time to avoid mission failure. Summary of the Invention

[0004] The embodiments of the present application provide an on-orbit intelligent propulsion method, apparatus, storage medium, and terminal for an ion thruster. To provide a basic understanding of some aspects of the disclosed embodiments, a brief summary is provided below. This summary is not intended to be a comprehensive review, identify key or important components, or delineate the scope of protection for these embodiments. Its sole purpose is to present some concepts in a simplified form, serving as a prelude to the detailed description that follows.

[0005] In a first aspect, an embodiment of the present application provides an on-orbit intelligent propulsion method for an ion thruster, the method comprising:

[0006] Collect test failure data and key characterization parameters of ion thrusters;

[0007] establishing an adaptive triggering mechanism for the ion thruster based on the test fault data;

[0008] Performing index deviation judgment on the ion thruster according to the key characterization parameters;

[0009] If the indicator deviation judgment is passed, performing a key performance change judgment and a beam current change judgment on the ion thruster according to the key characterization parameters to obtain a judgment result of the ion thruster;

[0010] The operating state of the ion thruster is adjusted according to the judgment result and the adaptive trigger mechanism.

[0011] Optionally, collecting test fault data of the ion thruster includes:

[0012] Collect ground test data, test failure statistics and experimental failure analysis data of ion thrusters;

[0013] The ground test data, the test failure statistical data and the experimental failure analysis data are used as test failure data of the ion thruster.

[0014] Optionally, establishing an adaptive triggering mechanism for the ion thruster according to the test fault data includes:

[0015] Establishing a parameter change-fault cause correspondence table of the ion thruster according to the test fault data;

[0016] Based on the parameter change-fault cause correspondence table, an adaptive triggering mechanism for the ion thruster is established.

[0017] Optionally, the performing indicator deviation judgment on the ion thruster according to the key characterization parameters includes:

[0018] The indicator deviation of the ion thruster is judged based on the key characterization parameters and the preset indicator deviation threshold.

[0019] Optionally, performing key performance change judgment and beam current change judgment on the ion thruster according to the key characterization parameters to obtain a judgment result of the ion thruster includes:

[0020] performing a key performance change judgment on the ion thruster according to the key characterization parameters to obtain a performance change judgment result of the ion thruster;

[0021] performing beam current variation judgment on the ion thruster according to the key characterization parameters to obtain a beam current variation judgment result of the ion thruster;

[0022] The performance change determination result and the beam current change determination result are used as the determination result of the ion thruster.

[0023] Optionally, adjusting the operating state of the ion thruster according to the judgment result and the adaptive trigger mechanism includes:

[0024] determining an adjustment instruction for the ion thruster according to the judgment result and the adaptive trigger mechanism;

[0025] According to the adjustment instruction, the operating state of the ion thruster is adjusted.

[0026] Optionally, further comprising:

[0027] If the indicator deviation interpretation fails, the process returns to continue collecting the key characterization parameters of the ion thruster.

[0028] In a second aspect, an embodiment of the present application provides an on-orbit intelligent propulsion device for an ion thruster, the device comprising:

[0029] Information acquisition module, used to collect test fault data and key characterization parameters of ion thrusters;

[0030] a mechanism establishing module, configured to establish an adaptive triggering mechanism for the ion thruster according to the test fault data;

[0031] An indicator interpretation module, configured to interpret an indicator deviation of the ion thruster according to the key characterization parameters;

[0032] a judgment result determination module, configured to, when the indicator deviation judgment passes, perform a key performance change judgment and a beam current change judgment on the ion thruster according to the key characterization parameters to obtain a judgment result of the ion thruster;

[0033] An adjustment module is used to adjust the operating state of the ion thruster according to the judgment result and the adaptive trigger mechanism.

[0034] In a third aspect, an embodiment of the present application provides a computer storage medium, which stores a plurality of instructions suitable for being loaded by a processor and executing the above-mentioned method steps.

[0035] In a fourth aspect, an embodiment of the present application provides a terminal, which may include: a processor and a memory; wherein the memory stores a computer program, and the computer program is suitable for being loaded by the processor and executing the above-mentioned method steps.

[0036] The technical solutions provided by the embodiments of the present application may have the following beneficial effects:

[0037] In an embodiment of the present application, the on-orbit intelligent propulsion method for an ion thruster first collects test fault data and key characterization parameters of the ion thruster; then, based on the test fault data, establishes an adaptive trigger mechanism for the ion thruster; performs an indicator deviation assessment on the ion thruster based on the key characterization parameters; if the indicator deviation assessment passes, then performs a key performance change assessment and a beam current change assessment on the ion thruster based on the key characterization parameters to obtain an assessment result for the ion thruster; finally, based on the assessment result and the adaptive trigger mechanism, adjusts the operating state of the ion thruster. This embodiment of the present application establishes an adaptive trigger mechanism for an ion thruster for the first time, realizing the on-orbit intelligent propulsion function of the ion thruster.

[0038] It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and, together with the description, serve to explain the principles of the invention.

[0040] Figure 1 This is a flow chart of an on-orbit intelligent propulsion method for an ion thruster provided in an embodiment of the present application;

[0041] Figure 2 This is a schematic diagram of the overall process of an on-orbit intelligent propulsion method for an ion thruster provided in an embodiment of the present application;

[0042] Figure 3 This is a schematic diagram of an on-orbit intelligent propulsion device for an ion thruster provided in an embodiment of the present application;

[0043] Figure 4 This is a terminal schematic diagram provided in an embodiment of the present application. DETAILED DESCRIPTION

[0044] The following description and the drawings sufficiently illustrate specific embodiments of the invention to enable those skilled in the art to practice them.

[0045] It should be understood that the embodiments described are only a portion of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative work are within the scope of protection of the present invention.

[0046] In the following description, unless otherwise indicated, identical numbers in different figures represent identical or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Instead, they are merely examples of systems and methods consistent with certain aspects of the present invention, as detailed in the appended claims.

[0047] In the description of the present invention, it should be understood that the terms "first", "second", etc. are used for descriptive purposes only and are not to be understood as indicating or implying relative importance. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances. In addition, in the description of the present invention, unless otherwise specified, "plurality" refers to two or more. "And / or" describes the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. The character " / " generally indicates that the previous and subsequent associated objects are in an "or" relationship.

[0048] See Figure 1 and Figure 2, provides a flow chart of an on-orbit intelligent propulsion method for an ion thruster according to an embodiment of the present application. Figure 1 and Figure 2 As shown, the method of the embodiment of the present application may include the following steps:

[0049] During the on-orbit operation of an ion thruster, after eliminating incidental factors (such as grid damage and accidental power supply failure during launch), if problems arise such as changes in the on-orbit space environment, limited communication conditions with the ground measurement and control system, or degradation of the thruster's own operating performance, the ion thruster's operating parameters and operating status must be automatically adjusted in real time to address these issues. Failure to do so can cause the spacecraft mission to deviate from its target and, in severe cases, lead to mission failure. Therefore, if the ion thruster can accurately determine whether performance degradation is caused by flawed input parameter settings, structural wear of key components, or environmental factors during on-orbit operation, the thruster's operating life can be significantly extended and the success of its on-orbit mission can be guaranteed.

[0050] For example, when a spacecraft enters the solar shadow region or the on-orbit active thermal control power is insufficient, the thruster's grid assembly will change its structural parameters due to thermal deformation in this environment, further leading to a series of problems such as a decrease in the grid assembly's ability to extract plasma and an increase in the beam divergence angle, resulting in a decrease in thrust value and a deviation in the thrust vector angle. If the thrust value generated by the thruster is monitored to have significantly declined at this time, the thruster's intelligent propulsion function is triggered. Through the working performance parameter control model, the onboard computer calculates the optimal input parameters to adapt to this environment and issues instructions to the thruster's on-orbit active thermal control, gas supply, and power supply units. The closed-loop control mode adjusts the input parameters in this environment, thereby compensating for the thruster's working performance deviation caused by the structural changes of the ion optical system.

[0051] For example, when a thruster reaches the mid-life stage (4000 to 8000 hours), ion sputtering corrosion can cause the accelerating grid apertures to corrode continuously and expand, resulting in a decrease in the accelerating grid's ability to focus the ion beam and an increase in the number of charged particles in the plume. This ultimately leads to a decline in thruster performance and a significantly increased risk of accelerated end-of-life for the ion thruster. If the proportion of charged particles in the thruster plume and changes in the beam divergence angle are regularly monitored, and if the monitored values ​​exceed the threshold of the performance adaptive trigger mechanism, the performance parameter control model can be used to obtain input operating parameters that effectively suppress the charged particle proportion and beam divergence angle. Through closed-loop regulation, the ion etching rate can be reduced and the thruster life can be extended.

[0052] An embodiment of the present application provides an on-orbit intelligent propulsion method for an ion thruster. While the ion thruster is in an on-orbit operating state, the method accurately identifies thruster performance degradation caused by input operating parameter deviations, structural changes in key components, or degradation in the operating capacity of key components. The method then uses an adaptive trigger mechanism established based on previous test failure data to adjust the operating state of the ion thruster in light of these deviations, structural changes, or degradation. In this embodiment, the input operating parameter deviations represent input parameter setting defects, the structural changes in key components represent structural wear of key components, and the degradation in the operating capacity of key components represents degradation of key components caused by environmental factors.

[0053] S100, collecting test fault data and key characterization parameters of the ion thruster.

[0054] In step S100, that is, collecting the test fault data of the ion thruster, the process includes:

[0055] Collect ground test data, test failure statistics and experimental failure analysis data of ion thrusters; the experimental failure analysis data can be used to understand the causes of on-orbit failures.

[0056] The ground test data, the test failure statistical data and the experimental failure analysis data are used as test failure data of the ion thruster. Figure 2 The ion thruster ground test data and failure cause analysis in are the test failure data of the ion thruster.

[0057] In the embodiments of this application, a large amount of thruster test data was comprehensively compiled and subjected to burn-in screening and performance deviation testing, accumulating test failure data for at least 5,000 hours. This test data includes ground-based performance testing of ion thrusters, performance testing in high and low temperature environments, and performance testing in a simulated deep space cold environment.

[0058] In step S100, key characterization parameters of the ion thruster are collected as follows:

[0059] In an embodiment of the present application, after the thruster is in orbit, it operates under operating parameter inputs for given air and power supply conditions, and sensors attached to the ion thruster perform regular performance tests on the ion thruster. The ion thruster may be a spaceborne ion thruster, and the sensors may be spaceborne sensors.

[0060] The sensors undergo regular performance testing every 30 minutes. These sensors include various types, such as those for measuring temperature, vacuum, beam current, and supply voltage. Each characteristic parameter of the ion thruster is measured by a corresponding sensor. The sensors communicate with the onboard computer at a sampling frequency of 1 second. The onboard computer calculates the key characteristic parameters of the ion thruster based on the on-orbit measurements of the sensors, such as supply voltage, beam current, beam divergence angle, and charged particle ratio in the plume. These key characteristic parameters can include external environment perception parameters and thruster operating parameters, such as beam current, charged particle ratio in the plume, thrust value, specific impulse, efficiency, and divergence angle. These key characteristic parameters are also called key performance parameters.

[0061] In the embodiment of the present application, the fault logic interpretation of the ion thruster can be performed based on the key characterization parameters, and the fault logic interpretation includes the following contents: indicator deviation interpretation, key performance change interpretation, and beam change interpretation.

[0062] S200: Establishing an adaptive trigger mechanism for the ion thruster based on the test fault data; the adaptive trigger mechanism for the ion thruster is an adaptive trigger mechanism for the operating performance of the ion thruster. In an embodiment of the present application, the test fault data may be a summary of the relationships between operating parameters and causes of performance degradation in a large number of thrusters during early operational stages. Based on analysis of the test fault data, the range of abnormal variations in the input operating parameters of the thruster during on-orbit operation can be determined, thereby establishing the adaptive trigger mechanism for the ion thruster.

[0063] Specifically, step S200 includes:

[0064] Based on the test fault data, a correspondence table between parameter changes and fault causes for the ion thruster is established. In this embodiment of the present application, the thruster operating parameter range can be obtained based on the test fault data, and a thruster parameter change threshold table is established, covering more than 90% of the parameter types. Based on the thruster parameter change threshold table, the input parameter changes associated with each performance degradation case, i.e., each type of fault cause, are analyzed to establish a correspondence table between parameter changes and fault causes.

[0065] Based on the parameter change-fault cause correspondence table, an adaptive triggering mechanism for the ion thruster is established.

[0066] In an embodiment of the present application, the parameter change-fault cause correspondence table can be regarded as a retrieval system. The parameter change-fault cause correspondence table established based on the preset (rated) parameter range of the thruster, the fault phenomena encountered during a large number of ground tests, and the parameter abnormality range when the fault occurs is written into adaptive trigger software and loaded into the onboard computer to enter orbit together with the satellite; the adaptive trigger software contains an adaptive trigger mechanism.

[0067] In one possible implementation, the adaptive trigger mechanism of the ion thruster can be directly input into the onboard computer; when the adaptive trigger mechanism of the ion thruster needs to be modified and improved or new test failure data appears in ground experiments, the adaptive trigger mechanism needs to be updated, and the updated adaptive trigger mechanism is uploaded to the onboard computer for replacement according to the ground measurement and control network.

[0068] S300, performing index deviation judgment on the ion thruster according to the key characterization parameters; the step S300 includes:

[0069] The ion thruster's index deviation is judged based on the key characterization parameter and a preset index deviation threshold. The preset index deviation threshold is a preset key characterization parameter deviation threshold that will cause the thruster to operate abnormally on orbit, and can be set to 10%.

[0070] In the embodiment of the present application, step S300 primarily performs an indicator deviation verification for the ion thruster. If the deviation of the key characteristic parameter exceeds a preset indicator deviation threshold, it indicates that the key characteristic parameter of the thruster has a serious deviation, which will affect the on-orbit operation of the ion thruster, and the ion thruster indicator deviation is interpreted as passed. If the deviation of the key characteristic parameter is not greater than the preset indicator deviation threshold, it indicates that the key characteristic parameter of the thruster has a slight or no deviation, which will not affect the on-orbit operation of the ion thruster, and the ion thruster indicator deviation is interpreted as failed.

[0071] S400 : If the indicator deviation is judged to be passed, a key performance variation judgment and a beam current variation judgment are performed on the ion thruster according to the key characterization parameters to obtain a judgment result of the ion thruster.

[0072] In step S400, key performance variation and beam current variation of the ion thruster are interpreted based on the key characterization parameters to obtain interpretation results of the ion thruster, including:

[0073] performing the key performance change judgment on the ion thruster according to the key characterization parameters to obtain a performance change judgment result of the ion thruster; performing the beam current change judgment on the ion thruster according to the key characterization parameters to obtain a beam current change judgment result of the ion thruster;

[0074] The performance change determination result and the beam current change determination result are used as the determination result of the ion thruster.

[0075] In an embodiment of the present application, the onboard computer compares the key characterization parameters with preset key performance values ​​(i.e., key performance ratings) according to a deviation threshold, and based on the comparison results, interprets the key performance changes of the ion thruster. At this point, if the ion thruster's indicator deviation is interpreted as passing (i.e., the ion thruster's key characterization parameter has seriously deviated), if the comparison result shows a deviation of no more than 10%, it can be considered that the key characterization parameter has not changed, indicating that the ion thruster's input operating parameters have deviated, and the performance change judgment result is an input operating parameter deviation, which is fed back to the onboard computer. If the comparison result shows a deviation of more than 10%, it can be considered that the key characterization parameter has changed, and the thruster beam change analysis is performed. The specific process is as follows:

[0076] A deviation comparison is performed based on the telemetered beam current value, which is included in the key characterization parameters, and the preset beam current value (i.e., the rated beam current value). If the deviation comparison result is no greater than 10%, it is considered that the beam current change is caused by a structural change of a key component in the on-orbit environment. The beam current change is then judged as a structural change of the key component and fed back to the onboard computer.

[0077] If the deviation comparison result is greater than 10%, it is considered that the beam change is caused by the degradation of the working ability of the key component. The beam change judgment result is the degradation of the working ability of the key component, which is fed back to the onboard computer.

[0078] S500, adjusting the operating state of the ion thruster according to the judgment result and the adaptive trigger mechanism. The step S500 includes:

[0079] An adjustment instruction for the ion thruster is determined according to the judgment result and the adaptive trigger mechanism; and an operating state of the ion thruster is adjusted according to the adjustment instruction.

[0080] In an embodiment of the present application, an onboard computer receives the interpretation results, thereby enabling the onboard computer to determine the cause of ion thruster performance degradation (i.e., determine the cause of the ion thruster's on-orbit failure) based on the interpretation results, an adaptive trigger mechanism, and real-time monitored input operating parameters. The onboard computer then performs self-adjustment of the input operating parameters to compensate for the output parameters, thereby realizing the ion thruster's on-orbit intelligent propulsion function. The output parameters are the key characterization parameters, which comprehensively reflect changes in thruster operating performance. When the thruster's operating performance changes, the input operating parameters are adjusted in a timely manner, thereby adjusting the key characterization parameters of the ion thruster. This ensures that while maintaining operating performance, the thruster's on-orbit operating life is extended, thereby improving the success of the spacecraft mission.

[0081] The adaptive trigger mechanism can accurately determine which key characterization parameters cause the interpretation result to be deviation of input working parameters, structural changes of key components or degradation of key component working capabilities, and thus determine the main cause of the degradation of ion thruster performance.

[0082] The onboard computer adjusts the input operating parameters according to the adaptive trigger mechanism. When the response time does not exceed 60s, the onboard computer synchronously sends adjustment instructions containing the adjusted input operating parameters to the thruster, enabling the thruster to adjust the input operating parameters (i.e., the input operating parameters under given air and power supply conditions) and realize the thruster's on-orbit intelligent propulsion function.

[0083] In one possible implementation, if the indicator deviation judgment fails, it indicates that the ion thruster is operating normally on-orbit. That is, when the deviation of the key characteristic parameter is not greater than the preset indicator deviation threshold, the ion thruster is operating normally on-orbit. Therefore, the operating state of the ion thruster can be adjusted by simply failing the indicator deviation judgment of the ion thruster, as follows:

[0084] When the thruster is operating on orbit, if the deviation of a telemetry key characteristic parameter (such as thrust, specific impulse, efficiency and / or divergence angle) exceeds a preset indicator deviation threshold (the preset indicator deviation threshold is 10%), the onboard computer determines that the thruster has failed and calls and triggers the adaptive trigger mechanism;

[0085] By searching for parameter change-fault cause information within the adaptive trigger mechanism, the abnormal operating parameter category and the corresponding fault cause within the preset parameter range are searched. The onboard computer adjusts the abnormal operating parameters and issues adjustment instructions to the thrusters.

[0086] During the process of adjusting operating parameters, the onboard computer continuously determines, using telemetry signals fed back by sensors, whether the deviation of key characterization parameters is no longer greater than a preset indicator deviation threshold. If so, the onboard computer stops invoking and triggers the adaptive adjustment software including the adaptive trigger mechanism, stops adjusting the operating parameters, and resumes normal sampling. If not, the adaptive trigger mechanism is continuously triggered to adjust the operating parameters until the deviation of the key characterization parameters is no longer greater than the preset indicator deviation threshold. The operating parameters may include power supply voltage, beam current, magnet current, and working fluid gas flow rate. The types of operating parameter anomalies may include abnormal power supply voltage, abnormal beam current, abnormal magnet current, and abnormal working fluid gas flow rate.

[0087] In one possible implementation, when the onboard computer receives an interpretation result indicating a structural change in a key component or a degradation in the working capability of a key component, the preset key performance value or the preset beam current value may be lowered to lower the threshold condition for adaptive triggering, i.e., to lower the triggering threshold of the adaptive triggering mechanism; when the interpretation result indicates a degradation in the working capability of a key component, the on-orbit working performance of the thruster may be reduced to ensure the on-orbit working life of the thruster.

[0088] In an embodiment of the present application, the method further includes:

[0089] If the indicator deviation interpretation fails, the process returns to step S100 to continue collecting key characterization parameters of the ion thruster.

[0090] If the indicator deviation interpretation fails, it indicates that the thruster's on-orbit operating status is normal. In this case, the process returns to step S100 to continue collecting key characterization parameters of the ion thruster, and continues with the operations of steps S200, S300, S400, and S500 to perform real-time monitoring and adjustment of the on-orbit operating status of the ion thruster.

[0091] The on-orbit intelligent propulsion method for an ion thruster first collects test fault data and key characterization parameters of the ion thruster; then, based on the test fault data, establishes an adaptive trigger mechanism for the ion thruster; performs an indicator deviation judgment on the ion thruster based on the key characterization parameters; if the indicator deviation judgment passes, then performs a key performance change judgment and a beam current change judgment on the ion thruster based on the key characterization parameters to obtain an interpretation result of the ion thruster; finally, based on the interpretation result and the adaptive trigger mechanism, adjusts the operating state of the ion thruster. This embodiment of the present application establishes an adaptive trigger mechanism for the ion thruster, realizing the on-orbit intelligent propulsion function of the ion thruster.

[0092] The following are embodiments of the apparatus of the present invention, which can be used to implement the method embodiments of the present invention. For details not disclosed in the apparatus embodiments of the present invention, please refer to the method embodiments of the present invention.

[0093] See Figure 3 , which shows a schematic diagram of the structure of an on-orbit intelligent propulsion device for an ion thruster provided by an exemplary embodiment of the present invention. The device includes: an information collection module 10, a mechanism establishment module 20, an indicator interpretation module 30, an interpretation result determination module 40, and an adjustment module 50.

[0094] An information acquisition module 10 is used to collect test fault data and key characterization parameters of the ion thruster;

[0095] a mechanism establishing module 20, configured to establish an adaptive triggering mechanism for the ion thruster according to the test fault data;

[0096] An indicator interpretation module 30 is configured to interpret an indicator deviation of the ion thruster according to the key characterization parameters;

[0097] a judgment result determination module 40, configured to, when the indicator deviation judgment is passed, perform a key performance change judgment and a beam current change judgment on the ion thruster according to the key characterization parameters to obtain a judgment result of the ion thruster;

[0098] The adjustment module 50 is configured to adjust the operating state of the ion thruster according to the judgment result and the adaptive trigger mechanism.

[0099] It should be noted that the aforementioned embodiments of the on-orbit intelligent propulsion device for an ion thruster, when implementing the on-orbit intelligent propulsion method for an ion thruster, illustrate the division of the aforementioned functional modules only as an example. In actual applications, the aforementioned functions can be assigned to different functional modules as needed, i.e., the internal structure of the device can be divided into different functional modules to perform all or part of the functions described above. Furthermore, the on-orbit intelligent propulsion device for an ion thruster and the on-orbit intelligent propulsion method for an ion thruster provided in the aforementioned embodiments are based on the same concept. The implementation process is detailed in the method embodiments and will not be further elaborated here.

[0100] The serial numbers of the above embodiments of the present application are for description only and do not represent the advantages or disadvantages of the embodiments.

[0101] The on-orbit intelligent propulsion device for the ion thruster first collects test fault data and key characterization parameters of the ion thruster; then, based on the test fault data, establishes an adaptive trigger mechanism for the ion thruster; performs an indicator deviation judgment on the ion thruster based on the key characterization parameters; if the indicator deviation judgment passes, then performs a key performance change judgment and a beam current change judgment on the ion thruster based on the key characterization parameters to obtain a judgment result for the ion thruster; finally, based on the judgment result and the adaptive trigger mechanism, adjusts the operating state of the ion thruster. This embodiment of the present application establishes an adaptive trigger mechanism for the ion thruster, realizing the on-orbit intelligent propulsion function of the ion thruster.

[0102] The present invention also provides a computer-readable medium having program instructions stored thereon, which, when executed by a processor, implements the on-orbit intelligent propulsion method for an ion thruster provided in each of the above method embodiments.

[0103] The present invention also provides a computer program product comprising instructions, which, when executed on a computer, enables the computer to execute the on-orbit intelligent propulsion method for an ion thruster according to each of the above method embodiments.

[0104] See Figure 4 , provides a schematic diagram of the structure of a terminal according to an embodiment of the present application. Figure 4 As shown, the terminal 1000 may include: at least one processor 1001 , at least one network interface 1004 , a user interface 1003 , a memory 1005 , and at least one communication bus 1002 .

[0105] The communication bus 1002 is used to implement the connection and communication between these components.

[0106] The user interface 1003 may include a display screen (Display) and a camera (Camera). Optionally, the user interface 1003 may also include a standard wired interface and a wireless interface.

[0107] Among them, the network interface 1004 may optionally include a standard wired interface or a wireless interface (such as a WI-Fl interface).

[0108] The processor 1001 may include one or more processing cores. The processor 1001 utilizes various interfaces and circuits to connect various components within the electronic device 1000. It executes instructions, programs, code sets, or instruction sets stored in the memory 1005, and accesses data stored in the memory 1005 to perform various functions and process data within the electronic device 1000. Optionally, the processor 1001 may be implemented using at least one of the following hardware forms: a digital signal processing (DSP), a field-programmable gate array (FPGA), or a programmable logic array (PLA). The processor 1001 may integrate one or a combination of a central processing unit (CPU), a graphics processing unit (GPU), and a modem. The CPU primarily processes the operating system, user interface, and application programs; the GPU is responsible for rendering and drawing content displayed on the display; and the modem handles wireless communications. It is understood that the modem may not be integrated into the processor 1001 but implemented as a separate chip.

[0109] Among them, the memory 1005 may include a random access memory (RAM) or a read-only memory (Read-Only Memory). Optionally, the memory 1005 includes a non-transitory computer-readable storage medium. The memory 1005 can be used to store instructions, programs, codes, code sets or instruction sets. The memory 1005 may include a program storage area and a data storage area, wherein the program storage area may store instructions for implementing an operating system, instructions for at least one function (such as a touch function, a sound playback function, an image playback function, etc.), instructions for implementing the above-mentioned various method embodiments, etc.; the data storage area may store data involved in the above-mentioned various method embodiments, etc. The memory 1005 may optionally be at least one storage device located away from the aforementioned processor 1001. As Figure 4 As shown, the memory 1005 as a computer storage medium may include an operating system, a network communication module, a user interface module, and an on-orbit intelligent propulsion application for an ion thruster.

[0110] exist Figure 4In the terminal 1000 shown, the user interface 1003 is mainly used to provide an input interface for the user and obtain user input data; and the processor 1001 can be used to call the on-orbit intelligent propulsion application of the ion thruster stored in the memory 1005 and specifically perform the following operations:

[0111] Collect test failure data and key characterization parameters of ion thrusters;

[0112] establishing an adaptive triggering mechanism for the ion thruster based on the test fault data;

[0113] Performing index deviation judgment on the ion thruster according to the key characterization parameters;

[0114] If the indicator deviation judgment is passed, performing a key performance change judgment and a beam current change judgment on the ion thruster according to the key characterization parameters to obtain a judgment result of the ion thruster;

[0115] adjusting the operating state of the ion thruster according to the read result and the adaptive trigger mechanism;

[0116] If the indicator deviation interpretation fails, the process returns to continue collecting the key characterization parameters of the ion thruster.

[0117] In one embodiment, when executing the method of collecting the test fault data of the ion thruster, the processor 1001 specifically performs the following operations:

[0118] Collect ground test data, test failure statistics and experimental failure analysis data of ion thrusters;

[0119] The ground test data, the test failure statistical data and the experimental failure analysis data are used as test failure data of the ion thruster.

[0120] In one embodiment, when executing the step of establishing the adaptive triggering mechanism of the ion thruster according to the test fault data, the processor 1001 specifically performs the following operations:

[0121] Establishing a parameter change-fault cause correspondence table of the ion thruster according to the test fault data;

[0122] Based on the parameter change-fault cause correspondence table, an adaptive triggering mechanism for the ion thruster is established.

[0123] In one embodiment, when performing the indicator deviation judgment of the ion thruster according to the key characterization parameters, the processor 1001 specifically performs the following operations:

[0124] The indicator deviation of the ion thruster is judged based on the key characterization parameters and the preset indicator deviation threshold.

[0125] In one embodiment, when the processor 1001 performs the key performance change judgment and beam current change judgment on the ion thruster according to the key characterization parameters to obtain the judgment result of the ion thruster, the processor 1001 specifically performs the following operations:

[0126] performing a key performance change judgment on the ion thruster according to the key characterization parameters to obtain a performance change judgment result of the ion thruster;

[0127] performing beam current variation judgment on the ion thruster according to the key characterization parameters to obtain a beam current variation judgment result of the ion thruster;

[0128] The performance change determination result and the beam current change determination result are used as the determination result of the ion thruster.

[0129] In one embodiment, when the processor 1001 adjusts the operating state of the ion thruster according to the determination result and the adaptive trigger mechanism, the processor 1001 specifically performs the following operations:

[0130] determining an adjustment instruction for the ion thruster according to the judgment result and the adaptive trigger mechanism;

[0131] According to the adjustment instruction, the operating state of the ion thruster is adjusted.

[0132] The on-orbit intelligent propulsion method for an ion thruster first collects test fault data and key characterization parameters of the ion thruster; then, based on the test fault data, establishes an adaptive trigger mechanism for the ion thruster; performs an indicator deviation judgment on the ion thruster based on the key characterization parameters; if the indicator deviation judgment passes, then performs a key performance change judgment and a beam current change judgment on the ion thruster based on the key characterization parameters to obtain an interpretation result of the ion thruster; finally, based on the interpretation result and the adaptive trigger mechanism, adjusts the operating state of the ion thruster. This embodiment of the present application establishes an adaptive trigger mechanism for the ion thruster, realizing the on-orbit intelligent propulsion function of the ion thruster.

[0133] Those skilled in the art will appreciate that all or part of the processes in the above-described method embodiments can be implemented by instructing related hardware through a computer program. The program can be stored in a computer-readable storage medium, and when executed, the program can include the processes in the above-described method embodiments. The storage medium can be a magnetic disk, an optical disk, a read-only memory, or a random access memory.

[0134] The above disclosure is only a preferred embodiment of the present application, and certainly cannot be used to limit the scope of rights of the present application. Therefore, equivalent changes made according to the claims of the present application are still within the scope covered by the present application.

Claims

1. An on-orbit intelligent propulsion method for an ion thruster, characterized in that: The following steps are involved: Collect test failure data and key characterization parameters of ion thrusters; The collecting of test fault data of the ion thruster includes: Collect ground test data, test failure statistics and experimental failure analysis data of ion thrusters; Using the ground test data, the test failure statistical data and the experimental failure analysis data as test failure data of the ion thruster; Establishing an adaptive triggering mechanism for the ion thruster according to the test fault data, including: Establishing a parameter change-fault cause correspondence table of the ion thruster according to the test fault data; establishing an adaptive triggering mechanism for the ion thruster based on the parameter change-fault cause correspondence table; Performing index deviation judgment on the ion thruster according to the key characterization parameters; If the indicator deviation judgment is passed, performing a key performance change judgment and a beam current change judgment on the ion thruster according to the key characterization parameters to obtain a judgment result of the ion thruster; The operating state of the ion thruster is adjusted according to the judgment result and the adaptive trigger mechanism.

2. The on-orbit intelligent propulsion method according to claim 1, characterized in that: The step of judging the index deviation of the ion thruster according to the key characterization parameters includes: The indicator deviation of the ion thruster is judged based on the key characterization parameters and the preset indicator deviation threshold.

3. The on-orbit intelligent propulsion method according to claim 1, characterized in that: The step of performing key performance change judgment and beam current change judgment on the ion thruster according to the key characterization parameters to obtain a judgment result of the ion thruster includes: performing a key performance change judgment on the ion thruster according to the key characterization parameters to obtain a performance change judgment result of the ion thruster; performing beam current variation judgment on the ion thruster according to the key characterization parameters to obtain a beam current variation judgment result of the ion thruster; The performance change determination result and the beam current change determination result are used as the determination result of the ion thruster.

4. The on-orbit intelligent propulsion method according to claim 1, characterized in that: The step of adjusting the operating state of the ion thruster according to the reading result and the adaptive trigger mechanism includes: determining an adjustment instruction for the ion thruster according to the judgment result and the adaptive trigger mechanism; According to the adjustment instruction, the operating state of the ion thruster is adjusted.

5. The on-orbit intelligent propulsion method according to claim 1, characterized in that: Furthermore, it also includes: If the indicator deviation interpretation fails, the process returns to continue collecting the key characterization parameters of the ion thruster.

6. An on-orbit intelligent propulsion device for an ion thruster, characterized in that: include: Information acquisition module, used to collect test fault data and key characterization parameters of ion thrusters; The collecting of test fault data of the ion thruster includes: Collect ground test data, test failure statistics and experimental failure analysis data of ion thrusters; Using the ground test data, the test failure statistical data and the experimental failure analysis data as test failure data of the ion thruster; A mechanism establishment module is used to establish an adaptive trigger mechanism for the ion thruster according to the test fault data, including: Establishing a parameter change-fault cause correspondence table of the ion thruster according to the test fault data; establishing an adaptive triggering mechanism for the ion thruster based on the parameter change-fault cause correspondence table; An indicator interpretation module, configured to interpret an indicator deviation of the ion thruster according to the key characterization parameters; a judgment result determination module, configured to, when the indicator deviation judgment passes, perform a key performance change judgment and a beam current change judgment on the ion thruster according to the key characterization parameters to obtain a judgment result of the ion thruster; An adjustment module is used to adjust the operating state of the ion thruster according to the judgment result and the adaptive trigger mechanism.

7. A computer storage medium, characterized in that The computer storage medium stores a plurality of instructions, which are suitable for being loaded by a processor and executing the method steps according to any one of claims 1 to 5.

8. A terminal, characterized in that: include: A processor and a memory; wherein the memory stores a computer program, and the computer program is suitable for being loaded by the processor and executing the method steps according to any one of claims 1 to 5.

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