Ion electric propulsion system double-engine ignition performance consistency control method and device

Abstract

The invention relates to a method and a device for controlling consistency of double ignition performance of an ion electric propulsion system. The method comprises the following steps: acquiring a thermal throttler, an anode power supply and a screen grid power supply which are used for controlling the double-firing ignition performance of the ion electric propulsion system; the heat throttlers are screened, so that the gas supply performance consistency control of the double-engine ignition performance control of the ion electric propulsion system is realized; through the anode power supply and the screen grid power supply, power supply performance consistency control and software consistency control of double-firing ignition performance control of the ion electric propulsion system are realized. According to the dual-engine thruster performance consistency control method and system, the purpose of dual-engine thruster performance consistency is comprehensively achieved by improving air supply performance consistency control, improving power supply performance consistency control and improving software consistency control, finally, the satellite disturbance torque is minimum, the propulsion efficiency is highest, and the whole satellite application efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft electric propulsion systems, and more specifically, to a method and device for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system. Background Art

[0002] It is a common on-orbit propulsion method to configure an ion electric propulsion system with two thrusters working simultaneously. The thrust of the two thrusters must be consistent so that the combined force can pass through the center of mass, minimize the satellite interference torque, and maximize the propulsion efficiency. Therefore, in general usage scenarios, the thrust deviation of paired thrusters is required to be ≤±5%. Since the amount of thrust generated is not only related to the performance of the ion thruster itself, but also to the gas supply of the storage and supply system, the power supply of the power system, and the setting of the control unit software strategy. Therefore, high requirements are placed on the consistency of the dual-engine ignition performance of the ion electric propulsion system. In order to minimize the satellite interference torque and maximize the propulsion efficiency, comprehensive control is required from multiple levels of power supply, gas supply, and software. Summary of the invention

[0003] The embodiments of the present application provide a method and device for controlling the consistency of the dual-engine ignition performance of an ion electric propulsion system. In order to have a basic understanding of some aspects of the disclosed embodiments, a simple summary is given below. This summary is not a general review, nor is it intended to identify key / important components or to describe the scope of protection of these embodiments. Its only purpose is to present some concepts in a simple form as a preface to the detailed description that follows.

[0004] In a first aspect, the present application provides a method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system, the method comprising:

[0005] Acquire the thermal throttle, anode power supply and screen grid power supply for dual-engine ignition performance control of the ion electric propulsion system;

[0006] By screening the thermal throttle, the air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is achieved;

[0007] The power supply performance consistency control and software consistency control of the dual-engine ignition performance control of the ion electric propulsion system are achieved through the anode power supply and the screen grid power supply.

[0008] According to a preferred embodiment, the method of implementing the air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system by screening the thermal throttle includes:

[0009] The thermal throttle is screened by a 9-point calibration and linear fitting screening method to achieve consistency control of the air supply performance of the dual-engine ignition performance control of the ion electric propulsion system.

[0010] According to a preferred embodiment, the power supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is realized by the anode power supply and the screen grid power supply, including:

[0011] The power supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is achieved through the anode power supply, the screen grid power supply and the slow power-on instruction; the slow power-on instruction includes instructions for starting step division and step dwell time.

[0012] According to a preferred embodiment, the software consistency control of the dual-engine ignition performance control of the ion electric propulsion system is realized by the anode power supply and the screen grid power supply, including:

[0013] The beam guide timer and beam closed-loop regulation are set by the anode power supply and the screen grid power supply to achieve software consistency control of the dual-engine ignition performance control of the ion electric propulsion system.

[0014] According to a preferred embodiment, the beam closed-loop regulation performs performance difference regulation or performance degradation control on the thruster.

[0015] In a second aspect, the present application provides a device for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system, the device comprising:

[0016] Acquisition module, used to acquire the thermal throttle, anode power supply and screen grid power supply for dual-engine ignition performance control of the ion electric propulsion system;

[0017] An air supply control module, used for achieving air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system by screening the thermal throttle;

[0018] The power supply and software control module is used to achieve power supply performance consistency control and software consistency control of the dual-engine ignition performance control of the ion electric propulsion system through the anode power supply and the screen grid power supply.

[0019] According to a preferred embodiment, the gas supply control module is specifically used for:

[0020] The thermal throttle is screened by a 9-point calibration and linear fitting screening method to achieve consistency control of the air supply performance of the dual-engine ignition performance control of the ion electric propulsion system.

[0021] According to a preferred embodiment, the power supply and software control module includes:

[0022] A power supply control unit is used to achieve power supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system through the anode power supply, the screen grid power supply and a slow power-on instruction; the slow power-on instruction includes an instruction to start step division and step dwell time.

[0023] According to a preferred embodiment, the power supply and software control module includes:

[0024] A software control unit is used to set a beam current timer and a beam current closed-loop adjustment through the anode power supply and the screen grid power supply, so as to realize software consistency control of the dual-engine ignition performance control of the ion electric propulsion system.

[0025] According to a preferred embodiment, in the software control unit, the beam closed-loop regulation is used to perform performance difference regulation or performance degradation control on the thruster.

[0026] In a third aspect, the present application provides a computer storage medium, which stores a plurality of instructions, and the instructions are suitable for being loaded by a processor and executing the above-mentioned method steps.

[0027] In a fourth aspect, 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.

[0028] The technical solution provided by this application may have the following beneficial effects:

[0029] In the present application, the method for controlling the performance consistency of the dual-engine ignition of the ion electric propulsion system obtains the thermal throttle, anode power supply and screen grid power supply for the dual-engine ignition performance control of the ion electric propulsion system; by screening the thermal throttle, the air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is realized; by the anode power supply and screen grid power supply, the power supply performance consistency control and software consistency control of the dual-engine ignition performance control of the ion electric propulsion system are realized. This application comprehensively achieves the purpose of consistent performance of dual-engine thrusters from improving the consistency control of air supply performance, improving the consistency control of power supply performance, and improving the consistency control of software, and ultimately minimizes the satellite interference torque and maximizes the propulsion efficiency, thereby improving the application efficiency of the entire satellite.

[0030] It is to be understood that both 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

[0031] 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.

[0032] Figure 1It is a flow chart of a method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system provided in an embodiment of the present application;

[0033] Figure 2 It is a typical neutralizer linear fitting curve and determination coefficient schematic diagram of a method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system provided in an embodiment of the present application;

[0034] Figure 3 It is a typical main cathode linear fitting curve and a schematic diagram of a determination coefficient of a method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system provided in an embodiment of the present application;

[0035] Figure 4 It is a typical anode linear fitting curve and a schematic diagram of a coefficient of determination of a method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system provided in an embodiment of the present application;

[0036] Figure 5 It is a schematic diagram of the operation flow of the guide beam timer of a method for controlling the consistency of the ignition performance of dual engines of an ion electric propulsion system provided in an embodiment of the present application;

[0037] Figure 6 It is a flow chart of beam closed-loop regulation of a method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system provided in an embodiment of the present application;

[0038] Figure 7 It is a structural schematic diagram of a dual-engine ignition performance consistency control device for an ion electric propulsion system provided in an embodiment of the present application;

[0039] Figure 8 This is a terminal schematic diagram provided in an embodiment of the present application.

[0040] Reference numerals:

[0041] 10000, acquisition module, 20000, gas supply control module, 30000, power supply and software control module;

[0042] 1001. Processor, 1002. Communication bus, 1003. User interface, 1004. Network interface, 1005. Memory. DETAILED DESCRIPTION

[0043] The following description and the drawings sufficiently illustrate specific embodiments of the invention to enable those skilled in the art to practice them.

[0044] It should be clear that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0045] When the following description refers to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Instead, they are only examples of systems and methods consistent with some aspects of the present invention as detailed in the attached claims.

[0046] In the description of the present invention, it should be understood that the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. For those of ordinary skill 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 previously associated objects are in an "or" relationship.

[0047] The following will be combined with the attached Figure 1 -Attached Figure 6 , a method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system provided in an embodiment of the present application is introduced in detail.

[0048] See also Figure 1-6 The method of the embodiment of the present application may include the following steps:

[0049] The present application provides a method for controlling the consistency of the dual-engine ignition performance of an ion electric propulsion system, including: air supply performance consistency control, which is achieved through a 9-point calibration and linear fitting screening method to achieve consistent air supply performance of two thrusters. Power supply performance consistency control, which is achieved through a controlled slow power-on instruction to reduce output surges and achieve consistent working stability of the two thrusters. Software consistency control, which is achieved by setting a beam flow timer to achieve synchronous thrust generation by the two thrusters; and consistency control of the thrust size of the two thrusters is achieved through beam closed-loop regulation, including performance difference adjustment of the two thrusters in a healthy state and performance degradation control.

[0050] Step S100, obtaining a thermal throttle, an anode power supply and a screen grid power supply for controlling the dual-engine ignition performance of an ion electric propulsion system.

[0051] Step S200, by screening the thermal throttle, achieving air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system, including:

[0052] The thermal throttle is screened by a 9-point calibration and linear fitting screening method to achieve consistency control of the air supply performance of the dual-engine ignition performance control of the ion electric propulsion system.

[0053] In the embodiment of the present application, the consistency of gas supply performance is controlled as follows: First, the flow rates of the 9 points under the combination of ±4% inlet pressure of the rated inlet pressure and ±4°C of the rated temperature of each thermal throttle are calibrated, as shown in Tables 1, 2 and 3 below. It is required that the ratio of the flow rate under the deviation of the 8 temperature and inlet pressure combinations to the flow rate under the rated temperature and rated inlet pressure is within ±10%; secondly, linear fitting is performed on the three groups of curves at the same temperature and different inlet pressures, and the determination coefficient is required to be greater than 0.9, such as Figure 2 , Figure 3 and Figure 4 As shown, R 2 It represents the determination coefficient after the linear fitting curve, the horizontal axis represents the inlet pressure, the vertical axis represents the output flow rate, the blue curve represents the straight line obtained by the linear fitting curve under different inlet pressure conditions when the temperature is fixed at the rated temperature -4℃, the red curve represents the straight line obtained by the linear fitting curve under different inlet pressure conditions when the temperature is fixed at the rated temperature, and the green curve represents the straight line obtained by the linear fitting curve under different inlet pressure conditions when the temperature is fixed at the rated temperature +4℃, where, Figure 2 This is a typical neutralizer linear fitting curve and determination coefficient diagram, the rated temperature is 65℃, Figure 3 This is a typical main cathode linear fitting curve and determination coefficient diagram, the rated temperature is 53°C, Figure 4 It is a typical anode linear fitting curve and determination coefficient diagram, and the rated temperature is 90℃.

[0054] The thermal throttle is screened according to the above criteria to achieve consistent gas supply performance.

[0055] Table 1. Typical Neutralizer 9-point Calibration Table

[0056]

[0057]

[0058] Table 2. Typical main cathode 9-point calibration table

[0059]

[0060] Table 3. Typical anode 9-point calibration table

[0061]

[0062] Step S300, realizing power supply performance consistency control and software consistency control of dual-engine ignition performance control of the ion electric propulsion system through the anode power supply and the screen grid power supply.

[0063] In step S300, the power supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is realized through the anode power supply and the screen grid power supply, including:

[0064] The power supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is achieved through the anode power supply, the screen grid power supply and the slow power-on instruction; the slow power-on instruction includes instructions for starting step division and step dwell time. The starting step division can be divided into four steps, and the step dwell time can be 1s.

[0065] In the embodiment of the present application, the power supply performance consistency control is also called power supply stability control. The power supply performance consistency control: The maximum power supply of the ion thruster is the anode power supply and the screen grid power supply. If these two power supplies are output at full power in one step, it will cause the problem of excessive oscillation of plasma discharge and beam extraction, and there will be inconsistent oscillations of different thrusters, resulting in uncontrolled phenomena. The anode power supply is an adjustable constant current source, and the screen grid power supply is an adjustable constant voltage source. The start-up process is carried out in four steps of 25%, 50%, 75% and 100%, and the step dwell time of each step is 1s to realize the power supply slow start operation, thereby reducing the output surge and realizing the stable operation of the thruster.

[0066] In step S300, the software consistency control of the dual-engine ignition performance control of the ion electric propulsion system is implemented through the anode power supply and the screen grid power supply, including:

[0067] The anode power supply and the screen grid power supply are used to set the beam current timer and the beam current closed-loop regulation to achieve software consistency control of the dual-engine ignition performance control of the ion electric propulsion system. The beam current closed-loop regulation performs performance difference adjustment or performance degradation control on the thrusters. The performance degradation control of the thrusters refers to the power reduction performance consistency control of the two thrusters after performance degradation.

[0068] In the embodiment of the present application, software consistency control is performed: different thrusters have different start-up preparation times, and two thrusters share a beam-introduction timer. The beam-introduction timer can be triggered only when both thrusters have completed start-up preparation, so that the two thrusters can generate beams at the same time; at the same time, the time of the beam-introduction timer can be set, so that the beam-introduction time of the two thrusters can be the same each time. Figure 5The figure is a flow chart of the operation of the beam current timer. After receiving the dual-engine ignition command, the dual-engine ignition starts. First, the timer time can be set to 10 minutes, and the 10-minute ignition timing is started. 10 minutes is the maximum envelope time for the ignition preparation of the two thrusters. During this time, the two thrusters 1 and 2 independently complete the ignition of the neutralizer, the ignition of the main cathode discharge chamber, and adjust the anode power supply to the state of preparing the beam current. The anode power supply in the state of preparing the beam current can be 2.6A. At this point, both thrusters have completed the preparation work before the beam current generates thrust. Wait for the 10-minute timing time to load the screen grid power supply and the acceleration power supply voltage together to achieve the purpose of synchronously generating thrust. This process is controlled by a process in the software, and the anode power supply is adjusted to the set power gear corresponding to different working conditions. The set power gear can be the middle gear, that is, the anode power supply is adjusted to the middle gear, and then the screen grid current closed-loop regulation can be started, and the beam closed-loop regulation process is entered, and the dual-engine ignition is completed. Figure 5 The entire process ensures performance consistency throughout the initial moment of thrust generation, the intermediate loading process, and the continuous working phase.

[0069] The beam closed-loop adjustment process is as follows: Figure 6 As shown, PPMA, PPMB and PPMC are all power modules. The two thrusters can be powered by PPMA, PPMB and PPMC in pairs. After the beam closed loop starts, when the PPMA screen grid power supply output current exceeds the tolerance, the PPMB screen grid power supply output current exceeds the tolerance, or the PPMC screen grid power supply output current exceeds the tolerance, the PPMA anode power supply, the PPMB anode power supply or the PPMC anode power supply stage is adjusted, and the adjustment power code is 0x04. After the anode power supply is adjusted, or when the PPMA screen grid power supply output current exceeds the tolerance, the PPMB screen grid power supply output current exceeds the tolerance, and the PPMC screen grid power supply output current exceeds the tolerance, it is necessary to delay for 10 seconds to check whether the screen grid current closed-loop adjustment flag is in the open state. If so, continue to cycle the process after the above beam closed loop starts, otherwise, the beam closed loop ends; the above process is performed every 10 seconds to achieve continuous consistency control capability. Figure 6In the thruster power module, the screen grid power supply output current can directly represent the thrust. Therefore, it is judged whether the thrust represented by the screen grid power supply output current of each power module is within the allowable thrust deviation ≤ ±5%. If not, the screen grid power supply output current of the power module is out of tolerance. At this time, it is necessary to adjust the power code of the anode power supply control of the corresponding power module to restore the beam to the state where the thrust deviation is within ±5%. The beam closed-loop adjustment is used to achieve closed-loop control of the beam within the set beam closed-loop range. The same beam closed-loop range is set for the two thrusters to achieve the purpose of consistent output thrust. This function can be extended to the case where a thruster has performance degradation. By lowering the beam closed-loop range of the two thrusters, the consistency of thrust output under fault conditions can be ensured.

[0070] The above-mentioned beam closed-loop regulation is also called beam closed-loop control, autonomous regulation of anode current output by the anode power supply, and screen current closed-loop regulation.

[0071] In the present application, the method for controlling the performance consistency of the dual-engine ignition of the ion electric propulsion system obtains the thermal throttle, anode power supply and screen grid power supply for the dual-engine ignition performance control of the ion electric propulsion system; by screening the thermal throttle, the air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is realized; through the anode power supply and the screen grid power supply, the power supply performance consistency control and software consistency control of the dual-engine ignition performance control of the ion electric propulsion system are realized. This application comprehensively achieves the purpose of consistent performance of dual-engine thrusters from improving the consistency control of air supply performance, improving the consistency control of power supply performance, setting the software's beam flow timer, and the software's beam closed-loop regulation, ultimately minimizing the satellite interference torque and maximizing the propulsion efficiency, thereby improving the application efficiency of the entire satellite.

[0072] The following are embodiments of the device of the present invention, which can be used to implement the method embodiments of the present invention. For details not disclosed in the device embodiments of the present invention, please refer to the method embodiments of the present invention.

[0073] See also Figure 7 , which shows a schematic diagram of the structure of a dual-engine ignition performance consistency control device for an ion electric propulsion system provided by an exemplary embodiment of the present invention. The device includes: an acquisition module 10000, an air supply control module 20000, and a power supply and software control module 30000.

[0074] The acquisition module 10000 is used to acquire the thermal throttle, anode power supply and screen grid power supply for the dual-engine ignition performance control of the ion electric propulsion system;

[0075] The air supply control module 20000 is used to achieve air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system by screening the thermal throttle;

[0076] The power supply and software control module 30000 is used to achieve power supply performance consistency control and software consistency control of the dual-engine ignition performance control of the ion electric propulsion system through the anode power supply and the screen grid power supply.

[0077] According to a preferred embodiment, the gas supply control module 20000 is specifically used for:

[0078] The thermal throttle is screened by a 9-point calibration and linear fitting screening method to achieve consistency control of the air supply performance of the dual-engine ignition performance control of the ion electric propulsion system.

[0079] According to a preferred embodiment, the power supply and software control module 30000 includes:

[0080] A power supply control unit is used to achieve power supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system through the anode power supply, the screen grid power supply and a slow power-on instruction; the slow power-on instruction includes an instruction to start step division and step dwell time.

[0081] According to a preferred embodiment, the power supply and software control module 30000 includes:

[0082] A software control unit is used to set a beam current timer and a beam current closed-loop adjustment through the anode power supply and the screen grid power supply, so as to realize software consistency control of the dual-engine ignition performance control of the ion electric propulsion system.

[0083] According to a preferred embodiment, in the software control unit, the beam closed-loop regulation is used to perform performance difference regulation or performance degradation control on the thruster.

[0084] It should be noted that the dual-engine ignition performance consistency control device for an ion electric propulsion system provided in the above embodiment only uses the division of the above functional modules as an example when executing the dual-engine ignition performance consistency control method for an ion electric propulsion system. In actual applications, the above functional distribution can be completed by different functional modules as needed, that is, the internal structure of the device is divided into different functional modules to complete all or part of the functions described above. In addition, the dual-engine ignition performance consistency control device for an ion electric propulsion system provided in the above embodiment and the dual-engine ignition performance consistency control method for an ion electric propulsion system belong to the same concept, and the implementation process thereof is detailed in the method embodiment, which will not be repeated here.

[0085] In the embodiment of the present application, the ion electric propulsion system dual-engine ignition performance consistency control device obtains the thermal throttle, anode power supply and screen grid power supply of the ion electric propulsion system dual-engine ignition performance control; by screening the thermal throttle, the air supply performance consistency control of the ion electric propulsion system dual-engine ignition performance control is realized; through the anode power supply and the screen grid power supply, the power supply performance consistency control and software consistency control of the ion electric propulsion system dual-engine ignition performance control are realized. This application comprehensively achieves the purpose of consistent performance of dual-engine thrusters from improving air supply performance consistency control, improving power supply performance consistency control, and improving software consistency control, ultimately minimizing satellite interference torque and maximizing propulsion efficiency, thereby improving the application efficiency of the entire satellite.

[0086] The present invention also provides a computer-readable medium having program instructions stored thereon, which, when executed by a processor, implement the method for controlling the consistency of the dual-engine ignition performance of the ion electric propulsion system provided by the above-mentioned various method embodiments.

[0087] The present invention also provides a computer program product comprising instructions, which, when executed on a computer, enables the computer to execute the method for controlling the consistency of the dual-engine ignition performance of an ion electric propulsion system in accordance with each of the above-mentioned method embodiments.

[0088] See also Figure 8 , which is a schematic diagram of the structure of a terminal according to an embodiment of the present application. The terminal 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.

[0089] The communication bus 1002 is used to realize the connection and communication between these components.

[0090] The user interface 1003 may include a display screen (Display) and a camera (Camera), and the optional user interface 1003 may also include a standard wired interface and a wireless interface.

[0091] The network interface 1004 may optionally include a standard wired interface or a wireless interface (such as a WI-FI interface).

[0092] Among them, the processor 1001 may include one or more processing cores. The processor 1001 uses various interfaces and lines to connect various parts in the entire terminal, and executes various functions of the terminal and processes data by running or executing instructions, programs, code sets or instruction sets stored in the memory 1005, and calling data stored in the memory 1005. Optionally, the processor 1001 can be implemented in at least one hardware form of digital signal processing (Digital Signal Processing, DSP), field programmable gate array (Field-Programmable Gate Array, FPGA), and programmable logic array (Programmable Logic Array, PLA). The processor 1001 can integrate one or a combination of a central processing unit (Central Processing Unit, CPU), a graphics processing unit (Graphics Processing Unit, GPU) and a modem. Among them, the CPU mainly processes the operating system, user interface and application programs; the GPU is responsible for rendering and drawing the content to be displayed on the display screen; the modem is used to process wireless communications. It can be understood that the above-mentioned modem may not be integrated into the processor 1001, and it can be implemented separately through a chip.

[0093] Among them, the memory 1005 may include a random access memory (Random Access Memory, RAM) and may also include 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 8 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 ion electric propulsion system dual-engine ignition performance consistency control application.

[0094] exist Figure 8In the terminal shown, the user interface 1003 is mainly used to provide an input interface for the user and obtain the data input by the user; and the processor 1001 can be used to call the ion electric propulsion system dual-engine ignition performance consistency control application stored in the memory 1005, and specifically perform the following operations:

[0095] Acquire the thermal throttle, anode power supply and screen grid power supply for dual-engine ignition performance control of the ion electric propulsion system;

[0096] By screening the thermal throttle, the air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is achieved;

[0097] The power supply performance consistency control and software consistency control of the dual-engine ignition performance control of the ion electric propulsion system are achieved through the anode power supply and the screen grid power supply.

[0098] In one embodiment, when the processor 1001 performs the air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system by screening the thermal throttle, the processor 1001 specifically performs the following operations:

[0099] The thermal throttle is screened by a 9-point calibration and linear fitting screening method to achieve consistency control of the air supply performance of the dual-engine ignition performance control of the ion electric propulsion system.

[0100] In one embodiment, when the processor 1001 executes the power supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system through the anode power supply and the screen grid power supply, the processor 1001 specifically performs the following operations:

[0101] The power supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is achieved through the anode power supply, the screen grid power supply and the slow power-on instruction; the slow power-on instruction includes instructions for starting step division and step dwell time.

[0102] In one embodiment, when the processor 1001 executes the software consistency control of the dual-engine ignition performance control of the ion electric propulsion system through the anode power supply and the screen grid power supply, the processor 1001 specifically performs the following operations:

[0103] The beam current timer and beam current closed-loop regulation are set by the anode power supply and the screen grid power supply to achieve software consistency control of the dual-engine ignition performance control of the ion electric propulsion system; wherein the beam current closed-loop regulation performs performance difference adjustment or performance degradation control on the thruster.

[0104] In the embodiment of the present application, the method and device for controlling the consistency of the dual-engine ignition performance of the ion electric propulsion system obtains the thermal throttle, anode power supply and screen grid power supply for the dual-engine ignition performance control of the ion electric propulsion system; by screening the thermal throttle, the air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is realized; through the anode power supply and the screen grid power supply, the power supply performance consistency control and software consistency control of the dual-engine ignition performance control of the ion electric propulsion system are realized. The present application comprehensively achieves the purpose of consistent performance of dual-engine thrusters from improving the consistency control of air supply performance, improving the consistency control of power supply performance, and improving the consistency control of software, and ultimately minimizes the satellite interference torque and maximizes the propulsion efficiency, thereby improving the application efficiency of the entire satellite.

[0105] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiments can be implemented by instructing related hardware through a computer program, and the program can be stored in a computer-readable storage medium, and when the program is executed, it can include the processes of the embodiments of the above-mentioned methods. The storage medium can be a disk, an optical disk, a read-only storage memory, or a random access memory, etc.

[0106] The above disclosure is only the preferred embodiment of the present application, which 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. A method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system, characterized in that: The following steps are involved: Acquire the thermal throttle, anode power supply and screen grid power supply for dual-engine ignition performance control of the ion electric propulsion system; By screening the thermal throttle, the air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is achieved; The power supply performance consistency control and software consistency control of the dual-engine ignition performance control of the ion electric propulsion system are achieved through the anode power supply and the screen grid power supply.

2. The method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system according to claim 1, characterized in that: The method of implementing the air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system by screening the thermal throttle comprises: The thermal throttle is screened by a 9-point calibration and linear fitting screening method to achieve consistency control of the air supply performance of the dual-engine ignition performance control of the ion electric propulsion system.

3. The method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system according to claim 1, characterized in that: The power supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is realized by the anode power supply and the screen grid power supply, including: The power supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system is achieved through the anode power supply, the screen grid power supply and the slow power-on instruction; the slow power-on instruction includes instructions for starting step division and step dwell time.

4. The method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system according to claim 1, characterized in that: The software consistency control of the dual-engine ignition performance control of the ion electric propulsion system is realized by the anode power supply and the screen grid power supply, including: The beam guide timer and beam closed-loop regulation are set by the anode power supply and the screen grid power supply to achieve software consistency control of the dual-engine ignition performance control of the ion electric propulsion system.

5. The method for controlling the consistency of dual-engine ignition performance of an ion electric propulsion system according to claim 4, characterized in that: The beam closed-loop regulation performs performance difference regulation or performance degradation control on the thruster.

6. A dual-engine ignition performance consistency control device for an ion electric propulsion system, characterized in that: include: Acquisition module, used to acquire the thermal throttle, anode power supply and screen grid power supply for dual-engine ignition performance control of the ion electric propulsion system; An air supply control module, used for achieving air supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system by screening the thermal throttle; The power supply and software control module is used to achieve power supply performance consistency control and software consistency control of the dual-engine ignition performance control of the ion electric propulsion system through the anode power supply and the screen grid power supply.

7. The ion electric propulsion system dual-engine ignition performance consistency control device according to claim 6, characterized in that: The air supply control module is specifically used for: The thermal throttle is screened by a 9-point calibration and linear fitting screening method to achieve consistency control of the air supply performance of the dual-engine ignition performance control of the ion electric propulsion system.

8. The ion electric propulsion system dual-engine ignition performance consistency control device according to claim 6, characterized in that: The power supply and software control module comprises: A power supply control unit is used to achieve power supply performance consistency control of the dual-engine ignition performance control of the ion electric propulsion system through the anode power supply, the screen grid power supply and a slow power-on instruction; the slow power-on instruction includes an instruction to start step division and step dwell time.

9. The ion electric propulsion system dual-engine ignition performance consistency control device according to claim 6, characterized in that: The power supply and software control module comprises: A software control unit is used to set a beam current timer and a beam current closed-loop adjustment through the anode power supply and the screen grid power supply, so as to realize software consistency control of the dual-engine ignition performance control of the ion electric propulsion system.

10. The ion electric propulsion system dual-engine ignition performance consistency control device according to claim 9, characterized in that: In the software control unit, the beam closed-loop regulation is used to perform performance difference regulation or performance degradation control on the thruster.

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