Starting time sequence control method and device for ion electric propulsion system

Abstract

The invention relates to a starting time sequence control method and device for an ion electric propulsion system. According to the neutralizer ignition control time sequence, the main cathode ignition control time sequence and the discharge chamber arcing control time sequence, neutralizer arcing, main cathode arcing and discharge chamber arcing controlled by the ion electric propulsion system starting time sequence are carried out; after arc starting of the discharge chamber succeeds, beam extraction of ion electric propulsion system starting time sequence control is carried out according to the beam extraction control time sequence; and after the beam current is successfully led out, power supply out-of-tolerance judgment for starting time sequence control of the ion electric propulsion system is carried out, and if the power supply out-of-tolerance judgment passes, the ion electric propulsion system is successfully started. According to the invention, on the premise of ensuring normal starting of the ion electric propulsion system, optimization of the ignition time sequence of the thruster is realized; the purposes that the neutralizer starts arcing preferentially, the ignition time of the main cathode is shortest, the gas supply balance time of the anode is shortest, the discharge chamber starts arcing stably, the length and width range of the ignition starting time of the thruster is adjustable, and the whole starting time sequence has high robustness control are achieved.

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 startup timing of an ion electric propulsion system. Background Art

[0002] As an advanced propulsion technology for spacecraft applications, the ion electric propulsion system is generally composed of single units such as ion thrusters, power processing and control units (hereinafter referred to as: PPCU), propellant storage and supply units, and vector control mechanisms. It has the advantages of high energy conversion efficiency, large specific impulse, and wide range of thrust and precise adjustment. During the startup process, it involves four stages: neutralizer ignition, main cathode ignition, discharge chamber arcing, and beam loading and extraction. Factors such as differences in product assembly processes, differences in on-orbit working environments, differences in power supply and gas supply conditions, and different stages of on-orbit service lead to the following problems in the above four stages: too long heating time for the neutralizer and the main cathode, confusion in the arcing timing of the neutralizer and the main cathode, excessive propellant loss, unstable anode arcing, wide range of changes in beam extraction time, and the risk of fault shutdown caused by power overshoot and unstable plasma discharge.

[0003] In actual engineering applications, it is necessary to control the neutralizer ignition timing, main cathode ignition timing, discharge chamber arcing timing, beam extraction timing and the coupling process of the above timings during the startup process of the ion electric propulsion system to ensure the reliable operation of the spacecraft using the ion electric propulsion system throughout its life cycle. The present application proposes an ion electric propulsion system startup timing control method and device, which can solve the problems in the prior art. Summary of the invention

[0004] The embodiments of the present application provide a method and device for controlling the startup timing 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 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.

[0005] In a first aspect, the present application provides a method for controlling the startup timing of an ion electric propulsion system, the method comprising:

[0006] Obtain the neutralizer ignition control timing, main cathode ignition control timing, discharge chamber arc control timing and beam current control timing of the ion electric propulsion system startup timing control;

[0007] According to the neutralizer ignition control timing, the main cathode ignition control timing and the discharge chamber arc ignition control timing, the neutralizer arc ignition, the main cathode arc ignition and the discharge chamber arc ignition of the ion electric propulsion system startup timing control are performed;

[0008] After the arc is successfully started in the discharge chamber, the beam extraction of the ion electric propulsion system is performed according to the beam extraction control timing sequence;

[0009] After the beam is extracted successfully, a power out-of-tolerance judgment is performed on the ion electric propulsion system startup timing control. If the power out-of-tolerance judgment is passed, the ion electric propulsion system of the ion electric propulsion system startup timing control is successfully started.

[0010] According to a preferred embodiment, the neutralizer ignition control timing of the ion electric propulsion system startup timing control obtained includes:

[0011] The power processing and control unit controls the storage and supply unit to provide xenon gas to the neutralizer;

[0012] The power processing and control unit provides the neutralizer with a neutralizer heating power supply, a neutralizer holding power supply, and a neutralizer ignition power supply in sequence, and the start-up time of the neutralizer heating power supply, the start-up time of the neutralizer holding power supply, and the start-up time of the neutralizer ignition power supply are respectively earlier than the start-up time of the main cathode heating power supply, the start-up time of the main cathode holding power supply, and the start-up time of the main cathode ignition power supply.

[0013] According to a preferred embodiment, the main cathode ignition control timing of the ion electric propulsion system startup timing control obtained includes:

[0014] The time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the neutralizer is the same as the time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the main cathode;

[0015] The start time of the main cathode heating power supply is set after the start time of the neutralizer heating power supply;

[0016] The main cathode holding power supply is turned on after the anode gas supply balance is stabilized and before the anode power supply is turned on;

[0017] The main cathode ignition power supply is turned on after the anode power supply is turned on;

[0018] The arc starting time of the main cathode is the same as the arc starting time of the discharge chamber.

[0019] According to a preferred embodiment, the obtained discharge chamber arcing control timing of the ion electric propulsion system startup timing control includes:

[0020] After the neutralizer arc is successfully started, the anode xenon gas supply switch of the ion electric propulsion system start-up timing control is turned on;

[0021] According to the length of the pipeline, setting the anode gas supply balance time of the ion electric propulsion system start-up timing control;

[0022] According to the differences of thrusters, the anode arc starting current gear of the ion electric propulsion system startup timing control is set.

[0023] According to a preferred embodiment, the obtained guide beam flow control timing of the ion electric propulsion system startup timing control includes:

[0024] According to the set discharge chamber stabilization time and beam extraction timing, the ion electric propulsion system is loaded to start the beam extraction with timing control.

[0025] In a second aspect, the present application provides an ion electric propulsion system startup timing control device, the device comprising:

[0026] An acquisition module is used to acquire the neutralizer ignition control timing, main cathode ignition control timing, discharge chamber arc control timing and beam current control timing of the ion electric propulsion system startup timing control;

[0027] An arc starting module, used for performing neutralizer arc starting, main cathode arc starting and discharge chamber arc starting of the ion electric propulsion system startup timing control according to the neutralizer ignition control timing, the main cathode ignition control timing and the discharge chamber arc starting control timing;

[0028] A beam extraction module, used for extracting the beam according to the start-up timing control of the ion electric propulsion system according to the beam extraction control timing after the arc in the discharge chamber is successfully started;

[0029] The judgment module is used to perform power out-of-tolerance judgment on the ion electric propulsion system startup timing control after the beam is successfully extracted. If the power out-of-tolerance judgment is passed, the ion electric propulsion system with the ion electric propulsion system startup timing control is successfully started.

[0030] According to a preferred embodiment, in the acquisition module, the neutralizer ignition control timing of the ion electric propulsion system startup timing control acquired includes:

[0031] The power processing and control unit controls the storage and supply unit to provide xenon gas to the neutralizer;

[0032] The power processing and control unit provides the neutralizer with a neutralizer heating power supply, a neutralizer holding power supply, and a neutralizer ignition power supply in sequence, and the start-up time of the neutralizer heating power supply, the start-up time of the neutralizer holding power supply, and the start-up time of the neutralizer ignition power supply are respectively earlier than the start-up time of the main cathode heating power supply, the start-up time of the main cathode holding power supply, and the start-up time of the main cathode ignition power supply.

[0033] According to a preferred embodiment, in the acquisition module, the main cathode ignition control timing of the ion electric propulsion system startup timing control acquired includes:

[0034] The time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the neutralizer is the same as the time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the main cathode;

[0035] The start time of the main cathode heating power supply is set after the start time of the neutralizer heating power supply;

[0036] The main cathode holding power supply is turned on after the anode gas supply balance is stabilized and before the anode power supply is turned on;

[0037] The main cathode ignition power supply is turned on after the anode power supply is turned on;

[0038] The arc starting time of the main cathode is the same as the arc starting time of the discharge chamber.

[0039] According to a preferred embodiment, in the acquisition module, the acquired discharge chamber arcing control timing of the ion electric propulsion system startup timing control includes:

[0040] After the neutralizer arc is successfully started, the anode xenon gas supply switch of the ion electric propulsion system start-up timing control is turned on;

[0041] According to the length of the pipeline, setting the anode gas supply balance time of the ion electric propulsion system start-up timing control;

[0042] According to the differences of thrusters, the anode arc starting current gear of the ion electric propulsion system startup timing control is set.

[0043] According to a preferred embodiment, in the acquisition module, the obtained guide beam flow control timing of the ion electric propulsion system startup timing control includes:

[0044] According to the set discharge chamber stabilization time and beam extraction timing, the ion electric propulsion system is loaded to start the beam extraction with timing control.

[0045] 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.

[0046] 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.

[0047] The technical solution provided by this application may have the following beneficial effects:

[0048] In the present application, the method for controlling the startup timing of an ion electric propulsion system obtains the neutralizer ignition control timing, the main cathode ignition control timing, the discharge chamber arc starting control timing and the beam lead control timing of the startup timing control of the ion electric propulsion system; performs the neutralizer arc starting, the main cathode arc starting and the discharge chamber arc starting of the startup timing control of the ion electric propulsion system according to the neutralizer ignition control timing, the main cathode ignition control timing and the discharge chamber arc starting control timing; after the arc starting in the discharge chamber is successful, the beam extraction of the startup timing control of the ion electric propulsion system is performed according to the beam lead control timing; after the beam extraction is successful, the power supply out-of-tolerance judgment of the startup timing control of the ion electric propulsion system is performed, and if the power supply out-of-tolerance judgment is passed, the ion electric propulsion system of the startup timing control of the ion electric propulsion system is successfully started. Under the premise of ensuring that the ion electric propulsion system can be started normally, the present application realizes the optimization of the ion thruster ignition timing, and achieves the purpose of neutralizer priority arc starting, shortest main cathode ignition time, shortest anode gas supply balance time, stable discharge chamber arc starting, wide range adjustable thruster ignition start time, and strong robustness control of the entire startup timing.

[0049] 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

[0050] 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.

[0051] Figure 1 It is a flow chart of a method for controlling the startup sequence of an ion electric propulsion system provided in an embodiment of the present application;

[0052] Figure 2 It is a schematic diagram of an engineering example of a method for starting timing control of an ion electric propulsion system provided in an embodiment of the present application;

[0053] Figure 3 It is a schematic diagram of an electrical parameter curve of a real ignition start-up process of an ion electric propulsion system according to a method for controlling the start-up timing of an ion electric propulsion system provided in an embodiment of the present application;

[0054] Figure 4 It is a schematic diagram of a device for starting timing control of an ion electric propulsion system provided in an embodiment of the present application;

[0055] Figure 5 This is a terminal schematic diagram provided in an embodiment of the present application.

[0056] Reference numerals:

[0057] 10000, acquisition module, 20000, arc starting module, 30000, beam extraction module, 40000, judgment module;

[0058] 1001. Processor, 1002. Communication bus, 1003. User interface, 1004. Network interface, 1005. Memory. DETAILED DESCRIPTION

[0059] The following description and the drawings sufficiently illustrate specific embodiments of the invention to enable those skilled in the art to practice them.

[0060] 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.

[0061] 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.

[0062] 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.

[0063] The following will be combined with the attached Figure 1 -Attached Figure 3 , a method for starting timing control of an ion electric propulsion system provided in an embodiment of the present application is introduced in detail.

[0064] See also Figure 1-3 The method of the embodiment of the present application may include the following steps:

[0065] An ion electric propulsion system startup timing control method provided in an embodiment of the present application includes: neutralizer ignition control timing, main cathode ignition control timing, discharge chamber arcing control timing, beam flow control timing, and control of these timing coupling processes. Comprehensive optimal control of neutralizer priority arcing and shortest main cathode heating time is achieved, and a strong robust control process is provided that can encompass product differences, environmental differences, and differences in power supply and gas supply conditions. Specifically, the main cathode startup heating time of the embodiment of the present application can be set, and the neutralizer ignition and the main cathode ignition are neither in series nor in parallel, which can achieve multi-objective optimal control of neutralizer priority arcing and shortest main cathode heating time; the main cathode heating time is the main cathode ignition time. In the neutralizer ignition and main cathode heating stages of the embodiment of the present application, the holding current is judged. Once the arc is started by self-ignition, the ignition power supply is no longer turned on, so as to achieve the optimal control goals of ambient temperature difference, shortest main cathode ignition time, and minimum cathode electrical stress; the anode gas supply balance time of the embodiment of the present application can be set, and the anode arc current can be set. According to the length of the pipeline and the difference of the thruster products, the anode gas supply balance time and the initial anode current are set to achieve the multi-objective optimal control of stable arcing in the discharge chamber and the shortest anode gas supply balance time; the extraction beam timing T of the embodiment of the present application can be set to achieve the wide range control goals of inconsistent start-up preparation time for different thrusters and inconsistent start-up preparation time at the beginning and end of the life of the same thruster. The opening time of all power supply out-of-tolerance judgments in the embodiment of the present application can be set to leave enough stable time for power supply overshoot and plasma discharge, so as to achieve strong robustness control of the system.

[0066] Step S100, obtaining the neutralizer ignition control timing, main cathode ignition control timing, discharge chamber arc control timing and beam current control timing of the ion electric propulsion system startup timing control.

[0067] In step S100, the ion electric propulsion system startup timing control neutralizer ignition control timing sequence is obtained, including: a power processing and control unit (PPCU for short) controls the storage and supply unit to provide xenon gas to the neutralizer; the power processing and control unit sequentially provides the neutralizer with a neutralizer heating power source I NJ1 , Neutralizer touch power supply I NC1 , Neutralizer ignition power supply U N1 , and the neutralizer heating power supply I NJ1 The opening time of the neutralizer is NC1 The opening time of the neutralizer ignition power supply U N1 The opening time of the main cathode heating power supply I MJ1 The opening time, main cathode contact power supply I MC1 The opening time, main cathode ignition power supply U M1The opening time can ensure the control goal of neutralizer arc starting first.

[0068] In step S100, the main cathode ignition control timing of the ion electric propulsion system startup timing control is obtained, including: the time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the neutralizer is the same as the time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the main cathode; the main cathode heating power supply I MJ1 The opening time is set at the neutralizer heating power supply I NJ1 After the opening time; the main cathode touch power supply I MC1 The start time is after the anode gas supply balance is stable and before the start time of the anode power supply; the main cathode ignition power supply U M1 The start time of the anode power supply is after the start time of the anode power supply; the main cathode arc starting time and the discharge chamber arc starting time are the same time, which can ensure the control target of the shortest main cathode ignition time.

[0069] In step S100, the arcing control timing of the discharge chamber of the startup timing control of the ion electric propulsion system is obtained, including: the anode gas supply accounts for the majority of the propellant supply of the entire ion electric propulsion system. In order to reduce the propellant loss, the anode xenon gas supply lags behind the neutralizer xenon gas supply and the main cathode xenon gas supply. After the neutralizer arcs successfully, the anode xenon gas supply switch of the startup timing control of the ion electric propulsion system is turned on; the anode gas supply balance time of the startup timing control of the ion electric propulsion system can be set according to the length of the pipeline; the anode arcing current gear of the startup timing control of the ion electric propulsion system is set according to the differences of the thrusters; the control targets of the shortest anode gas supply balance time and stable arcing of the discharge chamber can be ensured. The anode arcing current gear is the anode power supply stability gear, which can be used I A2 express.

[0070] In step S100, the obtained beam extraction control sequence of the ion electric propulsion system startup sequence control includes: the beam is loaded and extracted after the discharge chamber arc is stabilized for a period of time, which is related to the set discharge chamber stabilization time and the extraction beam timing T. According to the set discharge chamber stabilization time and the extraction beam timing T, the beam extraction of the ion electric propulsion system startup sequence control is loaded; it can ensure the inconsistency of the start preparation time of different thrusters, and the inconsistency of the start preparation time of the same thruster at the beginning and end of its life. The set discharge chamber stabilization time, also known as the set discharge chamber arc stabilization time, can be the following set gear stabilization time t9.

[0071] Step S200, according to the neutralizer ignition control timing, the main cathode ignition control timing and the discharge chamber arcing control timing, the neutralizer arcing, the main cathode arcing and the discharge chamber arcing of the ion electric propulsion system startup timing control are performed. In the embodiment of the present application, the specific process of step S200 is as follows:

[0072] Step S201: The ion electric propulsion system is ignited and started, and the beam loading timing T is the timing of extracting the beam. In this step, the beam loading timing T can be the ignition timing 10 minutes.

[0073] Step S202: The power processing and control unit controls the storage and supply unit to provide the ion thruster neutralizer and the main cathode with flow rates of f and N and f M of xenon as propellant; where f N is the neutralizer supply air flow rate, f M is the gas flow rate for the main cathode. M =0.136mg / s, f N =0.136mg / s.

[0074] Step S203: The power processing and control unit provides output power to the thruster neutralizer according to the set power level, and the output power is the neutralizer heating power I NJ1 Neutralizer touch-hold power supply I NC1 After a delay of t1, the neutralizer heating power supply threshold monitoring is turned on, and after a delay of t2, the main cathode heating power supply I is turned on. MJ1 , and then after a delay of t3, the main cathode heating power supply threshold monitoring is turned on. NJ1 =7.5A, I NC1 =1.9A, t1=10s, turning on the neutralizer heating power threshold monitoring is to turn on the neutralizer 7.5A heating current out-of-tolerance judgment function; t2=160s, I MJ1 =7.5A, t3=10s, turning on the main cathode heating power threshold monitoring means turning on the main cathode 7.5A heating current and its out-of-tolerance judgment function.

[0075] Step S204: After a delay of t4, the neutralizer ignition power supply U is turned on. N1 , and judge whether the neutralizer holding current reaches the neutralizer arc starting success criterion I within the time t5. NC2 Once reached, the neutralizer heating power supply threshold monitoring and neutralizer heating power supply I are immediately turned off. NJ1 And neutralizer ignition power supply U N1 , the neutralizer starts the arc successfully. In this step, t4 = 10s, and the delay t4 is the main cathode 7.5A heating current over-tolerance judgment function is turned on for 10s; U N1=1000V pulse ignition power supply; t5 = 180s, if it is judged that the neutralizer holding current reaches 1.9A, the neutralizer will have priority in arcing success; if it is judged that the neutralizer holding current does not reach the neutralizer arcing success judgment criterion I within 180s, NC2 , the neutralizer fails to start the arc and enters the fault mode.

[0076] Step S205: Once the neutralizer successfully starts the arc, the power processing and control unit immediately controls the storage and supply unit to open the anode passage to supply the anode with an anode supply gas flow rate of f. A The xenon gas is used as the propellant, and the anode gas supply balance time t6 is set in combination with the actual gas supply pipeline length. When the anode gas supply reaches t6 and stabilizes, the power processing and control unit sequentially provides the main cathode holding power I for the ion thruster. MC1 , Anode power supply arc starting position I A1 , Main cathode ignition power supply U M1 , and judge whether the anode current reaches the discharge chamber arc ignition success criterion I within the time t7. A2 Once reached, the main cathode heating power supply threshold monitoring and main cathode heating power supply I are immediately turned off. MJ1 And the main cathode ignition power supply U M1 After t8, the anode current is adjusted to the arc-starting stable position I A2 , the main cathode arc is successfully started and the discharge chamber arc is successfully started. At this stage, the multi-objective optimal control of the shortest main cathode ignition time, the shortest anode gas supply balance time and the stable arc starting of the discharge chamber is achieved. A =1.09mg / s, t6=160s, I MC1 =0.8A, I A1 =4.6A, U M1 =1000V pulse ignition power supply, t7=180s, I A2 =1.0A; t8=30s, I A2 =2.6A; if the discharge chamber fails to successfully start an arc within 180s, it will enter the fault mode.

[0077] The above neutralizer air supply rate f N , main cathode air supply rate f M and anode gas flow rate f A All can be changed by data injection. Figure 2 In the case shown, they are: 0.136 mg / s, 0.136 mg / s and 1.090 mg / s respectively.

[0078] Step S300, after the arc is successfully started in the discharge chamber, the beam extraction of the ion electric propulsion system is started according to the beam extraction control timing.

[0079] In the embodiment of the present application, the arc is successfully started in the discharge chamber, and when the set gear stabilization time t9 is reached and the ion electric propulsion system ignition start time reaches the beam loading timing T, the screen grid power supply U is loaded at the same time. S And acceleration power U A , so that the beam can be extracted. T = 10min in this step, U S =1000V, U A =185V.

[0080] Step S400, after the beam is extracted successfully, a power out-of-tolerance judgment is performed on the ion electric propulsion system startup timing control. If the power out-of-tolerance judgment is passed, the ion electric propulsion system startup timing control is successfully started.

[0081] In the embodiment of the present application, in order to solve the problem that overshoot and unstable plasma discharge may occur at the moment of loading of each power supply provided by the power processing and control unit, sufficient time is set for the stability of overshoot power supply and plasma discharge before judging the power supply out of tolerance, so as to ensure the strong robustness control target of starting the ion electric propulsion system. The power supply out of tolerance judgment is also called power supply threshold out of tolerance judgment and power supply electrical parameter threshold judgment; the power supply out of tolerance judgment includes out of tolerance judgment of power supply parameters such as screen grid voltage, screen grid current, acceleration current, anode voltage, anode power supply, main cathode touch-holding power supply, and neutralizer touch-holding power supply.

[0082] Figure 3 This is a schematic diagram of the electrical parameter curve of the actual ignition and startup process of the ion electric propulsion system, involving the PPMA screen grid current and PPMA anode voltage. Figure 3 The PPMA anode current in is the anode power supply, and the PPMA current is the neutralizer heating power supply I NJ1 PPMA main current is the main cathode heating power supply I MJ1 PPMA main contact current is the main cathode contact holding power I MC1 , the contact current in PPMA is the neutralizer contact holding power I NC1 After the beam is extracted successfully, the embodiment of the present application starts the beam continuous flashing protection function, and after stabilization for 5 seconds, the anode current is adjusted to the rated gear I according to the power operation of the ion electric propulsion system. A3 , the ion thruster beam moves to the corresponding gear and at t 10 After a certain time, the power supply is judged to be out of tolerance. If it does not enter the fault mode, the ion electric propulsion system is successfully ignited and started. A3 =4.0A, t 10 =5s. At this stage, the flexible adjustment of the arc stabilization time of the discharge chamber, the beam loading timing and the start time of the power supply deviation judgment realizes the wide range adjustment of the thruster ignition start time and the strong robustness control of the entire start sequence.

[0083] The times T, t1, t2, t3L mentioned above are 10 , all of which can be changed by data injection, ensuring the strong robustness control of the startup timing of the ion electric propulsion system in this application. Figure 2 In the case shown, the specific description and value of each time are shown in Table 1.

[0084] Table 1

[0085] time describe Figure 2 The value in Remark T Extraction beam timing 10min Injectable adjustment <![CDATA[t1]]> Neutralizer heating current threshold monitoring delay time 10s Injectable adjustment <![CDATA[t2]]> Main cathode heating current start delay time 160s Injectable adjustment <![CDATA[t3]]> Main cathode heating current threshold monitoring delay time 10s Injectable adjustment <![CDATA[t4]]> Neutralizer ignition power on delay time 10s Injectable adjustment <![CDATA[t5]]> Neutralizer ignition judgment time 180s Injectable adjustment <![CDATA[t6]]> Anode gas supply balance time 160s Injectable adjustment <![CDATA[t7]]> Main cathode ignition judgment time 180s Injectable adjustment <![CDATA[t8]]> Discharge chamber jump delay time 30s Injectable adjustment <![CDATA[t9]]> Discharge chamber arc stabilization time 60s Injectable adjustment <![CDATA[t 10 ]]> Power threshold out-of-tolerance judgment start delay time 5s Injectable adjustment

[0086] The above mentioned I NJ1 ,I NC1 ,I NC2 All power supply parameters can be set. Figure 2 In the case shown, the specific instructions and descriptions of the electrical parameters of each power supply are shown in Table 2 below.

[0087] Table 2

[0088]

[0089] Figure 2A specific engineering example is given. First, the ignition timing is started for 10 minutes. After 10 minutes, the screen power supply and the acceleration power supply are turned on to realize beam extraction. The ignition timing time is the preparation time before beam extraction, including neutralizer ignition, main cathode ignition, discharge chamber arcing, and stable balance time after arcing; FCM temperature closed-loop control is started. FCM is a thermal throttling flow control module. There are three temperatures corresponding to the neutralizer flow, main cathode flow, and anode flow. The three-way temperature control means that the three-way flow control is in place. This step only opens the neutralizer gas supply valve and the main cathode gas supply valve, and does not open the anode gas supply valve; open the bus to provide 100V bus power input for the PPCU power processing and control unit. ; Set the power code according to the standby configuration to achieve the size setting of the neutralizer heating current and the main cathode heating current, the default is 7.5A; turn on the DCAC control, which includes turning on the neutralizer holding power supply, the neutralizer heating power supply, and the main cathode heating power supply. The main cathode heating power supply is only used to judge the health status of the power supply. It will be turned off immediately after 10s, and the neutralizer heating current threshold monitoring will be started at the same time; delay 160s to officially turn on the main cathode heating power supply, and start the main cathode heating current threshold monitoring after 10s; turn on the neutralizer ignition power supply after another 10s, and judge whether the neutralizer is ignited successfully within the next 180s. The success criterion is that the neutralizer holding current is ≥0.8A. If it is not successful, shut down. If successful, turn off the neutralizer heating current threshold monitoring, turn off the neutralizer heating power supply, turn off the neutralizer ignition power supply, and start the neutralizer arc extinction monitoring; open the FCM anode passage, open the anode gas supply valve, officially start the anode gas supply, and balance for 160s; then turn on the main cathode contact power supply, turn on the anode power supply, and turn on the main cathode ignition power supply; in the following 180s, judge whether the discharge chamber is ignited successfully. The success criterion is that the anode current is ≥1.0A. If it is not successful, shut down. If successful, turn off the main cathode heating current threshold monitoring, turn off the main cathode heating power supply, and turn off the main cathode ignition power supply; after a delay of 30s, lower the anode current to 2.6A and stabilize it for 60s to prepare for the low-power beam current. Preparation; start the arc extinction monitoring of the discharge chamber and wait for the 10min timing to end; turn on the screen grid power supply and the acceleration power supply. This step realizes the beam extraction at low power, and the thrust is generated from this moment; start the ignition protection monitoring to ensure that the thruster can operate stably; delay 5s, and adjust the anode power supply to the rated gear of the set power, that is, restore to the state of 90% of the rated power; start the screen grid current closed-loop adjustment, indicating that the remaining 10% of the power will be supplemented by the screen grid current closed-loop; after a delay of 5s, determine whether the power supply tolerance is enabled. If enabled, determine whether any power supply is out of tolerance. If it is out of tolerance, shut down. If it is not out of tolerance, repeat the above tolerance judgment process until the shutdown command is received; at this point, the thruster autonomous operation ends.

[0090] In an embodiment of the present application, the ion electric propulsion system startup timing control method obtains the neutralizer ignition control timing, main cathode ignition control timing, discharge chamber arc starting control timing and beam lead control timing of the ion electric propulsion system startup timing control; performs neutralizer arc starting, main cathode arc starting and discharge chamber arc starting of the ion electric propulsion system startup timing control according to the neutralizer ignition control timing, the main cathode ignition control timing and the discharge chamber arc starting control timing; after the arc starting in the discharge chamber is successful, the beam extraction of the ion electric propulsion system startup timing control is performed according to the beam lead control timing; after the beam extraction is successful, the power supply out-of-tolerance judgment of the ion electric propulsion system startup timing control is performed, and if the power supply out-of-tolerance judgment is passed, the ion electric propulsion system of the ion electric propulsion system startup timing control is successfully started. Under the premise of ensuring that the ion electric propulsion system can be started normally, the present application realizes the optimization of the ion thruster ignition timing, and achieves the purpose of neutralizer priority arc starting, shortest main cathode ignition time, shortest anode gas supply balance time, stable discharge chamber arc starting, wide range adjustable thruster ignition start time, and strong robustness control of the entire startup timing.

[0091] The following are embodiments of the apparatus of the present invention, which can be used to implement the embodiments of the method of the present invention. For details not disclosed in the embodiments of the apparatus of the present invention, please refer to the embodiments of the method of the present invention.

[0092] See also Figure 4 , which shows a schematic diagram of the structure of an ion electric propulsion system startup timing control device provided by an exemplary embodiment of the present invention. The device includes: an acquisition module 10000, an arc starting module 20000, a beam extraction module 30000 and a judgment module 40000.

[0093] An acquisition module 10000 is used to acquire the neutralizer ignition control timing, the main cathode ignition control timing, the discharge chamber arc control timing and the guide beam current control timing of the ion electric propulsion system startup timing control;

[0094] The arc starting module 20000 is used to perform the neutralizer arc starting, the main cathode arc starting and the discharge chamber arc starting of the ion electric propulsion system startup timing control according to the neutralizer ignition control timing, the main cathode ignition control timing and the discharge chamber arc starting control timing;

[0095] A beam extraction module 30000 is used to extract the beam according to the start-up timing control of the ion electric propulsion system according to the beam extraction control timing after the arc in the discharge chamber is successfully started;

[0096] The judgment module 40000 is used to perform a power out-of-tolerance judgment on the ion electric propulsion system startup timing control after the beam is extracted successfully. If the power out-of-tolerance judgment is passed, the ion electric propulsion system with the ion electric propulsion system startup timing control is started successfully.

[0097] According to a preferred embodiment, in the acquisition module 10000, the neutralizer ignition control timing of the ion electric propulsion system startup timing control obtained includes:

[0098] The power processing and control unit controls the storage and supply unit to provide xenon gas to the neutralizer;

[0099] The power processing and control unit provides the neutralizer with a neutralizer heating power supply, a neutralizer holding power supply, and a neutralizer ignition power supply in sequence, and the start-up time of the neutralizer heating power supply, the start-up time of the neutralizer holding power supply, and the start-up time of the neutralizer ignition power supply are respectively earlier than the start-up time of the main cathode heating power supply, the start-up time of the main cathode holding power supply, and the start-up time of the main cathode ignition power supply.

[0100] According to a preferred embodiment, in the acquisition module 10000, the main cathode ignition control timing of the ion electric propulsion system startup timing control obtained includes:

[0101] The time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the neutralizer is the same as the time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the main cathode;

[0102] The start time of the main cathode heating power supply is set after the start time of the neutralizer heating power supply;

[0103] The main cathode holding power supply is turned on after the anode gas supply balance is stabilized and before the anode power supply is turned on;

[0104] The main cathode ignition power supply is turned on after the anode power supply is turned on;

[0105] The arc starting time of the main cathode is the same as the arc starting time of the discharge chamber.

[0106] According to a preferred embodiment, in the acquisition module 10000, the acquired discharge chamber arcing control timing of the ion electric propulsion system startup timing control includes:

[0107] After the neutralizer arc is successfully started, the anode xenon gas supply switch of the ion electric propulsion system start-up timing control is turned on;

[0108] According to the length of the pipeline, setting the anode gas supply balance time of the ion electric propulsion system start-up timing control;

[0109] According to the differences of thrusters, the anode arc starting current gear of the ion electric propulsion system startup timing control is set.

[0110] According to a preferred embodiment, in the acquisition module 10000, the obtained guide beam flow control timing of the ion electric propulsion system startup timing control includes:

[0111] According to the set discharge chamber stabilization time and beam extraction timing, the ion electric propulsion system is loaded to start the beam extraction with timing control.

[0112] It should be noted that the ion electric propulsion system startup timing control device provided in the above embodiment only uses the division of the above functional modules as an example when executing the ion electric propulsion system startup timing control method. In actual applications, the above functions can be assigned to 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 ion electric propulsion system startup timing control device provided in the above embodiment and the ion electric propulsion system startup timing control embodiment belong to the same concept, and the implementation process thereof is detailed in the method embodiment, which will not be repeated here.

[0113] In an embodiment of the present application, the ion electric propulsion system startup timing control device obtains the neutralizer ignition control timing, main cathode ignition control timing, discharge chamber arc starting control timing and beam lead control timing of the ion electric propulsion system startup timing control; performs neutralizer arc starting, main cathode arc starting and discharge chamber arc starting of the ion electric propulsion system startup timing control according to the neutralizer ignition control timing, the main cathode ignition control timing and the discharge chamber arc starting control timing; after the arc starting in the discharge chamber is successful, the beam extraction of the ion electric propulsion system startup timing control is performed according to the beam lead control timing; after the beam extraction is successful, the power supply out-of-tolerance judgment of the ion electric propulsion system startup timing control is performed, and if the power supply out-of-tolerance judgment is passed, the ion electric propulsion system of the ion electric propulsion system startup timing control is successfully started. Under the premise of ensuring that the ion electric propulsion system can be started normally, the present application realizes the optimization of the ion thruster ignition timing, and achieves the purpose of neutralizer priority arc starting, shortest main cathode ignition time, shortest anode gas supply balance time, stable discharge chamber arc starting, wide range adjustable thruster ignition start time, and strong robustness control of the entire startup timing.

[0114] The present invention also provides a computer-readable medium having program instructions stored thereon, and when the program instructions are executed by a processor, the ion electric propulsion system startup timing control method provided by the above-mentioned various method embodiments is implemented.

[0115] The present invention also provides a computer program product containing instructions, which, when executed on a computer, enables the computer to execute the ion electric propulsion system startup timing control method of each of the above method embodiments.

[0116] See also Figure 5 , 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.

[0117] The communication bus 1002 is used to realize the connection and communication between these components.

[0118] 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.

[0119] The network interface 1004 may optionally include a standard wired interface or a wireless interface (such as a WI-FI interface).

[0120] 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.

[0121] 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 5 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 startup timing control application.

[0122] exist Figure 5 In 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 startup timing control application stored in the memory 1005, and specifically perform the following operations:

[0123] Obtain the neutralizer ignition control timing, main cathode ignition control timing, discharge chamber arc control timing and beam current control timing of the ion electric propulsion system startup timing control;

[0124] According to the neutralizer ignition control timing, the main cathode ignition control timing and the discharge chamber arc ignition control timing, the neutralizer arc ignition, the main cathode arc ignition and the discharge chamber arc ignition of the ion electric propulsion system startup timing control are performed;

[0125] After the arc is successfully started in the discharge chamber, the beam extraction of the ion electric propulsion system is performed according to the beam extraction control timing sequence;

[0126] After the beam extraction is successful, a power out-of-tolerance judgment is performed for the ion electric propulsion system startup sequence control. If the power out-of-tolerance judgment is passed, the ion electric propulsion system of the ion electric propulsion system startup sequence control is successfully started;

[0127] The obtained neutralizer ignition control timing of the ion electric propulsion system startup timing control includes:

[0128] The power processing and control unit controls the storage and supply unit to provide xenon gas to the neutralizer;

[0129] The power processing and control unit provides the neutralizer with a neutralizer heating power supply, a neutralizer holding power supply, and a neutralizer ignition power supply in sequence, and the start-up time of the neutralizer heating power supply, the start-up time of the neutralizer holding power supply, and the start-up time of the neutralizer ignition power supply are respectively earlier than the start-up time of the main cathode heating power supply, the start-up time of the main cathode holding power supply, and the start-up time of the main cathode ignition power supply.

[0130] The main cathode ignition control timing of the ion electric propulsion system startup timing control obtained includes:

[0131] The time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the neutralizer is the same as the time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the main cathode;

[0132] The start time of the main cathode heating power supply is set after the start time of the neutralizer heating power supply;

[0133] The main cathode holding power supply is turned on after the anode gas supply balance is stabilized and before the anode power supply is turned on;

[0134] The main cathode ignition power supply is turned on after the anode power supply is turned on;

[0135] The arc starting time of the main cathode is the same as the arc starting time of the discharge chamber.

[0136] The obtained discharge chamber arcing control timing of the ion electric propulsion system startup timing control includes:

[0137] After the neutralizer arc is successfully started, the anode xenon gas supply switch of the ion electric propulsion system start-up timing control is turned on;

[0138] According to the length of the pipeline, setting the anode gas supply balance time of the ion electric propulsion system start-up timing control;

[0139] According to the differences of thrusters, the anode arc starting current gear of the ion electric propulsion system startup timing control is set.

[0140] The obtained guide beam flow control timing of the ion electric propulsion system startup timing control includes:

[0141] According to the set discharge chamber stabilization time and beam extraction timing, the ion electric propulsion system is loaded to start the beam extraction with timing control.

[0142] In an embodiment of the present application, the method and device for controlling the startup timing of an ion electric propulsion system obtain the neutralizer ignition control timing, the main cathode ignition control timing, the discharge chamber arc starting control timing and the beam lead control timing of the startup timing control of the ion electric propulsion system; according to the neutralizer ignition control timing, the main cathode ignition control timing and the discharge chamber arc starting control timing, the neutralizer arc starting, the main cathode arc starting and the discharge chamber arc starting of the startup timing control of the ion electric propulsion system are performed; after the arc starting in the discharge chamber is successful, the beam extraction of the startup timing control of the ion electric propulsion system is performed according to the beam lead control timing; after the beam extraction is successful, the power supply out-of-tolerance judgment of the startup timing control of the ion electric propulsion system is performed, and if the power supply out-of-tolerance judgment is passed, the ion electric propulsion system of the startup timing control of the ion electric propulsion system is successfully started. Under the premise of ensuring that the ion electric propulsion system can be started normally, the present application realizes the optimization of the ion thruster ignition timing, and achieves the purpose of neutralizer priority arc starting, shortest main cathode ignition time, shortest anode gas supply balance time, stable discharge chamber arc starting, wide range adjustable thruster ignition start time, and strong robustness control of the entire startup timing.

[0143] 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.

[0144] 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 startup sequence of an ion electric propulsion system, characterized in that: The following steps are involved: Obtain the neutralizer ignition control timing, main cathode ignition control timing, discharge chamber arc control timing and beam current control timing of the ion electric propulsion system startup timing control; According to the neutralizer ignition control timing, the main cathode ignition control timing and the discharge chamber arc ignition control timing, the neutralizer arc ignition, the main cathode arc ignition and the discharge chamber arc ignition of the ion electric propulsion system startup timing control are performed; After the arc is successfully started in the discharge chamber, the beam extraction of the ion electric propulsion system is performed according to the beam extraction control timing sequence; After the beam is extracted successfully, a power out-of-tolerance judgment is performed on the ion electric propulsion system startup timing control. If the power out-of-tolerance judgment is passed, the ion electric propulsion system of the ion electric propulsion system startup timing control is successfully started.

2. The method for controlling the startup sequence of an ion electric propulsion system according to claim 1, characterized in that: The obtained neutralizer ignition control timing of the ion electric propulsion system startup timing control includes: The power processing and control unit controls the storage and supply unit to provide xenon gas to the neutralizer; The power processing and control unit provides the neutralizer with a neutralizer heating power supply, a neutralizer holding power supply, and a neutralizer ignition power supply in sequence, and the start-up time of the neutralizer heating power supply, the start-up time of the neutralizer holding power supply, and the start-up time of the neutralizer ignition power supply are respectively earlier than the start-up time of the main cathode heating power supply, the start-up time of the main cathode holding power supply, and the start-up time of the main cathode ignition power supply.

3. The method for controlling the startup sequence of an ion electric propulsion system according to claim 2, characterized in that: The main cathode ignition control timing of the ion electric propulsion system startup timing control obtained includes: The time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the neutralizer is the same as the time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the main cathode; The start time of the main cathode heating power supply is set after the start time of the neutralizer heating power supply; The main cathode holding power supply is turned on after the anode gas supply balance is stabilized and before the anode power supply is turned on; The main cathode ignition power supply is turned on after the anode power supply is turned on; The arc starting time of the main cathode is the same as the arc starting time of the discharge chamber.

4. The method for controlling the startup sequence of an ion electric propulsion system according to claim 1, characterized in that: The obtained discharge chamber arcing control timing of the ion electric propulsion system startup timing control includes: After the neutralizer arc is successfully started, the anode xenon gas supply switch of the ion electric propulsion system start-up timing control is turned on; According to the length of the pipeline, setting the anode gas supply balance time of the ion electric propulsion system start-up timing control; According to the differences of thrusters, the anode arc starting current gear of the ion electric propulsion system startup timing control is set.

5. The method for controlling the startup sequence of an ion electric propulsion system according to claim 1, characterized in that: The obtained guide beam flow control timing of the ion electric propulsion system startup timing control includes: According to the set discharge chamber stabilization time and beam extraction timing, the ion electric propulsion system is loaded to start the beam extraction with timing control.

6. An ion electric propulsion system startup timing control device, characterized in that: include: An acquisition module is used to acquire the neutralizer ignition control timing, main cathode ignition control timing, discharge chamber arc control timing and beam current control timing of the ion electric propulsion system startup timing control; An arc starting module, used for performing neutralizer arc starting, main cathode arc starting and discharge chamber arc starting of the ion electric propulsion system startup timing control according to the neutralizer ignition control timing, the main cathode ignition control timing and the discharge chamber arc starting control timing; A beam extraction module, used for extracting the beam according to the start-up timing control of the ion electric propulsion system according to the beam extraction control timing after the arc in the discharge chamber is successfully started; The judgment module is used to perform power out-of-tolerance judgment on the ion electric propulsion system startup timing control after the beam is successfully extracted. If the power out-of-tolerance judgment is passed, the ion electric propulsion system with the ion electric propulsion system startup timing control is successfully started.

7. The ion electric propulsion system startup timing control device according to claim 6, characterized in that: In the acquisition module, the neutralizer ignition control timing of the ion electric propulsion system startup timing control obtained includes: The power processing and control unit controls the storage and supply unit to provide xenon gas to the neutralizer; The power processing and control unit provides the neutralizer with a neutralizer heating power supply, a neutralizer holding power supply, and a neutralizer ignition power supply in sequence, and the start-up time of the neutralizer heating power supply, the start-up time of the neutralizer holding power supply, and the start-up time of the neutralizer ignition power supply are respectively earlier than the start-up time of the main cathode heating power supply, the start-up time of the main cathode holding power supply, and the start-up time of the main cathode ignition power supply.

8. The ion electric propulsion system startup timing control device according to claim 6, characterized in that: In the acquisition module, the main cathode ignition control timing of the ion electric propulsion system startup timing control obtained includes: The time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the neutralizer is the same as the time when the power processing and control unit controls the storage and supply unit to provide the xenon gas to the main cathode; The start time of the main cathode heating power supply is set after the start time of the neutralizer heating power supply; The main cathode holding power supply is turned on after the anode gas supply balance is stabilized and before the anode power supply is turned on; The main cathode ignition power supply is turned on after the anode power supply is turned on; The arc starting time of the main cathode is the same as the arc starting time of the discharge chamber.

9. The ion electric propulsion system startup timing control device according to claim 6, characterized in that: In the acquisition module, the acquired discharge chamber arcing control timing of the ion electric propulsion system startup timing control includes: After the neutralizer arc is successfully started, the anode xenon gas supply switch of the ion electric propulsion system start-up timing control is turned on; According to the length of the pipeline, setting the anode gas supply balance time of the ion electric propulsion system start-up timing control; According to the differences of thrusters, the anode arc starting current gear of the ion electric propulsion system startup timing control is set.

10. The ion electric propulsion system startup timing control device according to claim 6, characterized in that: In the acquisition module, the obtained guide beam flow control timing of the ion electric propulsion system startup timing control includes: According to the set discharge chamber stabilization time and beam extraction timing, the ion electric propulsion system is loaded to start the beam extraction with timing control.

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