CN112347610B - Hall thruster service life evaluation method based on hollow cathode - Google Patents

Hall thruster service life evaluation method based on hollow cathode Download PDF

Info

Publication number
CN112347610B
CN112347610B CN202011063440.3A CN202011063440A CN112347610B CN 112347610 B CN112347610 B CN 112347610B CN 202011063440 A CN202011063440 A CN 202011063440A CN 112347610 B CN112347610 B CN 112347610B
Authority
CN
China
Prior art keywords
hall thruster
different particles
hollow cathode
neutral atoms
discharge cavity
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN202011063440.3A
Other languages
Chinese (zh)
Other versions
CN112347610A (en
Inventor
陈娟娟
吴辰宸
李文峰
孙新锋
蒲彦旭
李兴达
郭宁
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Lanzhou Institute of Physics of Chinese Academy of Space Technology
Original Assignee
Lanzhou Institute of Physics of Chinese Academy of Space Technology
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Lanzhou Institute of Physics of Chinese Academy of Space Technology filed Critical Lanzhou Institute of Physics of Chinese Academy of Space Technology
Priority to CN202011063440.3A priority Critical patent/CN112347610B/en
Publication of CN112347610A publication Critical patent/CN112347610A/en
Application granted granted Critical
Publication of CN112347610B publication Critical patent/CN112347610B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00—Using plasma to produce a reactive propulsive thrust
    • F03H1/0037—Electrostatic ion thrusters
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/04—Ageing analysis or optimisation against ageing

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Geometry (AREA)
  • Computer Hardware Design (AREA)
  • Evolutionary Computation (AREA)
  • Plasma & Fusion (AREA)
  • Mechanical Engineering (AREA)
  • Computer Graphics (AREA)
  • Software Systems (AREA)
  • Plasma Technology (AREA)
  • Management, Administration, Business Operations System, And Electronic Commerce (AREA)

Abstract

The method for evaluating the service life of the Hall thruster based on the hollow cathode comprises the steps of establishing a three-dimensional simulation model of the Hall thruster; injecting neutral atoms into the discharge cavity, simulating collision among the neutral atoms, and calculating the density, the speed distribution and the electrostatic field distribution of the neutral atoms when the neutral atoms reach a convergence state; the hollow cathode emits electrons into the discharge cavity, the electrons and neutral atoms collide under the action of electrostatic field distribution to obtain different particles, and the velocity distribution of the different particles is calculated; counting the number of different particles which are out of bounds, and calculating the performance parameters of the Hall thruster according to the number and the speed distribution of the different particles; and comparing the measurement result and the calculation result of the performance parameters, and when the error is smaller than the error precision, calculating the sputtering corrosion rate and the sputtering corrosion depth of different particles to the hollow cathode contact electrode respectively, and evaluating the service life of the Hall thruster. The performance and the service life of the Hall thruster can be rapidly evaluated, and the research and development efficiency is improved.

Description

Hall thruster life evaluation method based on hollow cathode
Technical Field
The disclosure belongs to the technical field of thruster service life assessment, and particularly relates to a service life assessment method of a Hall thruster based on a hollow cathode.
Background
The Hall thruster ionizes electrons drifting along a Hall and working media into ions, and the ions are accelerated to be sprayed out under the action of an axial electric field in a channel to generate recoil thrust. Meanwhile, electrons reach the anode through conduction, a stable plasma discharge process is realized in the channel, and continuous and stable thrust is formed.
The generation process of the plasma is the most important physical process in the hall thruster, and the performance of the hall thruster is largely determined by the characteristics of the density, uniformity and the like of the plasma generated in the hall thruster. In fact, the lifetime of the hall thruster is also largely determined by the density and uniformity of the plasma, because the ions in the plasma generated by the hall thruster will exchange charges with the neutral gas leaked from the thruster or the neutral gas leaked from the neutralizer in the plume region of the thruster, and then generate fast neutral atoms and slow ions in the beam direction. A local electric field is generated under the interaction of the accelerating electric field at the outlet region of the thruster and the plasma of the neutralizer, and slow ions flow back to the thruster under the action of the local electric field or impact nearby spacecraft parts after being accelerated.
The bombardment of plasma on spacecraft parts is that as the thruster is continuously operated, some parts are subjected to ion sputtering abrasion and finally cause performance degradation or failure, and further cause failure of the Hall thruster, and the bombardment is time-dependent and is a long-term accumulation process. It is difficult to accurately measure or evaluate the thruster during the test of the thruster test. The numerical simulation method has low cost and high efficiency, so that the numerical simulation method is always the main method for researching the plasma generation and evolution process. However, the composition of the plasma in the hall thruster is complex, the characteristic difference of different particles is huge, and the generation of the plasma and the bombardment sputtering process of ions to the spacecraft component assembly are coupled together, so that the difficulty in developing a model for evaluating the service life of the hall thruster is high. In addition, the Hall thruster is only provided with one neutralizer, and the thruster structure has a non-axisymmetric condition, so that a three-dimensional simulation model needs to be established to research the Hall thruster.
Disclosure of Invention
In view of the above, the disclosure provides a method for evaluating the service life of a hall thruster based on a hollow cathode, which improves the calculation accuracy of performance parameters of the hall thruster by simulating the whole working process of a hall sensor, and can quickly evaluate the performance and the service life of the hall thruster; saving research and development cost and improving research and development efficiency.
According to an aspect of the present disclosure, a method for estimating a lifetime of a hollow cathode based hall thruster is provided, the method including:
establishing a three-dimensional simulation model of the Hall thruster, wherein the three-dimensional simulation model comprises a hollow cathode, a discharge cavity and a plume region, and the discharge cavity is communicated with the plume region;
injecting neutral atoms into the discharge cavity, simulating collision among the neutral atoms by using a Monte Carlo method, and calculating density distribution and speed distribution of the neutral atoms in the discharge cavity and the plume region and electrostatic field distribution in the discharge cavity when the neutral atoms reach a convergence state;
the hollow cathode emits original electrons into the discharge cavity, the original electrons and the neutral atoms collide under the action of the electrostatic field to obtain different particles, and the velocity distribution of the different particles is calculated;
counting the number of different particles out of the right boundary of the plume region, and calculating to obtain the performance parameters of the Hall thruster according to the number and the speed distribution of the different particles;
measuring the performance parameters of the Hall thruster in real time, comparing the measurement results of the performance parameters with the calculation results, and calculating the sputter etching rate and the sputter etching depth of different particles to the contact electrode of the hollow cathode respectively when the error between the measurement results and the calculation results is smaller than the preset error precision;
and comparing the sputtering corrosion rate and the sputtering etching depth of different particles to the contact level of the hollow cathode, and evaluating the service life of the Hall thruster.
In one possible implementation, the different particles include: secondary electrons, monovalent ions, divalent ions, monovalent charge exchange ions, and divalent charge exchange ions.
In one possible implementation, the collision between the original electron and the neutral atom results in different particles, including:
the primary electron and the neutral atom collide to obtain a secondary electron;
collision occurs between the secondary electrons and the neutral atoms to obtain monovalent ions and divalent ions;
and the primary electrons and the secondary electrons elastically and ionically collide with the monovalent ions, the neutral atoms elastically and exchange charges collide with the monovalent ions, and the neutral atoms elastically and exchange charges collide with the divalent ions to generate monovalent charge exchange ions and divalent charge exchange ions respectively.
In one possible implementation manner, the performance parameters of the hall thruster include: thrust, specific impulse and efficiency.
According to the method, a three-dimensional simulation model of the Hall thruster is established, wherein the three-dimensional simulation model comprises a hollow cathode, a discharge cavity and a plume region, and the discharge cavity is communicated with the plume region; injecting neutral atoms into the discharge cavity, simulating collision among the neutral atoms by using a Monte Carlo method, and calculating density distribution and speed distribution of the neutral atoms in the discharge cavity and the plume region and electrostatic field distribution in the discharge cavity when the neutral atoms reach a convergence state; the hollow cathode emits original electrons into the discharge cavity, under the action of the electrostatic field, the original electrons and the neutral atoms collide to obtain different particles, and the velocity distribution of the different particles is calculated; counting the number of different particles out of the right boundary of the plume region, and calculating to obtain the performance parameters of the Hall thruster according to the number and the speed distribution of the different particles; measuring the performance parameters of the Hall thruster in real time, comparing the measurement result with the calculation result of the performance parameters, counting the number of different particles bombarded on the surface of the hollow cathode contact electrode when the error between the measurement result and the calculation result is smaller than the preset error precision, and calculating the sputter etching rate and the sputter etching depth of the different particles to the contact electrode of the hollow cathode; and comparing the sputtering corrosion rate and the sputtering etching depth of different particles to the contact level of the hollow cathode, and evaluating the service life of the Hall thruster. The method can improve the calculation precision of the performance parameters of the Hall thruster, quickly evaluate the performance and the service life of the Hall thruster, save the research and development cost and improve the research and development efficiency.
Other features and aspects of the present disclosure will become apparent from the following detailed description of exemplary embodiments, which proceeds with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate exemplary embodiments, features, and aspects of the disclosure and, together with the description, serve to explain the principles of the disclosure.
Fig. 1 shows a flowchart of a method for estimating a lifetime of a hollow cathode based hall thruster according to an embodiment of the present disclosure;
fig. 2 illustrates a functional block diagram of a life evaluation method of a hollow cathode-based hall thruster according to another embodiment of the present disclosure.
Detailed Description
Various exemplary embodiments, features and aspects of the present disclosure will be described in detail below with reference to the accompanying drawings. In the drawings, like reference numbers can indicate functionally identical or similar elements. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments.
Furthermore, in the following detailed description, numerous specific details are set forth in order to provide a better understanding of the present disclosure. It will be understood by those skilled in the art that the present disclosure may be practiced without some of these specific details. In some instances, methods, means, elements and circuits that are well known to those skilled in the art have not been described in detail so as not to obscure the subject matter of the present disclosure.
Fig. 2 illustrates a block diagram of a hollow cathode based hall thruster according to another embodiment of the present disclosure. As shown in fig. 2, the hall thruster may include a hollow cathode, an anode, a magnet, a discharge chamber, and a plume region. Wherein, the discharge cavity is communicated with the plume region.
Fig. 1 shows a flowchart of a method for estimating the lifetime of a hollow cathode-based hall thruster according to an embodiment of the present disclosure. As shown in fig. 1, the method may include:
step S11: and establishing a three-dimensional simulation model of the Hall thruster, wherein the three-dimensional simulation model comprises a hollow cathode, a discharge cavity and a plume region, and the discharge cavity is communicated with the plume region.
The Hall thruster three-dimensional simulation model is established according to the structure of the Hall thruster shown in FIG. 2 and can comprise a hollow cathode, a discharge cavity and a plume region, wherein the discharge cavity is communicated with the plume region. Wherein the discharge chamber and plume region may be referred to as the calculation region of the hall thruster. In addition, according to actual measurement needs, the hall thruster three-dimensional simulation model may further include an ion optical system region, which is not limited herein.
Step S12: injecting neutral atoms into the discharge cavity, simulating collision among the neutral atoms by using a Monte Carlo method, and calculating density distribution and speed distribution of the neutral atoms in the discharge cavity and the plume region and electrostatic field distribution in the discharge cavity when the neutral atoms reach a convergence state.
In one example, neutral atoms are injected into the discharge chamber region as in fig. 2, the neutral atoms are tracked using a PIC (particle cloud) method, collisions between neutral atoms are simulated using a DSMC (monte carlo) method, e.g., N neutral atoms are included in a mesh, and the number of pairs of neutral atoms in the mesh that may be collided is calculated using the DSMC method
Figure BDA0002713075050000051
Probability p of collision between two atoms constituting a collision pair within Δ t time D ，
Figure BDA0002713075050000052
Wherein, F N For simulated atoms representing the true number of atomsAnd S Δ t is the grid volume swept by the relative velocity of the colliding neutral atom pairs, Δ t V c Is the volume of the grid. When the position and velocity of the neutral atoms satisfy the diffuse reflection, the part of the neutral atoms will go out from the right boundary of the plume region, otherwise return to the plume region. Counting the number of neutral atoms which are discharged from the right boundary of the plume region, when the number of the discharged neutral atoms is equal to the number of the neutral atoms which enter the discharge cavity region, enabling the neutral atoms of the discharge cavity of the Hall thruster and the plume region to reach a steady state, enabling the neutral atoms to be converged, automatically counting the number of the neutral atoms on each grid point, calculating the density distribution and the speed distribution of the neutral atoms on each grid point, and further obtaining the density distribution and the speed distribution of the neutral atoms in the whole calculation region (the discharge cavity and the plume region). The static magnetic field distribution of the static magnetic field in the discharge cavity can be calculated by adopting ANSYS software and by adopting a Laplace equation.
Step S13: and the hollow cathode emits original electrons into the discharge cavity, the original electrons and the neutral atoms collide under the action of the electrostatic field to obtain different particles, and the velocity distribution of the different particles is calculated.
In one example, the different particles may include: secondary electrons, monovalent ions, divalent ions, monovalent charge exchange ions, and divalent charge exchange ions. Secondary electrons can be obtained by collision between the primary electrons and neutral atoms; monovalent ions and divalent ions can be obtained by collision between secondary electrons and neutral atoms; primary and secondary electrons elastically and ionically collide with monovalent ions, neutral atoms and monovalent ions elastically and exchange charges, neutral atoms and divalent ions elastically and exchange charges collide, respectively, resulting in monovalent charge exchange ions and divalent charge exchange ions.
And emitting primary electrons into the discharge cavity by the hollow cathode, and tracking the primary electrons by adopting a PIC (particle cloud) method, wherein the velocity of the primary electrons obeys the Maxwell distribution. The number of the original electrons emitted into the discharge cavity by the hollow cathode and the emission current I of the hollow cathode e Related to the hollow cathode pore volume V, e.g. at Δ tThe number N of the original electrons emitted into the discharge cavity by the cathode of the hollow electrode in time p In which
Figure BDA0002713075050000061
The MCC (monte carlo) method can be used to simulate collisions between primary electrons and neutral atoms, producing secondary electrons; collisions between the newly generated secondary electrons and the neutral atoms generate monovalent ions and divalent ions. And calculating to obtain the density distribution and the speed distribution of the monovalent ions and the divalent ions in the whole calculation area according to the statistics of the number of the monovalent ions and the divalent ions of each grid point.
The MCC (Monte Carlo) method can be adopted to simulate the elastic and ionizing collision of primary electrons, secondary electrons and monovalent ions, the elastic and exchange charge collision of neutral atoms and monovalent ions, and the elastic and exchange charge collision of neutral atoms and divalent ions, so that monovalent charge exchange ions and divalent charge exchange ions which cannot be measured microscopically can be generated, and the density distribution and the speed distribution of the monovalent charge exchange ions and the divalent charge exchange ions in the whole calculation region can be calculated according to the statistics of the numbers of the monovalent charge exchange ions and the divalent charge exchange ions at each grid point.
Step S14: and counting the number of different particles out of the right boundary of the plume region, and calculating to obtain the performance parameters of the Hall thruster according to the number and the speed distribution of the different particles.
In an example, the performance parameters of the Hall thruster may include thrust force T, specific impulse I sp And efficiency eta.
For example, the number of particles exiting from the right boundary of the plume region of the calculation region is counted, and the thrust T of the thruster is calculated according to the relationship among the number of particles, the particle speed and the thrust,
Figure BDA0002713075050000071
wherein n is 1 、n 2 、n 11 、n 12 Respectively monovalent ion, divalent ion, monovalent charge exchange ion, divalent charge exchange ionThe number of children; m is i1 、m i2 、m i11 、m i12 Monovalent ion, divalent ion, monovalent charge exchange ion, divalent charge exchange ion mass, respectively; v. of i1 、v i2 、v i11 、v i12 The velocity of monovalent ion, divalent ion, monovalent charge exchange ion, and divalent charge exchange ion, respectively.
According to thrust T and specific impulse I sp Calculating the relation among the flow rate m of the working medium and the gravity acceleration g to obtain the specific impulse I of the thruster sp ，
Figure BDA0002713075050000072
Calculating to obtain the efficiency eta of the thruster according to the relationship among the thrust T, the flow rate m of the working medium and the power p,
Figure BDA0002713075050000073
through the relation, the performance parameters of the Hall thruster can be calculated.
Step S15: and measuring the performance parameters of the Hall thruster in real time, comparing the measurement result of the performance parameters with the calculation result, and calculating the sputtering corrosion rate and the sputtering etching depth of different particles on the contact electrode of the hollow cathode respectively when the error between the measurement result and the calculation result is smaller than the preset error precision.
The performance parameters of the Hall thruster can be measured in real time by using an oscilloscope to obtain the measurement results of the thrust, the specific impulse and the efficiency of the Hall thruster, the measurement results of the thrust, the specific impulse and the efficiency of the Hall thruster are compared with the calculation results of the Hall thruster, when the error between the measurement results and the calculation results is less than or equal to 10%, the calculation results of the three-dimensional simulation model of the Hall thruster are considered to be correct, and the number of different particles bombarded to the surface of the hollow cathode contact electrode is counted. Of course, the predetermined error accuracy of the hall thruster may be set to 15%, 5%, etc. according to actual needs, and is not limited herein.
By counting the number of different particles (monovalent ions, divalent ions, monovalent charge exchange ions and divalent charge exchange ions) bombarded on the surface of the hollow cathode contact electrode, the sputter etching rate r and the sputter etching depth h' of the hollow cathode contact electrode respectively caused by the different particles can be calculated.
For example, N is the number of particles bombarded onto the surface of the support electrode of the hollow cathode; m is i Is the mass of the particles; v. of i Is the particle velocity; t is total working time; f is the collision frequency of the particles colliding with the surface of the touch electrode of the hollow cathode; h is the thickness of the contact electrode of the hollow cathode, then
Figure BDA0002713075050000081
m and rho are respectively the mass and the mass density of the contact electrode material of the hollow cathode; d c 、t c The diameter and thickness of the contact electrode hole of the hollow cathode respectively
Figure BDA0002713075050000082
According to the formula of the sputtering corrosion rate and the sputtering etching depth of the hollow cathode holding pole, the sputtering corrosion rate and the sputtering etching depth of different particles such as monovalent ions, divalent ions, monovalent charge exchange ions, divalent charge exchange ions and the like on the hollow cathode holding pole can be calculated.
Step S16: and comparing the sputtering corrosion rate and the sputtering etching depth of different particles to the contact level of the hollow cathode, and evaluating the service life of the Hall thruster.
Wherein the working life of the Hall thruster
Figure BDA0002713075050000083
The working life of the Hall thruster under the sputtering corrosion state of different particles such as monovalent ions, divalent ions, monovalent charge exchange ions, divalent charge exchange ions and the like on the contact electrode of the hollow cathode can be calculated according to the working life of the Hall thruster, the most critical influence factors of the sputtering corrosion of the hollow cathode of the Hall thruster are analyzed to be the divalent ions and the monovalent charge exchange ions, the performance of the Hall thruster is optimized according to the analysis result, and the working life of the Hall thruster is prolonged.
According to the method, a three-dimensional simulation model of the Hall thruster is established, wherein the three-dimensional simulation model comprises a hollow cathode, a discharge cavity and a plume region, and the discharge cavity is communicated with the plume region; injecting neutral atoms into the discharge cavity, simulating collision among the neutral atoms by using a Monte Carlo method, and calculating density distribution and speed distribution of the neutral atoms in the discharge cavity and a plume region and electrostatic field distribution in the discharge cavity when the neutral atoms reach a convergence state; the hollow cathode emits original electrons into the discharge cavity, the original electrons and the neutral atoms collide under the action of the electrostatic field to obtain different particles, and the velocity distribution of the different particles is calculated; counting the number of different particles out of the right boundary of the plume region, and calculating to obtain the performance parameters of the Hall thruster according to the number and the speed distribution of the different particles; measuring the performance parameters of the Hall thruster in real time, comparing the measurement results of the performance parameters with the calculation results, counting the number of different particles bombarded to the surface of the hollow cathode contact electrode when the error between the measurement results and the calculation results is smaller than the preset error precision, and calculating the sputter etching rate and the sputter etching depth of the different particles to the contact electrode of the hollow cathode respectively; and comparing the sputtering corrosion rate and the sputtering etching depth of different particles to the contact level of the hollow cathode, and evaluating the service life of the Hall thruster. The method can improve the calculation precision of the performance parameters of the Hall thruster, quickly evaluate the performance and the service life of the Hall thruster, save the research and development cost and improve the research and development efficiency.
Having described embodiments of the present disclosure, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen in order to best explain the principles of the embodiments, the practical application, or improvements made to the technology in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.

Claims (3)

1. A service life evaluation method of a Hall thruster based on a hollow cathode is characterized by comprising the following steps:
establishing a three-dimensional simulation model of the Hall thruster, wherein the three-dimensional simulation model comprises a hollow cathode, a discharge cavity and a plume region, and the discharge cavity is communicated with the plume region;
injecting neutral atoms into the discharge cavity, simulating collision among the neutral atoms by using a Monte Carlo method, and calculating density distribution and speed distribution of the neutral atoms in the discharge cavity and the plume region and electrostatic field distribution in the discharge cavity when the neutral atoms reach a convergence state;
the hollow cathode emits original electrons into the discharge cavity, the original electrons and the neutral atoms collide under the action of the electrostatic field to obtain different particles, and the velocity distribution of the different particles is calculated;
counting the number of different particles out of the right boundary of the plume region, and calculating to obtain the performance parameters of the Hall thruster according to the number and the speed distribution of the different particles;
measuring the performance parameters of the Hall thruster in real time, comparing the measurement result with the calculation result of the performance parameters, and calculating the sputter etching rate and the sputter etching depth of different particles to the contact electrode of the hollow cathode when the error between the measurement result and the calculation result is smaller than the preset error precision;
and comparing the sputtering corrosion rate and the sputtering etching depth of different particles to the contact level of the hollow cathode, and evaluating the service life of the Hall thruster.
2. The life evaluation method according to claim 1, wherein the different particles include: secondary electrons, monovalent ions, divalent ions, monovalent charge exchange ions, and divalent charge exchange ions.
3. The life evaluation method of claim 1, wherein the performance parameters of the hall thruster comprise: thrust, specific impulse and efficiency.
CN202011063440.3A 2020-09-30 2020-09-30 Hall thruster service life evaluation method based on hollow cathode Active CN112347610B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202011063440.3A CN112347610B (en) 2020-09-30 2020-09-30 Hall thruster service life evaluation method based on hollow cathode

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202011063440.3A CN112347610B (en) 2020-09-30 2020-09-30 Hall thruster service life evaluation method based on hollow cathode

Publications (2)

Publication Number Publication Date
CN112347610A CN112347610A (en) 2021-02-09
CN112347610B true CN112347610B (en) 2022-09-23

Family

ID=74360389

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202011063440.3A Active CN112347610B (en) 2020-09-30 2020-09-30 Hall thruster service life evaluation method based on hollow cathode

Country Status (1)

Country Link
CN (1) CN112347610B (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114329919B (en) * 2021-12-09 2023-05-23 兰州空间技术物理研究所 Simulation analysis method for sputter etching of screen grid of ion thruster
CN114595571B (en) * 2022-03-07 2024-09-03 北京理工大学 Hollow cathode discharge instability prediction method
CN117420102B (en) * 2023-12-19 2024-04-09 哈尔滨工业大学 Optical on-line monitoring device and emitter life rapid assessment method

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111199099A (en) * 2019-12-26 2020-05-26 兰州空间技术物理研究所 Method for evaluating operation life of ion thruster based on grid corrosion

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101334352B (en) * 2008-07-30 2011-06-22 哈尔滨工业大学 Hall thruster life-span estimation method
US9089040B2 (en) * 2010-03-01 2015-07-21 Mitsubishi Electric Corporation Hall thruster, cosmonautic vehicle, and propulsion method
CN110851939A (en) * 2018-07-27 2020-02-28 核工业西南物理研究院 Simulation calculation method for service life evaluation of cylindrical anode layer Hall thruster
CN110058097B (en) * 2019-03-22 2021-04-13 北京控制工程研究所 Hall thruster accelerated life test method
CN111259514B (en) * 2019-12-26 2022-11-25 兰州空间技术物理研究所 Full-flow numerical simulation system of Hall thruster and full-flow numerical simulation method using same

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111199099A (en) * 2019-12-26 2020-05-26 兰州空间技术物理研究所 Method for evaluating operation life of ion thruster based on grid corrosion

Also Published As

Publication number Publication date
CN112347610A (en) 2021-02-09

Similar Documents

Publication Publication Date Title
CN112347610B (en) Hall thruster service life evaluation method based on hollow cathode
CN111199099B (en) Method for evaluating operation life of ion thruster based on grid corrosion
Kalentev et al. Electrostatic Ion Thrusters‐Towards Predictive Modeling
CN112329247B (en) Simulation method for discharge plasma and self-sputtering of Hall electric thruster
CN112329201B (en) Integrated ionic electric propulsion simulation model and method
Gamero-Castano et al. Estimation of Hall thruster erosion using HPHall
Peng et al. Plasma particle simulation of electrostatic ion thrusters
Appelhans et al. Measurement of external ion injection and trapping efficiency in the ion trap mass spectrometer and comparison with a predictive model
CN107679274B (en) Spacecraft charging and discharging comprehensive analysis method
CN105844095B (en) A kind of ion thruster System in Small Sample Situation reliability estimation method based on performance degradation
CN110851939A (en) Simulation calculation method for service life evaluation of cylindrical anode layer Hall thruster
Ahern Investigation of a space propulsion concept using inertial electrostatic confinement
Huismann Improving hall thruster plume simulation through refined characterization of near-field plasma properties
Taccogna et al. Particle-in-cell with Monte Carlo simulation of SPT-100 exhaust plumes
CN115495930A (en) Method for calculating performance of variable-aperture grid ion thruster
CN113221432B (en) Dynamic prediction method for service life of grid electrode of ion thruster based on artificial intelligence
CN114329919B (en) Simulation analysis method for sputter etching of screen grid of ion thruster
Tartz et al. Study of extraction grid erosion in a long-time ion thruster operational test
Ahern et al. Current Status of the Helicon Injected Inertial Plasma Electrostatic Rocket
Sullivan The physics of high-velocity ions in the Hall thruster near-field
Shagayda et al. Near-Wall Conductivity of Primary Electrons in the Discharge Chamber of an Ion Thruster
Tartz et al. Validated ion thruster grid lifetime simulation
Tartz et al. Extraction Grid Erosion in Long-time Ion Thruster Operation: Comparison with Simulation
Nishii et al. Three-Dimensional kinetic simulation of an ion thruster plume with carbon backsputtering in a vacuum chamber
Watanabe et al. Feasibility Study on Numerical Life Qualification of Ion Thruster's Ion Optics Using the JIEDI Tool

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant