CN118067398B - On-orbit optical monitoring method for thrust distribution of multichannel Hall thruster - Google Patents
On-orbit optical monitoring method for thrust distribution of multichannel Hall thruster Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- 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
- F03H1/0062—Electrostatic ion thrusters grid-less with an applied magnetic field
- F03H1/0075—Electrostatic ion thrusters grid-less with an applied magnetic field with an annular channel; Hall-effect thrusters with closed electron drift
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0028—Force sensors associated with force applying means
- G01L5/0038—Force sensors associated with force applying means applying a pushing force
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- G01T—MEASUREMENT OF NUCLEAR OR X-RADIATION
- G01T1/00—Measuring X-radiation, gamma radiation, corpuscular radiation, or cosmic radiation
- G01T1/29—Measurement performed on radiation beams, e.g. position or section of the beam; Measurement of spatial distribution of radiation
- G01T1/2914—Measurement of spatial distribution of radiation
- G01T1/2921—Static instruments for imaging the distribution of radioactivity in one or two dimensions; Radio-isotope cameras
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Abstract
The invention belongs to the field of aerospace plasma propulsion, and provides an on-orbit optical monitoring method for thrust distribution of a multichannel Hall thruster. Step 1: when the multi-channel Hall thruster normally operates under a set working condition, the mechanical arm controls the imaging monitoring device to acquire the imaging of the opposite multi-channel Hall thruster; step 2: calculating ion density distribution at the outlets of different discharge channels of the plasma by using a spectral line ratio method based on imaging; step 3: calculating the thrust generated by different channels by utilizing ion density distribution, synthesizing total thrust, and comparing with the set thrust under the set working condition; step 4: and judging whether the working condition is regulated according to the comparison result until the calculated thrust is consistent with the set thrust. The plasma ion-discharging device is used for solving the problems that the plasma density is different among different discharge channels and finally the thrust generated by the propeller after the ions are sprayed out is unbalanced due to the different ionization states among the different discharge channels.
Description
Technical Field
The invention belongs to the technical field of aerospace plasma propulsion, and particularly relates to an on-orbit optical monitoring method for thrust distribution of a multichannel Hall thruster.
Background
With the development and progress of technology, the demands of human beings for deep space and planetary exploration are increasing, such as Mars, wooden stars, earth stars and exploration tasks far from the solar system. These tasks require propulsion systems to achieve adequate long-haul flights and precise orbit control. The Hall propeller is a preferred propelling device for space detection by virtue of the characteristics of high specific impulse and long service life. With advances in electronics and materials science, electric propulsion technology has improved. The development of high-power hall thrusters is made possible by more efficient electric propulsion systems and more powerful electric power supply means. The multi-channel Hall propeller is one development direction of a high-power Hall, and is formed by concentrically nesting multiple layers of discharge channels. The thrust can reach the level of cattle, the power can reach hundreds of kilowatts, and the requirement of deep space exploration on a propulsion system is met.
However, the multi-stage discharge channels can cause the regional ionization of the working medium gas, and as the discharge channels are radially arranged, the electron turning radiuses under different radiuses are different, namely the ionization states among different discharge channels are different, so that the plasma densities among the discharge channels are different, and finally, the thrust imbalance generated by the propeller after the ions are sprayed out is caused.
Disclosure of Invention
The invention provides an on-orbit optical monitoring method for thrust distribution of a multi-channel Hall thruster, which is used for solving the problem that plasma density among discharge channels is different due to different ionization states among different discharge channels, and finally, thrust imbalance generated by the thruster after ion ejection is caused.
The invention is realized by the following technical scheme:
An on-orbit optical monitoring method for thrust distribution of a multichannel Hall thruster comprises the following steps:
step 1: when the multi-channel Hall thruster normally operates under a set working condition, the mechanical arm controls the imaging monitoring device to acquire the imaging of the opposite multi-channel Hall thruster, and the imaging monitoring device comprises a camera and a wavelength selector;
Step 2: calculating ion density distribution at the outlets of different discharge channels of the plasma by using a spectral line ratio method based on the imaging of the step 1;
step 3: calculating the thrust generated by different channels by utilizing the ion density distribution in the step 2, synthesizing the total thrust, and comparing the total thrust with the set thrust under the set working condition;
Step 4: and (3) judging whether to adjust the working condition according to the comparison result in the step (3) until the calculated thrust is consistent with the set thrust.
Further, the multi-channel hall thruster in the step 1 is arranged at the tail end of the satellite, one end of the mechanical arm is connected with the satellite, the other end of the mechanical arm is connected with the imaging monitoring device, the camera of the imaging monitoring device and the multi-channel hall thruster are positioned on the same plane, and the axis of the camera coincides with the axis of the multi-channel hall thruster.
Further, the wavelength emitted by the control wavelength selector in the control imaging monitoring device is 460nm, 630 nm,830nm and 880nm, respectively.
Further, the imaging monitoring device in the step 1 is used for capturing plasma fluctuation states of different areas when the multi-channel Hall thruster works;
The multi-channel Hall thruster is used for space detection;
the mechanical arm is used for adjusting the imaging monitoring device to obtain pictures corresponding to different wavelengths of the channel outlets of the multi-channel Hall propeller.
Furthermore, in the step 2, a collision radiation model is used to calculate theoretical spectra of working medium gases under different ion densities, and a relation between a spectral line ratio and the ion densities is calculated through least square fitting.
Further, the theoretical spectrum of working medium gas under different ion densities is calculated by using the collision radiation model,
Wherein I 828、I881、I541、I529 represents theoretical spectra at different wavelengths, n i R represents radial ion density, T e R represents radial electron temperature, a 1 represents a first term coefficient of I 828 spectral intensity versus ion density and electron temperature function, B 1 represents a second term coefficient of I 828 spectral intensity versus ion density versus electron temperature function, C 1 represents a third term coefficient of I 828 spectral intensity versus ion density versus electron temperature function, D 1 represents a fourth term coefficient of I 828 spectral intensity versus ion density versus electron temperature function;
A 2 represents a first term of the I 881 spectral intensity versus ion density and electron temperature function, B 2 represents a second term of the I 881 spectral intensity versus ion density and electron temperature function, C 2 represents a third term of the I 881 spectral intensity versus ion density and electron temperature function, D 2 represents a fourth term of the I 881 spectral intensity versus ion density and electron temperature function, E 2 represents a fifth term of the I 881 spectral intensity versus ion density and electron temperature function, F 2 represents a sixth term of the I 881 spectral intensity versus ion density and electron temperature function, G 2 represents a seventh term of the I 881 spectral intensity versus ion density and electron temperature function;
A 3 represents a first term of the I 541 spectral intensity versus ion density and electron temperature function, B 3 represents a second term of the I 541 spectral intensity versus ion density and electron temperature function, C 3 represents a third term of the I 541 spectral intensity versus ion density and electron temperature function, D 3 represents a fourth term of the I 541 spectral intensity versus ion density and electron temperature function, E 3 represents a fifth term of the I 541 spectral intensity versus ion density and electron temperature function, F 3 represents a sixth term of the I 541 spectral intensity versus ion density and electron temperature function, G 3 represents a seventh term of the I 541 spectral intensity versus ion density and electron temperature function;
A 4 represents a first term of the I 529 spectral intensity versus ion density and electron temperature function, B 4 represents a second term of the I 529 spectral intensity versus ion density and electron temperature function, C 4 represents a third term of the I 529 spectral intensity versus ion density and electron temperature function, D 4 represents a fourth term of the I 529 spectral intensity versus ion density and electron temperature function, E 4 represents a fifth term of the I 529 spectral intensity versus ion density and electron temperature function, F 4 represents a sixth term of the I 529 spectral intensity versus ion density and electron temperature function, and G 4 represents a seventh term of the I 529 spectral intensity versus ion density and electron temperature function.
Further, the relation between the spectral line ratio and the ion density calculated by least square fitting is specifically that,
Wherein R represents the spectral line ratio, I 541、I529 represents the theoretical spectrum at different wavelengths, G 3 represents the seventh coefficient of the I 541 spectral intensity as a function of ion density and electron temperature, G 4 represents the seventh coefficient of the I 529 spectral intensity as a function of ion density and electron temperature, n i _r represents the radial ion density, and n g represents the atomic density, respectively.
Further, the step 3 specifically includes the following calculation formula:
F＝YTF
where γ T represents the thrust coefficient, F represents the total thrust, F i represents the thrust calculation result of each channel, θ b represents the plume divergence angle, and α represents the duty ratio of the doubly charged ions.
Further, in the step 4, if the set thrust is consistent with the calculated thrust, the thrust balance is determined, and the mechanical arm is retracted to the satellite load cabin; if the set thrust is inconsistent with the calculated thrust, judging that the thrust unbalance phenomenon exists, feeding back to the control center, adjusting working conditions, and repeating the steps 2-3 until the calculated thrust is consistent with the set thrust.
Further, the multichannel Hall thruster comprises a cathode, a permanent magnet, a discharge channel and an anode;
The cathode is used for providing primary electrons required by ionization;
The permanent magnet is used for providing an annular magnetic field to restrain electrons from moving in the discharge channel;
the discharge channel is used for generating plasma by electrons colliding with neutral gas;
The anode is used for providing an axial electric field and accelerating ions in the plasma to generate thrust.
The beneficial effects of the invention are as follows:
According to the invention, the transient imaging characteristic of the high-speed camera is utilized to capture the plasma fluctuation state of different areas when the multi-channel Hall propeller works, the multi-wavelength imaging of different channel plumes is realized by combining the high-performance wavelength selector, the ion density of different channel outlets is calculated by utilizing the spectral line ratio relation of different wavelengths, the spatial distribution information of the ion density is obtained, the corresponding thrust is calculated, the thrust is compared with the thrust under the working condition setting, and the working condition is regulated until the set thrust is consistent with the imaging measurement thrust by utilizing the comparison result feedback control circuit.
Drawings
Fig. 1 is a schematic view of a multi-channel hall thruster of the present invention.
FIG. 2 is a schematic diagram of the thrust distribution on-orbit optical monitoring device according to the present invention.
Fig. 3 is a flow chart of the method of the present invention.
Detailed Description
In the following description, for purposes of explanation and not limitation, specific details are set forth such as the particular system architecture, techniques, etc., in order to provide a thorough understanding of the embodiments of the present application. It will be apparent, however, to one skilled in the art that the present application may be practiced in other embodiments that depart from these specific details. In other instances, detailed descriptions of well-known systems, devices, circuits, and methods are omitted so as not to obscure the description of the present application with unnecessary detail.
It should be understood that the terms "comprises" and/or "comprising," when used in this specification and the appended claims, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.
It is also to be understood that the terminology used in the description of the application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used in this specification and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
The following description of the embodiments of the present application will be made more fully with reference to the accompanying drawings, in which 1-3 are shown, and it is apparent that the embodiments described are merely some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application, but the present application may be practiced in other ways other than those described herein, and persons skilled in the art will readily appreciate that the present application is not limited to the specific embodiments disclosed below.
Example 1
The present embodiment provides a thrust distribution on-orbit optical monitoring device for a multi-channel hall thruster, where the thrust distribution on-orbit optical monitoring device includes a multi-channel hall thruster 203 disposed at a tail end of a satellite 202, one end of a mechanical arm 205 is connected with the satellite 202, the other end of the mechanical arm 205 is in the same plane with an imaging monitoring device 204, a camera of the imaging monitoring device 204 is in the same plane with the multi-channel hall thruster 203, and an axis of the camera coincides with an axis of the multi-channel hall thruster 203.
Further, the wavelength emitted by the control wavelength selector in the control imaging monitoring device 204 is 460nm, 630 nm,830nm and 880nm, respectively.
Further, the imaging monitoring device 204 in the step 1 is configured to capture plasma fluctuation states of different areas when the multi-channel hall thruster works;
the multi-channel Hall thruster 203 is used for space detection;
The mechanical arm 205 is configured to adjust the imaging monitoring device 204 to obtain pictures corresponding to different wavelengths at the channel outlet of the multi-channel hall thruster 203.
Further, the multi-channel hall thruster 203 includes a cathode 101, a permanent magnet 102, a discharge channel 103, and an anode 104;
The cathode 101 is used for providing primary electrons required for ionization;
The permanent magnet 102 is used for providing a ring magnetic field to restrain electrons from moving in the discharge channel;
the discharge channel 103 is used for generating plasma by electrons colliding with neutral gas;
the anode 104 is used to provide an axial electric field to accelerate ions in the plasma to generate thrust.
Example two
The embodiment provides an on-orbit optical monitoring method for thrust distribution of a multichannel Hall thruster, which specifically comprises the following steps:
step 1: when the multi-channel Hall thruster normally operates under a set working condition, the mechanical arm 205 controls the imaging monitoring device 204 to acquire the imaging of the opposite multi-channel Hall thruster 203, and the imaging monitoring device 204 comprises a camera and a wavelength selector;
Step 2: calculating ion density distribution at the outlet of different discharge channels 103 of the plasma by using a spectral line ratio method based on the imaging of the step 1;
step 3: calculating the thrust generated by different channels by utilizing the ion density distribution in the step 2, synthesizing the total thrust, and comparing the total thrust with the set thrust under the set working condition;
Step 4: and (3) judging whether to adjust the working condition according to the comparison result in the step (3) until the calculated thrust is consistent with the set thrust.
Further, the multi-channel hall thruster 203 in the step 1 is disposed at the tail end of the satellite 202, and the solar sailboard 201 is connected to two sides of the satellite 202; one end of the mechanical arm 205 is connected with the satellite 202, the other end of the mechanical arm 205 is connected with the imaging monitoring device 204, a camera of the imaging monitoring device 204 and the multi-channel Hall thruster 203 are located on the same plane, and the axis of the camera coincides with the axis of the multi-channel Hall thruster 203.
Further, the wavelength emitted by the control wavelength selector in the control imaging monitoring device 204 is 460nm, 630 nm,830nm and 880nm, respectively.
Further, the imaging monitoring device 204 in the step 1 is configured to capture plasma fluctuation states of different areas when the multi-channel hall thruster works;
the multi-channel Hall thruster 203 is used for space detection;
the mechanical arm 205 is configured to adjust the imaging monitoring device 204 to obtain pictures corresponding to different wavelengths at the channel outlet of the multi-channel hall thruster 203.
Furthermore, in the step 2, a collision radiation model is used to calculate theoretical spectra of working medium gases under different ion densities, and a relation between a spectral line ratio and the ion densities is calculated through least square fitting.
Further, the theoretical spectrum of working medium gas under different ion densities is calculated by using the collision radiation model,
Wherein I 828、I881、I541、I529 represents theoretical spectra at different wavelengths, n i R represents radial ion density, T e R represents radial electron temperature, a 1 represents a first term coefficient of I 828 spectral intensity versus ion density and electron temperature function, B 1 represents a second term coefficient of I 828 spectral intensity versus ion density versus electron temperature function, C 1 represents a third term coefficient of I 828 spectral intensity versus ion density versus electron temperature function, D 1 represents a fourth term coefficient of I 828 spectral intensity versus ion density versus electron temperature function;
A 2 represents a first term of the I 881 spectral intensity versus ion density and electron temperature function, B 2 represents a second term of the I 881 spectral intensity versus ion density and electron temperature function, C 2 represents a third term of the I 881 spectral intensity versus ion density and electron temperature function, D 2 represents a fourth term of the I 881 spectral intensity versus ion density and electron temperature function, E 2 represents a fifth term of the I 881 spectral intensity versus ion density and electron temperature function, F 2 represents a sixth term of the I 881 spectral intensity versus ion density and electron temperature function, G 2 represents a seventh term of the I 881 spectral intensity versus ion density and electron temperature function;
A 3 represents a first term of the I 541 spectral intensity versus ion density and electron temperature function, B 3 represents a second term of the I 541 spectral intensity versus ion density and electron temperature function, C 3 represents a third term of the I 541 spectral intensity versus ion density and electron temperature function, D 3 represents a fourth term of the I 541 spectral intensity versus ion density and electron temperature function, E 3 represents a fifth term of the I 541 spectral intensity versus ion density and electron temperature function, F 3 represents a sixth term of the I 541 spectral intensity versus ion density and electron temperature function, G 3 represents a seventh term of the I 541 spectral intensity versus ion density and electron temperature function;
A 4 represents a first term of the I 529 spectral intensity versus ion density and electron temperature function, B 4 represents a second term of the I 529 spectral intensity versus ion density and electron temperature function, C 4 represents a third term of the I 529 spectral intensity versus ion density and electron temperature function, D 4 represents a fourth term of the I 529 spectral intensity versus ion density and electron temperature function, E 4 represents a fifth term of the I 529 spectral intensity versus ion density and electron temperature function, F 4 represents a sixth term of the I 529 spectral intensity versus ion density and electron temperature function, and G 4 represents a seventh term of the I 529 spectral intensity versus ion density and electron temperature function.
Further, the relation between the spectral line ratio and the ion density calculated by least square fitting is specifically that,
Wherein R represents the spectral line ratio, I 541、I529 represents the theoretical spectrum at different wavelengths, G 3 represents the seventh coefficient of the I 541 spectral intensity as a function of ion density and electron temperature, G 4 represents the seventh coefficient of the I 529 spectral intensity as a function of ion density and electron temperature, ni_r represents the radial ion density, and n g represents the atomic density, respectively.
Further, the step 3 specifically includes the following calculation formula:
F＝Y-F
Where γ T represents the thrust coefficient, F represents the total thrust, F i represents the thrust calculation result of each channel, θ b represents the plume divergence angle, and α represents the duty ratio of the doubly charged ions. In practical calculations, gamma T is generally assumed to be 0.9.
Further, in the step 4, if the set thrust is consistent with the calculated thrust, the thrust balance is determined, and the mechanical arm is retracted to the satellite load cabin; if the set thrust is inconsistent with the calculated thrust, judging that the thrust unbalance phenomenon exists, feeding back to the control center, adjusting working conditions, and repeating the steps 2-3 until the calculated thrust is consistent with the set thrust.
Further, the multi-channel hall thruster 203 includes a cathode 101, a permanent magnet 102, a discharge channel 103, and an anode 104;
The cathode 101 is used for providing primary electrons required for ionization;
The permanent magnet 102 is used for providing a ring magnetic field to restrain electrons from moving in the discharge channel;
the discharge channel 103 is used for generating plasma by electrons colliding with neutral gas;
the anode 104 is used to provide an axial electric field to accelerate ions in the plasma to generate thrust.
Claims (8)
1. The on-orbit optical monitoring method for the thrust distribution of the multichannel Hall thruster is characterized by specifically comprising the following steps of:
Step 1: when the multi-channel Hall thruster normally operates under a set working condition, the mechanical arm (205) controls the imaging monitoring device (204) to acquire the imaging of the opposite multi-channel Hall thruster (203);
Step 2: calculating ion density distribution at the outlets of different discharge channels (103) of the plasma by using a spectral line ratio method based on the imaging of the step 1;
step 3: calculating the thrust generated by different channels by utilizing the ion density distribution in the step 2, synthesizing the total thrust, and comparing the total thrust with the set thrust under the set working condition;
Step 4: judging whether to adjust the working condition according to the comparison result in the step 3 until the calculated thrust is consistent with the set thrust;
Step 2, calculating theoretical spectra of working medium gas under different ion densities by using a collision radiation model, and calculating the relation between the spectral line ratio and the ion density by least square fitting;
the theoretical spectrum of working medium gas under different ion densities is calculated by using the collision radiation model,
Wherein I 828、I881、I541、I529 represents theoretical spectra at different wavelengths, n i R represents radial ion density, T e R represents radial electron temperature, a 1 represents a first term coefficient of I 828 spectral intensity versus ion density and electron temperature function, B 1 represents a second term coefficient of I 828 spectral intensity versus ion density versus electron temperature function, C 1 represents a third term coefficient of I 828 spectral intensity versus ion density versus electron temperature function, D 1 represents a fourth term coefficient of I 828 spectral intensity versus ion density versus electron temperature function;
A 2 represents a first term of the I 881 spectral intensity versus ion density and electron temperature function, B 2 represents a second term of the I 881 spectral intensity versus ion density and electron temperature function, C 2 represents a third term of the I 881 spectral intensity versus ion density and electron temperature function, D 2 represents a fourth term of the I 881 spectral intensity versus ion density and electron temperature function, E 2 represents a fifth term of the I 881 spectral intensity versus ion density and electron temperature function, F 2 represents a sixth term of the I 881 spectral intensity versus ion density and electron temperature function, G 2 represents a seventh term of the I 881 spectral intensity versus ion density and electron temperature function;
A 3 represents a first term of the I 541 spectral intensity versus ion density and electron temperature function, B 3 represents a second term of the I 541 spectral intensity versus ion density and electron temperature function, C 3 represents a third term of the I 541 spectral intensity versus ion density and electron temperature function, D 3 represents a fourth term of the I 541 spectral intensity versus ion density and electron temperature function, E 3 represents a fifth term of the I 541 spectral intensity versus ion density and electron temperature function, F 3 represents a sixth term of the I 541 spectral intensity versus ion density and electron temperature function, G 3 represents a seventh term of the I 541 spectral intensity versus ion density and electron temperature function;
A 4 represents a first term of the I 529 spectral intensity versus ion density and electron temperature function, B 4 represents a second term of the I 529 spectral intensity versus ion density and electron temperature function, C 4 represents a third term of the I 529 spectral intensity versus ion density and electron temperature function, D 4 represents a fourth term of the I 529 spectral intensity versus ion density and electron temperature function, E 4 represents a fifth term of the I 529 spectral intensity versus ion density and electron temperature function, F 4 represents a sixth term of the I 529 spectral intensity versus ion density and electron temperature function, and G 4 represents a seventh term of the I 529 spectral intensity versus ion density and electron temperature function.
2. The on-orbit optical monitoring method for thrust distribution according to claim 1, wherein the multi-channel hall thruster (203) in the step 1 is disposed at the tail end of the satellite (202), one end of the mechanical arm (205) is connected to the satellite (202), the other end of the mechanical arm (205) is connected to the imaging monitoring device (204), the camera of the imaging monitoring device (204) is in the same plane as the multi-channel hall thruster (203), and the axis of the camera coincides with the axis of the multi-channel hall thruster (203).
3. The thrust distribution on-orbit optical monitoring method of claim 1, wherein the control wavelength selectors within the control imaging monitoring device (204) emit wavelengths of 460nm,820nm,830nm and 880nm, respectively.
4. The on-orbit optical monitoring method for thrust distribution according to claim 2, wherein the imaging monitoring device (204) of step 1 is used for capturing plasma fluctuation states of different areas when the multi-channel hall thruster works;
the multi-channel Hall thruster (203) is used for space detection;
the mechanical arm (205) is used for adjusting the imaging monitoring device (204) to acquire pictures corresponding to different wavelengths at the channel outlet of the multi-channel Hall thruster (203).
5. The method for on-orbit optical monitoring of thrust force distribution according to claim 1, wherein the relationship between the spectral line ratio and the ion density calculated by least square fitting is as follows,
Wherein R represents the spectral line ratio, I 541、I529 represents the theoretical spectrum at different wavelengths, G 3 represents the seventh coefficient of the I 541 spectral intensity as a function of ion density and electron temperature, G 4 represents the seventh coefficient of the I 529 spectral intensity as a function of ion density and electron temperature, n i _r represents the radial ion density, and n g represents the atomic density, respectively.
6. The method for on-orbit optical monitoring of thrust distribution according to claim 1, wherein the calculation formula in step 3 is as follows:
F＝∑γTFi
where γ T represents the thrust coefficient, F represents the total thrust, F i represents the thrust calculation result of each channel, θ b represents the plume divergence angle, and α represents the duty ratio of the doubly charged ions.
7. The method for on-orbit optical monitoring of thrust distribution according to claim 2, wherein step 4 is specifically that if the set thrust is consistent with the calculated thrust, the thrust balance is determined, and the mechanical arm is retracted to the satellite load compartment; if the set thrust is inconsistent with the calculated thrust, judging that the thrust unbalance phenomenon exists, feeding back to the control center, adjusting working conditions, and repeating the steps 2-3 until the calculated thrust is consistent with the set thrust.
8. The thrust distribution on-orbit optical monitoring method according to claim 2, wherein the multichannel hall thruster (203) comprises a cathode (101), a permanent magnet (102), a discharge channel (103) and an anode (104);
the cathode (101) is used for providing primary electrons required for ionization;
The permanent magnet (102) is used for providing a ring magnetic field to restrain electrons from moving in the discharge channel;
the discharge channel (103) is used for generating plasma by electrons colliding with neutral gas;
the anode (104) is used for providing an axial electric field and accelerating ions in the plasma to generate thrust.
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