On-orbit Health Monitoring Method for High-Power Hall Thrusters

Abstract

The present invention belongs to the field of aerospace plasma propulsion, and provides a method for on-orbit health monitoring of high-power Hall thrusters. The on-orbit health monitoring device acquires the imaging of the discharge channel of the high-power Hall thruster; ignites the high-power Hall thruster and operates within the normal operating conditions range; the robotic arm controls each camera to scan within the range of the angular interval, and calculates the radiation intensity at different positions in real time; the temperature is obtained by inverse calculation based on the radiation intensity; the real-time calculation result shows whether the temperature at any point on the circumference of the discharge channel outlet of the high-power Hall thruster is higher than the threshold value of the wall material of the discharge channel of the high-power Hall thruster. If not, the monitoring is restarted at the set interval time; if so, it is determined that the health state of the high-power Hall thruster is abnormal, an alarm signal is sent, and the high-power Hall thruster is shut down. The thermal radiation monitoring at the discharge channel outlets at different positions is realized, so as to achieve the on-orbit health monitoring of the high-power Hall thruster.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace plasma propulsion, and particularly relates to a method for monitoring the on-orbit health status of a high-power Hall thruster. Background Art

[0002] High-power Hall electric thrusters are considered to be the most promising propulsion devices for deep space exploration at present, with great development potential and are suitable for power devices in space nuclear electric propulsion systems. However, during the operation of high-power Hall thrusters, due to the high plasma density and electric field strength in the discharge channel, the velocity of ions ejected from the discharge channel is extremely high. When there is an angle between the movement direction of the ions and the direction of the discharge channel, the ions will bombard the wall surface and the outlet of the discharge channel, causing wall losses, making the circumferential non-uniformity at the outlet of the discharge channel, affecting the health status of the thruster, and ultimately reducing the service life of the thruster. Summary of the Invention

[0003] The present invention provides a method for monitoring the on-orbit health status of a high-power Hall thruster, which is used to realize the thermal radiation monitoring of the outlets of the discharge channels at different positions, so as to achieve the monitoring of the on-orbit health status of the high-power Hall thruster.

[0004] The present invention is realized through the following technical solutions:

[0005] A method for monitoring the on-orbit health status of a high-power Hall thruster, the on-orbit health status monitoring method includes the following steps:

[0006] Step 1: The on-orbit health status monitoring device acquires an image of the discharge channel of the high-power Hall thruster;

[0007] Step 2: Ignite the high-power Hall thruster and operate it within the normal operating range;

[0008] Step 3: The robotic arm controls each infrared band camera to scan within the range of the angular interval, and calculates the radiation intensity at different positions in real time;

[0009] Step 4: The temperature is inversely obtained based on the radiation intensity at different positions in Step 3;

[0010] Step 5: Based on the temperature in Step 4, when the high-power Hall thruster is operating, the real-time calculation result shows whether the temperature at any point on the circumference of the outlet of the discharge channel of the high-power Hall thruster is higher than the threshold of the wall material of the discharge channel of the high-power Hall thruster. If not, return to Step 3 for monitoring again at the set interval time; if so, it is determined that the health status of the high-power Hall thruster is abnormal, an alarm signal is sent, and the high-power Hall thruster is shut down.

[0011] Furthermore, the on-orbit health monitoring device in step 1 includes a robotic arm, an infrared-band camera, and a high-power Hall thruster;

[0012] The robotic arm is used to adjust the position of the infrared-band camera and connect the infrared-band camera to the satellite wall surface;

[0013] The infrared-band camera is used to obtain the imaging of the discharge channel of the high-power Hall thruster;

[0014] The high-power Hall thruster is used for deep space exploration propulsion.

[0015] Furthermore, the robotic arm is installed on the satellite wall surface, and there are multiple robotic arms. The high-power Hall thruster is embedded in the satellite wall surface. An infrared-band camera is installed at the end of each robotic arm, and the robotic arm is used to photograph the imaging of the discharge channel of the high-power Hall thruster.

[0016] Furthermore, step 1 is specifically as follows: Each robotic arm controls an infrared-band camera paired with it to extend out of the payload bay of the satellite, and the infrared-band camera images the discharge channel of the high-power Hall thruster at the same interval angle in a plane perpendicular to the plume axis.

[0017] Furthermore, the interval angle is 90°.

[0018] Furthermore, the infrared-band camera is a camera paired with an infrared-band filter.

[0019] Furthermore, step 3 is specifically as follows: Perform dynamic scanning in real time, synchronously master the state of the thruster, and can also adjust the operating conditions according to the real-time results.

[0020] Furthermore, step 4 is specifically as follows: The temperature is obtained by inversion using the colorimetric temperature measurement method T , the temperature T The calculation formula is as follows;

[0021]

[0022] Among them, and are wavelengths, is the emissivity of the object to be measured at wavelength , is the emissivity of the object to be measured at wavelength , and are the light intensities of the selected wavelengths.

[0023] Furthermore, the wavelengths selected by the infrared-band camera avoid the characteristic wavelengths of the working medium gas used by the high-power Hall thruster to be measured.

[0024] Furthermore, the method for monitoring the on-orbit health status of the high-power Hall thruster further includes that after the shooting is completed, the robotic arm needs to be operated to move the infrared-band camera away from the plume area to prevent the infrared-band camera from being damaged.

[0025] The beneficial effects of the present invention are as follows:

[0026] The present invention uses a camera array and an infrared-band filter to obtain an infrared-band camera, realizes the thermal radiation monitoring at the outlet of the discharge channel of the high-power Hall thruster at different positions, judges the temperature distribution of the wall material of the discharge channel of the high-power Hall thruster through the radiation intensity, and when the temperature exceeds the set threshold of the wall material of the discharge channel of the high-power Hall thruster, an alarm signal is sent and the high-power Hall thruster is shut down. Description of the Drawings

[0027] Figure 1 is the flowchart of the method of the present invention.

[0028] Figure 2 is the structural schematic diagram of the present invention.

[0029] Description of the reference numerals: 101 - robotic arm, 102 - infrared-band camera, 103 - high-power Hall thruster, 104 - satellite wall. Detailed Embodiments

[0030] In the following description, for the purpose of illustration rather than limitation, specific details such as specific system structures and technologies are put forward to thoroughly understand the embodiments of the present application. However, those skilled in the art should understand that the present application can also be implemented in other embodiments without these specific details. In other cases, the detailed descriptions of well-known systems, devices, circuits, and methods are omitted to avoid unnecessary details from interfering with the description of the present application.

[0031] It should be understood that when used in this specification and the appended claims, the term "comprising" indicates the presence of the described features, wholes, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components, and / or their combinations.

[0032] It should also be understood that the terms used in the specification of the present application are only for the purpose of describing specific embodiments and are not intended to limit the present application. As used in the specification of the present application and the appended claims, unless the context clearly indicates otherwise, the singular forms "a", "an", and "the" are intended to include the plural forms.

[0033] The following is combined with the attached drawings of the specification of the present application Figure 1-2, the technical solutions in the embodiments of the present application are clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present application.

[0034] In the following description, many specific details are set forth in order to provide a thorough understanding of the present application. However, the present application may be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the connotation of the present application. Therefore, the present application is not limited by the specific embodiments disclosed below.

[0035] Embodiment 1

[0036] This embodiment provides a device for monitoring the on-orbit health status of a high-power Hall thruster, as Figure 2 shown. The on-orbit health status monitoring device includes a robotic arm 101, an infrared-band camera 102, and a high-power Hall thruster 103;

[0037] The robotic arm 101 is used to adjust the position of the infrared-band camera 102 and connect the infrared-band camera 102 to the satellite wall 104;

[0038] The infrared-band camera 102 is used to obtain an image of the discharge channel of the high-power Hall thruster 103;

[0039] The high-power Hall thruster 103 is used for deep space exploration propulsion.

[0040] Furthermore, the robotic arm 101 is installed on the satellite wall 104, and there are multiple robotic arms 101. The high-power Hall thruster 103 is embedded in the satellite wall 104. An infrared-band camera 102 is installed at the end of each robotic arm 101. The robotic arm 101 is used to capture an image of the discharge channel of the high-power Hall thruster 103.

[0041] Furthermore, step 1 is specifically as follows: each robotic arm 101 controls a paired infrared-band camera 102 to extend out of the payload bay of the satellite. The infrared-band camera 102 images the discharge channel of the high-power Hall thruster 103 at the same interval angle in a plane perpendicular to the plume axis.

[0042] Furthermore, the interval angle is 90°, that is, four imaging devices can cover a range of 360 degrees, that is, cover the entire planar space.

[0043] Furthermore, the infrared-band camera 102 is a camera equipped with an infrared-band filter.

[0044] Specifically, refer toFigure 2 It is described that for this device, a high-power Hall thruster 103 is installed on the satellite wall 104 of the artificial satellite. Four infrared-band cameras 102 are connected to the satellite wall 104 of the artificial satellite through four robotic arms 101. The four infrared-band cameras 102 are connected to infrared filter films of four wavelengths and can be moved through the robotic arms 101 to capture the plasma fluctuation states in different regions when the discharge channel of the high-power Hall thruster 103 is working, so as to realize the thermal radiation monitoring at the outlet of the discharge channel of the high-power Hall thruster 103 at different positions, judge the temperature distribution of the wall material of the discharge channel of the high-power Hall thruster 103 through the radiation intensity, and can avoid the plume of the high-power Hall thruster 103 when not monitoring, so as to improve the service life of the monitoring system.

[0045] Embodiment 2

[0046] This embodiment provides a method for monitoring the on-orbit health state of a high-power Hall thruster. Refer to Figure 1 It is described the specific steps of the on-orbit health state monitoring method in this embodiment:

[0047] Step 1: The on-orbit health state monitoring device acquires an image of the discharge channel of the high-power Hall thruster 103.

[0048] Step 2: Ignite the high-power Hall thruster 103 and operate it within the normal operating conditions range.

[0049] Step 3: The robotic arm 101 controls each infrared-band camera 102 to scan within the range of the angular interval and calculates the radiation intensity at different positions in real time.

[0050] Step 4: The temperature is inversely obtained based on the radiation intensity at different positions in Step 3.

[0051] Step 5: Based on the temperature in Step 4, when the high-power Hall thruster 103 is operating, the real-time calculation result shows whether the temperature at any point on the circumference of the outlet of the discharge channel of the high-power Hall thruster 103 is higher than the threshold of the wall material of the discharge channel of the high-power Hall thruster 103. If not, return to Step 3 for monitoring again at the set interval time. If so, it is judged that the health state of the high-power Hall thruster 103 is abnormal, an alarm signal is sent and the high-power Hall thruster 103 is shut down.

[0052] Furthermore, the on-orbit health state monitoring device in Step 1 includes a robotic arm 101, an infrared-band camera 102 and a high-power Hall thruster 103;

[0053] The robotic arm 101 is used to adjust the position of the infrared-band camera 102 and connect the infrared-band camera 102 to the satellite wall 104.

[0054] The infrared band camera 102 is used to obtain the imaging of the discharge channel of the high-power Hall thruster 103;

[0055] The high-power Hall thruster 103 is used for deep space exploration propulsion.

[0056] Furthermore, the robotic arm 101 is installed on the satellite wall 104, and there are multiple robotic arms 101. The high-power Hall thruster 103 is embedded in the satellite wall 104. An infrared band camera 102 is installed at the end of each robotic arm 101. The robotic arm 101 is used to photograph the imaging of the discharge channel of the high-power Hall thruster 103.

[0057] Furthermore, the specific content of step 1 is that each robotic arm 101 controls an infrared band camera 102 paired with it to extend out of the payload compartment of the satellite. The infrared band camera 102 images the discharge channel of the high-power Hall thruster 103 at the same interval angle in the plane perpendicular to the plume axis.

[0058] Furthermore, the interval angle is 90°, that is, four imaging devices can cover a range of 360 degrees, that is, cover the entire plane space.

[0059] Furthermore, the infrared band camera 102 is a camera paired with an infrared band filter.

[0060] Furthermore, the specific content of step 3 for calculating the radiation intensity at different positions in real time is to perform dynamic scanning and calculation in real time, which can synchronously master the state of the high-power Hall thruster 103, assist ground personnel or on-board computers to adjust the operating conditions according to the real-time results, and improve the system reliability.

[0061] Furthermore, the specific content of step 4 is to perform inversion using the colorimetric temperature measurement method to obtain the temperature T , the temperature T The calculation formula is as follows;

[0062]

[0063] Among them, and are wavelengths, is the emissivity of the object to be measured at wavelength , is the emissivity of the object to be measured at wavelength , and are the light intensities of the selected wavelengths.

[0064] Furthermore, the wavelengths selected by the infrared band camera 102 should avoid the characteristic wavelengths of the working fluid gas used by the high-power Hall thruster 103 to be measured.

[0065] Further, the method for monitoring the on-orbit health status of the high-power Hall thruster further includes that after the shooting is completed, it is necessary to operate the robotic arm 101 to move the infrared-band camera 102 away from the plume area to prevent the infrared-band camera 102 from being damaged.

Claims

1. A method for monitoring the health status of a high-power Hall thruster on orbit, characterized in that: The on-orbit health status monitoring method comprises the following steps: Step 1: An on-orbit health status monitoring device obtains an image of a discharge channel of a high-power Hall thruster (103); The on-orbit health status monitoring device of step 1 comprises a mechanical arm (101), an infrared band camera (102) and a high-power Hall thruster (103); The mechanical arm (101) is used to adjust the position of the infrared band camera (102) and connect the infrared band camera (102) to the satellite wall (104); The infrared band camera (102) is used to obtain an image of the discharge channel of the high-power Hall thruster (103); The high-power Hall thruster (103) is used for deep space exploration propulsion; The mechanical arm (101) is mounted on a satellite wall (104), and there are a plurality of mechanical arms (101); the high-power Hall thruster (103) is embedded in the satellite wall (104); an infrared band camera (102) is mounted on the tail end of each mechanical arm (101); and the mechanical arm (101) is used to capture images of a discharge channel of the high-power Hall thruster (103); Specifically, step 1 comprises: each mechanical arm (101) controls an infrared band camera (102) matched therewith to extend out of the payload cabin of the satellite, and the infrared band camera (102) images the discharge channel of the high-power Hall thruster (103) at the same interval angle in a plane perpendicular to the axial direction of the plume; Step 2: ignite the high-power Hall thruster (103) and operate it within the normal operating range; Step 3: The robotic arm (101) controls each infrared band camera (102) to scan within the range of the interval angle, and calculates the radiation intensity at different positions in real time; Step 4: Invert the radiation intensity at different locations based on step 3 to obtain the temperature; Step 5: Based on the temperature in step 4, when the high-power Hall thruster (103) is in operation, the real-time calculation result shows whether the temperature at any point on the circumference of the discharge channel outlet of the high-power Hall thruster (103) is higher than the threshold value of the discharge channel wall material of the high-power Hall thruster (103). If not, the process returns to step 3 according to the set interval time; if yes, the health status of the high-power Hall thruster (103) is judged to be abnormal, an alarm signal is issued, and the high-power Hall thruster (103) is shut down.

2. The on-orbit health status monitoring method of a high-power Hall thruster according to claim 1 is characterized in that: The interval angle is 90°.

3. The on-orbit health status monitoring method of a high-power Hall thruster according to claim 1 is characterized in that: The infrared band camera (102) is a camera equipped with an infrared band filter.

4. The on-orbit health status monitoring method of a high-power Hall thruster according to claim 1 is characterized in that: Specifically, step 3 is to perform dynamic scanning in real time, synchronously grasp the state of the high-power Hall thruster (103), and regulate the operating conditions according to the real-time results.

5. The on-orbit health status monitoring method of a high-power Hall thruster according to claim 4 is characterized in that: The step 4 specifically comprises: using the colorimetric temperature measurement method to invert the temperature T ,temperature T The calculation formula is as follows; in, and is the wavelength, is the wavelength of the object to be measured The emissivity at is the wavelength of the object to be measured The emissivity at and is the light intensity of the selected wavelength.

6. The on-orbit health status monitoring method of a high-power Hall thruster according to claim 5 is characterized in that: The wavelength selected by the infrared band camera (102) avoids the characteristic wavelength of the working gas used by the high-power Hall thruster (103) to be tested.

7. The on-orbit health status monitoring method of a high-power Hall thruster according to claim 1 is characterized in that: The high-power Hall thruster on-orbit health status monitoring method also includes the step of operating the mechanical arm (101) after the shooting is completed so that the infrared band camera (102) is away from the plume area to prevent the infrared band camera (102) from being damaged.

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