Spectrometer on-orbit optical axis calibration method and device and storage medium

Abstract

The invention provides a spectrometer on-orbit optical axis calibration method and device and a storage medium, and relates to the technical field of celestial body detector calibration. The method comprises the following steps: spirally scanning a celestial body to be measured; in the scanning process, continuously collecting imaging positions of the centroid of the to-be-detected celestial body in an imaging target surface of the imaging device, and collecting thermal radiation energy of a pointing position at a first angle based on a preset collection frequency through a spectrometer; inverting the continuously acquired imaging positions in the first target surface, and mapping the acquired thermal radiation energy to the corresponding positions in the first target surface according to the acquisition time to generate first thermal radiation data; and taking the position of a point with the highest heat radiation energy in the first heat radiation data in the first target surface as the optical axis pointing position of the spectrometer at the first angle. Combined observation is performed by synchronously controlling the imaging device of the celestial body detector and the spectrograph, the real pointing position of the optical axis of the spectrograph is determined through the observation result, operation is easy and convenient, and the accuracy is high.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the technical field of space probe calibration, and particularly relates to a method and device for calibrating an optical axis of a spectrometer in orbit and a storage medium. BACKGROUND

[0002] In a space probe, in order to reduce the influence of micro-vibration of a mounting surface on performance indicators of a spectrometer, a shock-absorbing pad is installed on the mounting surface of the spectrometer. The shock-absorbing pad has a certain elasticity and deformation, and after installation and precision measurement on the ground, the shock-absorbing pad will experience a mechanical environment in a powered phase, stress release of the mounting plate and the shock-absorbing pad in orbit, and long-term storage during operation of the space probe, thereby causing a slight deformation and leading to a change in the pointing direction of the optical axis of the spectrometer. SUMMARY

[0003] To overcome the problems in the prior art, the present disclosure provides a method and device for calibrating an optical axis of a spectrometer in orbit and a storage medium.

[0004] According to a first aspect of an embodiment of the present disclosure, a method for calibrating an optical axis of a spectrometer in orbit is provided, which is applied to a space probe, and the space probe is provided with an imaging device and a spectrometer; The method comprises: spiral scanning of a target celestial body; During the scanning process, an imaging position of a centroid of the target celestial body in an imaging target surface of the imaging device is continuously collected, and a thermal radiation energy of a pointing position thereof is collected by the spectrometer at a first angle based on a preset collection frequency; the continuously collected imaging positions are inversed in a first target surface, and the collected thermal radiation energy is mapped to a corresponding position in the first target surface according to a collection time, to generate first thermal radiation data; a position of a point with the highest thermal radiation energy in the first thermal radiation data in the first target surface is taken as the pointing position of the optical axis of the spectrometer at the first angle.

[0005] In some embodiments, the continuously collected imaging positions are inversed in a first target surface, and the thermal radiation energy collected by the spectrometer is mapped to a corresponding position in the first target surface according to a collection time, to generate first thermal radiation data, which comprises: the continuously collected imaging positions are inversed in a first target surface, so as to form a spiral scanning track on the first target surface; the collected thermal radiation energy is mapped to an imaging position in the spiral scanning track which is the same as the collection time thereof, to generate first thermal radiation data.

[0006] In some embodiments, before the first thermal radiation data is generated, the method further comprises: adjusting the pitch of the spiral scan; performing a spiral scan on the celestial body again based on the adjusted pitch, and continuously collecting imaging positions of the centroid of the celestial body on an imaging target surface of the imaging device during the scan, and collecting thermal radiation energy of a pointing position of the centroid based on a preset collection frequency by the spectrometer at a first angle; inverting the continuously collected imaging positions in the second target surface, and mapping the continuously collected thermal radiation energy to corresponding positions in the second target surface according to collection time, to generate second thermal radiation data; the generating the first thermal radiation data comprises: generating the first thermal radiation data based on the mapped thermal radiation energy collected multiple times in the first target surface.

[0007] In some embodiments, the performing a spiral scan on the celestial body comprises: performing an inside-out spiral scan on the celestial body; or performing an outside-in spiral scan on the celestial body.

[0008] In some embodiments, the method further comprises: adjusting the collection angle of the spectrometer to a second angle, and performing a spiral scan on the celestial body again; continuously collecting imaging positions of the centroid of the celestial body on an imaging target surface of the imaging device during the scan, and collecting thermal radiation energy of a pointing position of the centroid based on a preset collection frequency by the spectrometer at a second angle; inverting the continuously collected imaging positions in the second target surface, and mapping the continuously collected thermal radiation energy to corresponding positions in the second target surface according to collection time, to generate second thermal radiation data; taking the position of the point with the highest thermal radiation energy in the second thermal radiation data in the second target surface as a pointing position of an optical axis of the spectrometer at the second angle; taking a line connecting the pointing position of the optical axis at the first angle and the pointing position of the optical axis at the second angle as a one-dimensional scanning trajectory of the spectrometer.

[0009] In some embodiments, the performing a spiral scan on the celestial body again comprises: performing a spiral scan on the celestial body again along the scanning trajectory of the first spiral scan in a reverse scanning direction.

[0010] In some embodiments, an included angle between the second angle and the first angle is greater than a preset included angle threshold, and absolute values of the second angle and the first angle are both less than a preset upper limit of angle.

[0011] According to a second aspect of the embodiments of the present disclosure, a device for calibrating an optical axis of a spectrometer in orbit is provided, which is applied to a celestial body detector, and the celestial body detector is provided with an imaging device and a spectrometer; The device comprises: A scanning module configured to perform spiral scanning on the celestial body to be measured; A collecting module configured to continuously collect an imaging position of a centroid of the celestial body to be measured in an imaging target surface of the imaging device during the scanning, and collect thermal radiation energy of a pointing position of the centroid based on a preset collecting frequency and at a first angle by the spectrometer; A generating module configured to inverse the continuously collected imaging position in a first target surface, and map the collected thermal radiation energy to a corresponding position in the first target surface according to a collecting time, to generate first thermal radiation data; A calibrating module configured to take a position of a point with the highest thermal radiation energy in the first thermal radiation data in the first target surface as a pointing position of an optical axis of the spectrometer at the first angle.

[0012] According to a third aspect of the embodiments of the present disclosure, a computer readable storage medium is provided, which stores a computer program, and the computer program is executed by a processor to implement the method of the first aspect.

[0013] The technical solution provided by the embodiments of the present disclosure can have the following beneficial effects: The embodiments of the present disclosure can perform spiral scanning on the celestial body to be measured, continuously collect an imaging position of a centroid of the celestial body to be measured in an imaging target surface of the imaging device during the scanning, and collect thermal radiation energy of a pointing position of the centroid based on a preset collecting frequency and at a first angle by the spectrometer. The continuously collected imaging position can be inverse in a first target surface, and the collected thermal radiation energy can be mapped to a corresponding position in the first target surface according to a collecting time, to generate first thermal radiation data. A position of a point with the highest thermal radiation energy in the first thermal radiation data in the first target surface can be taken as a pointing position of an optical axis of the spectrometer at the first angle. The embodiments of the present disclosure can perform joint observation by synchronously controlling the imaging device and the spectrometer of the celestial body detector, and determine the real pointing position of the optical axis of the spectrometer based on the observation result, which is simple to operate and has high accuracy. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 An optical axis error diagram of a spectrometer and an imaging device in the embodiments of the present disclosure is shown.

[0015] Figure 2 An actual situation diagram of imaging field of view and spectrometer dotting error in the embodiments of the present disclosure is shown.

[0016] Figure 3This diagram illustrates a flow chart of an on-orbit optical axis calibration method for a spectrometer according to an embodiment of the present disclosure.

[0017] Figure 4 A schematic diagram of the scanning trajectory line of helical scanning in an embodiment of this disclosure is shown.

[0018] Figure 5 This diagram illustrates the spiral scanning trajectory obtained by imaging position inversion in an embodiment of the present disclosure.

[0019] Figure 6 A schematic diagram of thermal radiation data is shown in an embodiment of this disclosure.

[0020] Figure 7 A schematic diagram of surface-fitted thermal radiation data is shown in an embodiment of this disclosure.

[0021] Figure 8 A schematic diagram of a one-dimensional oscillating sweep trajectory of a spectrometer in an embodiment of this disclosure is shown.

[0022] Figure 9 This diagram illustrates the thermal radiation dot pattern obtained from image registration and inversion in an embodiment of this disclosure.

[0023] Figure 10 The image shown is a measured thermal radiation dot pattern obtained from image registration and inversion in an embodiment of this disclosure.

[0024] Figure 11 This diagram illustrates the structure of an on-orbit optical axis calibration device for a spectrometer according to an embodiment of the present disclosure. Detailed Implementation

[0025] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numerals in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this disclosure. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this disclosure as detailed in the appended claims.

[0026] The terminology used in this disclosure is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The singular forms “a,” “the,” and “the” as used in this disclosure and the appended claims are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term “and / or” as used herein refers to and includes any and all possible combinations of one or more of the associated listed items.

[0027] The spectrometer uses a north-south sampling method to acquire the thermal radiation energy of the target for on-orbit detection. Since it lacks imaging capabilities, to accurately retrieve the imprint of a single sampling on the target surface, an imaging device (e.g., a mid-field color camera) can be used for synchronous detection, and the thermal radiation imprint can be retrieved through image registration. This method is the most direct retrieval method and can effectively avoid error sources such as detector attitude error and detector position maintenance error. Only precise measurement of the relative optical axis error between the imaging device and the spectrometer is needed to directly achieve high-precision retrieval of a single sampling imprint corresponding to each image.

[0028] Because micro-vibrations have a significant impact on performance, the detector system plans to adopt a "wheel-free" attitude control method to establish a dedicated station for close-range detection. With wheel control disabled on the detector platform, the attitude control error expands to ±2° in all three axes, the attitude drift speed does not exceed 0.02° / s, and the position maintenance error is ±3m in all three axes. During the intermittent jet drift, there are no other external disturbances to the attitude. These errors will affect the inversion of thermal radiation detection imprints, further exacerbating the dependence on image registration methods.

[0029] To reduce the impact of micro-vibrations on the mounting surface on the spectrometer's performance, the astrophysical probe is equipped with vibration-damping pads on the mounting surface. Preliminary calibration of the spectrometer's optical axis, mounted on these pads, is performed in a ground-based environment. These vibration-damping pads possess a certain degree of elasticity and deformation. After experiencing the dynamic environment of the active phase during flight, the on-orbit stress release of the mounting plate and pads, and prolonged storage, they may undergo slight deformation, leading to changes in the optical axis orientation. Therefore, on-orbit optical axis calibration must be considered before close-range detection to ensure registration between the images acquired by the imaging device and the spectrometer's dotted detection imprints.

[0030] Figure 1 A schematic diagram of the optical axis error between the spectrometer and the imaging device is shown. The optical axis error is manifested not only in the non-coincidence of the optical axis zero point, but also in the non-parallelism between the thermal radiation dot pattern and the pixels of the imaging field of view.

[0031] Specifically, please refer to Figure 2 Assuming the thermal radiation spectrometer uses a point detection method with an angular resolution of 3.3 mrad (0.189°), at a detection distance of 20 km, the range of the point detection target is a circular field of view with a diameter of 66 m.

[0032] The imaging field of view of the imaging device is a two-dimensional window (5120×3840) in the XY plane of the detector's three-dimensional coordinate system. The field of view angle in the 5120 pixel direction is 27.32°, meaning the row pixel angle unit of the imaging field of view is 0.005336 degrees / pixel, corresponding to a pixel resolution of 1.9m at 20km. The relationship between the imaging field of view and the detector coordinates and thermal radiation marking points is as follows: Figure 2 As shown.

[0033] Where AC is the ideal pointing direction, the one-dimensional pointing mechanism's oscillating scanning surface is parallel to the long side of the imaging field of view and passes through the center of the imaging field of view.

[0034] AB represents the actual dot direction. Due to various factors, the one-dimensional pointing mechanism of the spectrometer is not parallel to the long side of the imaging field of view, resulting in a slight deviation in the actual dot direction.

[0035] In view of this, the scheme provided in this disclosure can simultaneously control the imaging device and spectrometer of the astronomical detector to conduct joint observations, and determine the true pointing position of the spectrometer's optical axis through the observation results, thereby achieving registration between the imaging device and the spectrometer.

[0036] The following will describe the exemplary implementation method in detail with reference to the accompanying drawings and embodiments.

[0037] First, this disclosure provides an on-orbit optical axis calibration method for a spectrometer, which can be performed by an astronomical detector equipped with an imaging device and a spectrometer.

[0038] Figure 3 This diagram illustrates a flowchart of an on-orbit optical axis calibration method for a spectrometer according to an embodiment of this disclosure. Figure 3 As shown in the embodiments of this disclosure, the on-orbit optical axis calibration method for a spectrometer includes the following steps.

[0039] S301 performs a spiral scan of the celestial body under test.

[0040] In some embodiments, the spiral scan can be an Archimedean isometric spiral scan, and its scan trajectory is as follows: Figure 4 As shown, this ensures that the data acquired during the scanning process is uniform in space. The scanning direction of the spiral scan can be arbitrary; for example, the celestial body to be scanned can be spirally scanned from the inside out or from the outside in. This disclosure does not limit this aspect.

[0041] S302, during the scanning process, continuously acquires the imaging position of the centroid of the celestial body to be measured in the imaging target surface of the imaging device, and acquires the thermal radiation energy of its pointing position at a first angle based on a preset acquisition frequency using a spectrometer.

[0042] In some embodiments, during the acquisition of imaging positions, the imaging device does not need to image; it can directly calculate the position of the centroid of the celestial body under test on the imaging target surface through the autonomous windowing function, and store the position in the form of row and column pixel coordinates.

[0043] In some embodiments, the spectrometer can fix its acquisition angle at a first angle within its scanning plane and continuously acquire thermal radiation energy at a preset acquisition frequency (e.g., once every 3 seconds).

[0044] S303, the continuously acquired imaging positions are inverted onto the first target surface, and the acquired thermal radiation energy is mapped onto the corresponding position on the first target surface according to the acquisition time, thereby generating the first thermal radiation data.

[0045] In some embodiments, the continuously acquired imaging positions can be inverted onto the same first target surface to form a spiral scanning trajectory on the first target surface. The first target surface can be understood as a two-dimensional plane corresponding to the imaging target surface. That is, the pixel coordinates of the centroid of the celestial body under test in the imaging target surface can be marked onto the same two-dimensional plane to form a spiral scanning trajectory.

[0046] For example, please refer to Figure 5 , Figure 5 A schematic diagram of the spiral scanning trajectory obtained by inverting the imaging position is shown. The spiral scanning trajectory can be represented in a two-dimensional coordinate system, reflecting the change in the imaging position of the centroid of the celestial body being measured on the imaging target surface during the spiral scanning process. When the imaging device is a mid-field color camera, the horizontal and vertical coordinates in this two-dimensional coordinate system correspond to the horizontal and vertical coordinates of a pixel in the mid-field color camera, respectively.

[0047] After obtaining the helical scan trajectory, the collected thermal radiation energy can be mapped to the imaging position within the helical scan trajectory that corresponds to the acquisition time, generating the first thermal radiation data. Please refer to... Figure 6 , Figure 6 A schematic diagram of the first target surface mapped with thermal radiation energy is shown. (See diagram below.) Figure 6 As shown, thermal radiation energy can be mapped onto the imaging target surface as data in the z-axis direction, thereby displaying the first thermal radiation data in the form of a three-dimensional image.

[0048] Understandably, although the initial thermal radiation data was... Figure 6 The data is presented in the form of a three-dimensional image. In practical applications, the first thermal radiation data can also be presented or stored in the form of tables, matrices, etc. Furthermore, S303 can be executed by an astronomical probe, or it can be executed by a ground-based computer after the astronomical probe transmits the collected imaging position and thermal radiation energy back to the ground. This disclosure does not limit this to any particular method.

[0049] Understandably, S303 can be executed by a celestial probe, or it can be executed by a computer deployed on the ground after the celestial probe transmits the collected imaging location and thermal radiation energy back to the ground.

[0050] S304, take the position of the point with the highest thermal radiation energy in the first thermal radiation data in the first target surface as the optical axis pointing position of the spectrometer at the first angle.

[0051] For example, please continue to refer to Figure 6 Because the spectrometer does not collect thermal radiation energy data continuously, but rather at preset time intervals, therefore Figure 6 The thermal radiation data shown is represented discretely in the three-dimensional thermal radiation data. To accurately locate the point of highest thermal radiation energy in the discrete three-dimensional thermal radiation data, one can... Figure 6 The three-dimensional thermal radiation data map shown is subjected to surface fitting to obtain, as shown below. Figure 7 The surface fitting results are shown. The surface fitting can be achieved by interpolation, least squares, or other methods, which will not be elaborated upon in this disclosure.

[0052] Please continue to refer to Figure 7 By identifying the point with the highest thermal radiation energy from the surface fitting results, the position of this point on the first target surface is determined as the optical axis pointing position of the spectrometer at the first angle. In other words, the point with the maximum z-axis energy can be determined in the three-dimensional thermal radiation data, and the coordinates of this point in the xy-plane are the optical axis pointing position of the spectrometer at the first angle. This optical axis pointing position can be understood as the actual position of the spectrometer's optical axis in the two-dimensional field of view of the imaging device when the spectrometer's acquisition angle is set to the first angle.

[0053] Thus, the embodiments disclosed herein can simultaneously control the imaging device and the spectrometer to conduct joint observations, bypassing all links in the error chain of installation, attitude, and position, and directly calculating the optical axis deviation from the detection results, making it convenient to use and accurate in calculation.

[0054] In some embodiments, before generating the first thermal radiation data, the pitch of the helical scan can be adjusted. Then, based on the adjusted pitch, the celestial body under test is helically scanned again. During the scan, the imaging position of the centroid of the celestial body under test in the imaging target surface of the imaging device is continuously acquired, and the thermal radiation energy at the pointing position is acquired by a spectrometer at a first angle based on a preset acquisition frequency. The continuously acquired imaging positions in the second scan are inverted onto the first target surface, and the thermal radiation energy acquired again is mapped to the corresponding position in the first target surface according to the acquisition time. When generating the first thermal radiation data, it can be generated based on the thermal radiation energy acquired multiple times and mapped in the first target surface.

[0055] By changing the pitch of the spiral scan and repeatedly performing spiral scans on the same celestial body under test at the first angle, the spatial resolution of the collected thermal radiation energy in the first imaging target surface can be improved, and the error caused by the surface fitting process can be reduced. This allows for a more accurate determination of the point with the highest thermal radiation energy in the first thermal radiation data, thereby improving the accuracy of the obtained optical axis pointing position.

[0056] In some embodiments, the spectrometer's acquisition angle can be adjusted to a second angle, and the celestial body to be measured can be spirally scanned again. During the scanning process, the imaging position of the centroid of the celestial body to be measured in the imaging target surface of the imaging device is continuously acquired, and the thermal radiation energy at its pointing position is acquired by the spectrometer at the second angle based on a preset acquisition frequency. The imaging positions continuously acquired during the re-scanning process are inverted onto the second target surface, and the thermal radiation energy acquired again is mapped to the corresponding position in the second target surface according to the acquisition time, generating second thermal radiation data. The position of the point with the highest thermal radiation energy in the second thermal radiation data in the second target surface is taken as the optical axis pointing position of the spectrometer at the second angle.

[0057] Understandably, since the spectrometer uses a one-dimensional pointing mechanism to complete the dotted scanning detection, the calibration is completed by using two different one-dimensional pointing angles during the on-orbit calibration process. The straight line trajectory of the one-dimensional pointing mechanism can be determined by the "two points to determine one line" method, which facilitates the determination of the pointing imprints of different one-dimensional pointing angles in the future.

[0058] Specifically, please refer to Figure 8 After obtaining the optical axis pointing positions of the spectrometer at the first angle and the second angle, the line connecting the optical axis pointing positions at the first angle and the second angle can be used as the one-dimensional sweep trajectory line of the spectrometer.

[0059] Please refer to the following. Figure 9 Once the one-dimensional sweep trajectory of the spectrometer is determined, during the subsequent detection process of the astronomical detector, the spectrometer can be registered with the imaging device. Based on the one-dimensional pointing angle of the spectrometer, a unique point M can be determined on the trajectory as the current position of the spectrometer in the field of view of the current imaging device.

[0060] exist Figure 9 Based on this, please continue to refer to Figure 10 The measured image shown demonstrates that when processing data collected by the astronomical sensor, the image collected by the imaging device and the detection position of the spectrometer can be placed on the same image target surface, thus visually obtaining the imprint of the spectrometer's thermal radiation detection position on the target surface.

[0061] The embodiments disclosed herein can integrate the detection data from the imaging device and the spectrometer during the imprint inversion process, project them onto the same screen, and simultaneously determine the detection point of the thermal radiation spectrometer and the image captured at this moment. This allows the thermal radiation spectrometer detection imprint to be intuitively marked on the surface of the small celestial body, greatly facilitating the intuitive inversion of scientific data.

[0062] In some embodiments, when performing a spiral scan on the celestial body under test again, the celestial body can be scanned again along the scanning trajectory of the first spiral scan in the opposite scanning direction. Thus, after completing one spiral scan through its own motion, the celestial body detector can directly begin the next spiral scan without returning to its initial position, thereby improving the scanning efficiency of the spiral scan.

[0063] In some embodiments, the angle between the second angle and the first angle is greater than a preset angle threshold, and the absolute value of the second angle and the absolute value of the first angle are both less than a preset angle upper limit.

[0064] Understandably, the larger the angle between the second angle and the first angle, the higher the accuracy of the spectrometer's sweep trajectory. However, since the maximum scanning angle of the helical scan depends on the maximum absolute value of the first and second angles, it is necessary to control both the absolute values ​​of the first and second angles while maintaining a significant difference between them to avoid excessively large scanning angles and excessively long scanning times.

[0065] For example, the first angle and the second angle can be two angles with the same absolute value but opposite directions, so as to reduce the absolute value of the first angle and the second angle while ensuring a large included angle between them, thereby reducing the maximum spiral scan angle of the astronomical detector. For example, when the included angle between the first angle and the second angle is 0.6°, the first angle and the second angle can be set to ±0.3° respectively, at which point the astronomical detector has a smaller maximum spiral scan angle.

[0066] Figure 11 This diagram illustrates the structure of an on-orbit optical axis calibration device for a spectrometer according to an embodiment of this disclosure. This device is applied to an astronomical detector equipped with an imaging device and a spectrometer. Figure 11 As shown, the on-orbit optical axis calibration device 1100 of the spectrometer includes: a scanning module 1101, an acquisition module 1102, a generation module 1103, and a calibration module 1104.

[0067] Specifically, the scanning module 1101 is used to perform a spiral scan of the celestial body to be measured.

[0068] The acquisition module 1102 is used to continuously acquire the imaging position of the centroid of the celestial body under test in the imaging target surface of the imaging device during the scanning process, and to acquire the thermal radiation energy of its pointing position at a first angle based on a preset acquisition frequency by a spectrometer.

[0069] The generation module 1103 is used to invert the continuously acquired imaging positions onto the first target surface, and to map the acquired thermal radiation energy onto the corresponding positions on the first target surface according to the acquisition time, thereby generating the first thermal radiation data.

[0070] The calibration module 1104 uses the position of the point with the highest thermal radiation energy in the first thermal radiation data in the first target surface as the optical axis pointing position of the spectrometer at the first angle.

[0071] In some embodiments, the generation module 1103 is specifically used to invert the continuously acquired imaging positions onto the first target surface to form a spiral scanning trajectory on the first target surface; and to map the acquired thermal radiation energy onto the imaging position in the spiral scanning trajectory that is the same as its acquisition time to generate first thermal radiation data.

[0072] In some embodiments, the on-orbit optical axis calibration device 1100 of the spectrometer further includes: an adjustment module for adjusting the pitch of the helical scan. The scanning module 1101 is further configured to perform a helical scan of the celestial body under test again based on the adjusted pitch. The acquisition module 1102 is further configured to continuously acquire the imaging position of the centroid of the celestial body under test in the imaging target surface of the imaging device during the re-scanning process, and acquire the thermal radiation energy of its pointing position at a first angle based on a preset acquisition frequency by the spectrometer. The generation module 1103 is further configured to invert the imaging positions continuously acquired during the re-scanning onto the first target surface, and map the re-acquired thermal radiation energy onto the corresponding position in the first target surface according to the acquisition time. Based on the thermal radiation energy acquired multiple times and mapped in the first target surface, first thermal radiation data is generated.

[0073] In some embodiments, the scanning module 1101 is specifically used to perform a spiral scan of the celestial body under test from the inside out; or to perform a spiral scan of the celestial body under test from the outside in.

[0074] In some embodiments, the adjustment module is further configured to adjust the acquisition angle of the spectrometer to a second angle. The scanning module 1101 is further configured to perform a spiral scan of the celestial body under test again after the acquisition angle is adjusted. The acquisition module 1102 is further configured to continuously acquire the imaging position of the centroid of the celestial body under test in the imaging target surface of the imaging device during the re-scanning process, and acquire the thermal radiation energy of its pointing position at the second angle based on a preset acquisition frequency by the spectrometer. The generation module 1103 is further configured to invert the imaging position continuously acquired during the re-scanning process onto the second target surface, and map the re-acquired thermal radiation energy to the corresponding position in the second target surface according to the acquisition time to generate second thermal radiation data; and take the position of the point with the highest thermal radiation energy in the second thermal radiation data in the second target surface as the optical axis pointing position of the spectrometer at the second angle. The on-orbit optical axis calibration device 1100 of the spectrometer further includes: a determination module, configured to take the line connecting the optical axis pointing position at the first angle and the optical axis pointing position at the second angle as the one-dimensional sweep trajectory line of the spectrometer.

[0075] In some embodiments, the scanning module 1101 is further configured to perform a spiral scan of the celestial body under test again in the opposite scanning direction along the scanning trajectory of the first spiral scan.

[0076] In some embodiments, the angle between the second angle and the first angle is greater than a preset angle threshold, and the absolute value of the second angle and the absolute value of the first angle are both less than a preset angle upper limit.

[0077] In some embodiments, the spiral scan is an Archimedes equidistant spiral scan.

[0078] Those skilled in the art will understand that various aspects of this disclosure can be implemented as a system, method, or program product. Therefore, various aspects of this disclosure can be specifically implemented in the following forms: a completely hardware implementation, a completely software implementation (including firmware, microcode, etc.), or a combination of hardware and software aspects, collectively referred to herein as a "circuit," "module," or "system."

[0079] In exemplary embodiments of this disclosure, a computer-readable storage medium is also provided, which may be a readable signal medium or a readable storage medium. A program product capable of implementing the methods described above is stored thereon. In some possible implementations, various aspects of this disclosure may also be implemented as a program product including program code, which, when run on a terminal device, causes the terminal device to perform the steps described in the "Exemplary Methods" section of this specification according to various exemplary embodiments of this disclosure.

[0080] Other embodiments of this disclosure will readily occur to those skilled in the art upon consideration of the specification and practice of the invention disclosed herein. This disclosure is intended to cover any variations, uses, or adaptations of this disclosure that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only, and the true scope and spirit of this disclosure are indicated by the appended claims.

Claims

1. A method for on-orbit optical axis calibration of a spectrometer, characterized in that, The application is applied to a celestial body detector provided with an imaging device and a spectrometer; The method comprises: spiral scanning of the celestial body to be measured; during the scanning, continuously collecting the imaging position of the centroid of the celestial body to be measured on the imaging target surface of the imaging device, and collecting the thermal radiation energy of the pointing position of the centroid of the celestial body to be measured at the first angle by the spectrometer based on a preset collection frequency; inverting the continuously collected imaging position in the first target surface, and mapping the collected thermal radiation energy to the corresponding position in the first target surface according to the collection time, to generate first thermal radiation data; the position of the point with the highest thermal radiation energy in the first target surface in the first thermal radiation data is taken as the pointing position of the optical axis of the spectrometer at the first angle.

2. The method of claim 1, wherein, The method further comprises: inverting the continuously collected imaging position in the first target surface, so as to form a spiral scanning track on the first target surface; mapping the collected thermal radiation energy to the imaging position in the spiral scanning track with the same collection time, to generate first thermal radiation data.

3. The method of claim 2, wherein, Before the first thermal radiation data is generated, the method further comprises: adjusting the pitch of the spiral scanning; based on the adjusted pitch, performing spiral scanning of the celestial body to be measured again, and during the scanning, continuously collecting the imaging position of the centroid of the celestial body to be measured on the imaging target surface of the imaging device, and collecting the thermal radiation energy of the pointing position of the centroid of the celestial body to be measured at the first angle by the spectrometer based on a preset collection frequency; inverting the continuously collected imaging position in the first target surface, and mapping the collected thermal radiation energy to the corresponding position in the first target surface according to the collection time, to generate first thermal radiation data; The method further comprises: generating first thermal radiation data based on the thermal radiation energy collected multiple times in the first target surface.

4. The method of claim 1, wherein, The spiral scanning of the celestial body to be measured comprises: performing spiral scanning of the celestial body to be measured from inside to outside; or performing spiral scanning of the celestial body to be measured from outside to inside.

5. The method of claim 1, wherein, The method further comprises: adjusting the collection angle of the spectrometer to a second angle, and performing spiral scanning of the celestial body to be measured again; during the scanning, continuously collecting the imaging position of the centroid of the celestial body to be measured on the imaging target surface of the imaging device, and collecting the thermal radiation energy of the pointing position of the centroid of the celestial body to be measured at the second angle by the spectrometer based on a preset collection frequency; inverting the continuously collected imaging position in the second target surface during the scanning, and mapping the collected thermal radiation energy to the corresponding position in the second target surface according to the collection time, to generate second thermal radiation data; the position of the point with the highest thermal radiation energy in the second thermal radiation data in the second target surface is taken as the pointing position of the optical axis of the spectrometer at the second angle; the line connecting the pointing position of the optical axis at the first angle and the pointing position of the optical axis at the second angle is taken as a one-dimensional swing scanning track line of the spectrometer.

6. The method of claim 5, wherein, The measured celestial body is scanned again by a spiral scan, comprising: The measured celestial body is scanned again by a spiral scan along the scan track of the first spiral scan in a reverse scan direction.

7. The method of claim 5, wherein, The included angle between the second angle and the first angle is greater than a preset included angle threshold, and the absolute values of the second angle and the first angle are both less than a preset upper limit of angle.

8. The method according to any one of claims 1 to 7, characterized in that, The spiral scan is an Archimedes equidistant spiral scan.

9. An apparatus for in-orbit optical axis calibration of a spectrometer, characterized in that, The application is applied to a celestial body detector, and the celestial body detector is provided with an imaging device and a spectrometer. The device comprises: A scan module for scanning a measured celestial body by a spiral scan; A collection module for continuously collecting an imaging position of a centroid of the measured celestial body in an imaging target surface of the imaging device during the scan, and collecting thermal radiation energy of a pointing position by the spectrometer at a first angle based on a preset collection frequency; A generation module for inverting the continuously collected imaging position in a first target surface, and mapping the collected thermal radiation energy to a corresponding position in the first target surface according to a collection time to generate first thermal radiation data; A calibration module for taking a position of a point with the highest thermal radiation energy in the first target surface as a pointing position of an optical axis of the spectrometer at the first angle.

10. A computer-readable storage medium having stored thereon a computer program, characterized in that, The computer program is executed by a processor to implement the method in any one of claims 1 to 8.

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