Remote sensing load channel inter-registration device and method thereof
By designing a registration device between remote sensing payload channels, and using a metal bucket and a one-dimensional rotation mechanism in conjunction with a lunar reference source for actual measurements, the problem of insufficient registration accuracy between remote sensing payload channels was solved, and the effectiveness of remote sensing data and the feasibility of on-orbit registration were realized.
Patent Information
- Application Number
- CN202610175311.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-02-06
- Publication Date
- 2026-06-23
AI Technical Summary
Existing technologies cannot achieve accurate registration between remote sensing payload channels on the ground. In particular, the registration accuracy between remote sensing payload channels is insufficient due to factors such as the size of the remote sensing payload and natural interference, which affects the effectiveness of remote sensing data.
A registration device for remote sensing payload channels was designed, including a metal bucket and a one-dimensional rotation mechanism. The metal bucket provides electromagnetic shielding, and the one-dimensional rotation mechanism enables full-dimensional scanning of the remote sensing payload. The moon is used as a reference source for actual measurement to correct channel deviations. Semi-physical simulation is used for comparison.
Accurate registration between remote sensing payload channels was achieved under real-world operating conditions across the entire aperture and the entire data link, ensuring the validity of microwave remote sensing data and verifying the feasibility of registration between on-orbit remote sensing payload channels.
Smart Images
Figure CN122258965A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of remote sensing instrument technology, specifically relating to a registration device and method for remote sensing payload channels. Background Technology
[0002] The instruments, equipment, and subsystems carried on a satellite to directly accomplish specific tasks during its on-orbit operation are called satellite payloads. Microwave and infrared payloads are important payloads on meteorological satellites. They enable satellites to detect atmospheric temperature and humidity profiles, surface wind fields, and sea surface wind fields by rotating antennas or reflectors. Currently, they are widely used in weather forecasting, resource exploration, and environmental protection.
[0003] Registration between remote sensing payload channels is one of the key testing items in the development of remote sensing instruments. It is a prerequisite for the normal operation of the instrument to obtain high-precision and high-reliability remote sensing data, and an important basis for the instrument to analyze and measure objects.
[0004] The design requirements for payloads specify clear requirements for the registration accuracy between remote sensing payload channels. Currently, due to limitations such as the size of the remote sensing payload, the large-aperture antenna, and natural interference, the registration between remote sensing payload channels can only be obtained through semi-physical simulation of the antenna pattern. As antenna apertures increase and the number of cascaded reflector antennas grows, the antenna profile and orientation change significantly after satellite launch and orbit insertion. This leads to substantial deviations in the beam pointing of the remote sensing payload obtained through ground simulation, potentially rendering the remote sensing data invalid. Accurate testing of the beam pointing of the remote sensing payload channels and registration of the pointing between different channels are crucial for ensuring the pointing accuracy of the remote sensing payload and guaranteeing the quality of remote sensing data.
[0005] Therefore, it is urgent to develop and establish dedicated testing equipment for registration between remote sensing payload channels. Under real working conditions such as full aperture and full channel, beam pointing registration tests of different channels of remote sensing payloads should be carried out. These tests play a decisive role in obtaining high-accuracy beam pointing of the payload. The key technologies to be solved and the technical platforms to be established can support the performance testing of satellite microwave or infrared payloads.
[0006] Li Yangwei, Sun Liang, et al., in their paper "Research on Batch Automatic Registration of Domestic Gaofen Series Remote Sensing Satellite Imagery" published in *China Agricultural Information*, Vol. 35, No. 3, June 2023, proposed an automatic registration and orthorectification package (AROP). They selected 16m resolution Gaofen-1 and Gaofen-6 wide-swath imagery and 3m resolution Gaofen-2 and Gaofen-7 multispectral imagery as experimental data. Using geometrically corrected 10m resolution Sentinel-2 imagery and 3m resolution Google imagery as reference images, they conducted batch geometric registration experiments in agricultural and urban land use scenarios. The registration results were then visually verified and quantitatively evaluated.
[0007] In their paper "Image Registration Algorithm Based on Multi-Scale Harris Corner Detection" published in *Electro-Optics and Control*, Vol. 31, No. 1, 2024, Shang Mingshu and Wang Kechao proposed an efficient and simple algorithm to address the problems of existing multi-scale operator algorithms, which are complex, computationally intensive, and generally inaccurate. First, a multi-scale space is established, and the operator extracts feature points in this space, describing the features using simplified 3D eigenvectors. The nearest neighbor method is used to match feature points; then, an improved similar triangle method is employed to filter matching points; next, an improved K-algorithm is used to group feature points, ensuring that feature points within a group cluster together and feature points between groups are spaced further apart; finally, an improved algorithm is applied to select feature points from different groups to calculate the transformation matrix, avoiding the problem of selected feature points being too close together and the algorithm getting trapped in local optima. Experiments verify the performance of the proposed algorithm.
[0008] In their paper "Methods for Improving Geometric Positioning Accuracy of Ocean Imaging Images from Medium and High Orbit Satellites" published in Spacecraft Engineering, Vol. 29, No. 2, April 2020, Liu Xiaolei, Dong Xiaomeng, et al. proposed a method to improve the positioning accuracy of ocean images by utilizing the large imaging range of medium and high orbit satellites and coordinating attitude maneuvers. This method involves finding regions with characteristic points in a short time, matching satellite images with high-precision control images to locate control points, solving for the bias matrix, and then compensating the bias matrix of the region to the ocean area, thereby improving the positioning accuracy of the images.
[0009] In their paper "Geometric Positioning Method of HY-1C / D Satellite Ocean Color and Temperature Scanner" published in the May 2022 issue of the *Acta Oceanologica Sinica*, Liu Jianyang, Mao Zhihua, et al. proposed extracting satellite ephemeris from Level 0 data and using interpolation to obtain the satellite position and velocity corresponding to the sampling time, thereby deriving the transformation matrix from the orbital (ORB) coordinate system to the geocentric rotation (ECR) coordinate system. Based on the characteristics of quaternary point-by-point scanning, the central view vector is rotated around the X and Y axes by corresponding angles to obtain the ORB view vectors of each sampling point in the scan line. A model of the relationship between the view vector and the Earth's intersection point is established, thereby enabling geolocation of remote sensing images drawn from band data. Lin Danying, Huang Lilin, et al., in their paper "A High-Precision Image Registration Method for Multi-Channel Single-Molecule Localization" published in Acta Physica Sinica, Vol. 73, No. 6, 2024, proposed a high-precision image registration method based on local nonlinear transformation and mismatch point elimination. This method can directly use randomly distributed fluorescent bead samples as reference materials. By monitoring and iteratively screening control points during feature matching and transformation model parameter estimation, it eliminates inaccurately matched control point pairs caused by inaccurate or poor single-molecule localization. This eliminates the adverse effects of using randomly distributed fluorescent bead samples as reference materials on accurate control point acquisition and precise matching. Simultaneously, a second-order polynomial fitting based on local weighted averaging is used for transformation model parameter estimation to better suit situations with local nonlinear deformation between different channels. The results show that this method only requires three iterations to find and eliminate inaccurately located and mismatched control point pairs, thus achieving more accurate transformation model parameter estimation and improving registration accuracy by an order of magnitude.
[0010] However, the above methods for improving the registration accuracy between microwave remote sensing payload channels have the following problems: Microwave remote sensing payloads using a three-reflector antenna cascade method have a complex structure. The reflector antennas are affected by factors such as transmission, deployment after orbit insertion, and thermal environment, resulting in changes in surface accuracy. There are also uncertain factors such as shape and position changes between reflectors. Furthermore, due to limitations such as the size of the remote sensing payload and natural interference, it is impossible to achieve registration testing between remote sensing payload channels under ground conditions.
[0011] To achieve registration testing between remote sensing payload channels, this invention designs a registration device and method for remote sensing payload channels, thus solving the aforementioned problems. Summary of the Invention
[0012] To address the shortcomings of existing technologies, the present invention aims to provide a registration device and method for remote sensing payload channels.
[0013] According to the present invention, a registration device between remote sensing payload channels includes: a metal bucket, a remote sensing payload, and a one-dimensional rotation mechanism; the metal bucket has an upward-facing opening; the one-dimensional rotation mechanism is housed in the metal bucket; and the remote sensing payload is housed in the metal bucket and disposed on the rotating end of the one-dimensional rotation mechanism.
[0014] Preferably, the sidewall of the metal bucket is inclined outward from bottom to top.
[0015] Preferably, the one-dimensional rotating mechanism is located at the center of the bottom of the metal bucket.
[0016] Preferably, the remote sensing payload is a real aperture radiometer with an offset Cassegrain three-reflector antenna, with the cold source field of view set to 210°-230°, the hot source field of view set to 310°-330°, and the remote sensing detection field of view set to 40°-140°.
[0017] According to the present invention, a method for registration between remote sensing payload channels is provided, employing a remote sensing payload channel registration device, and the steps include: Step S1: Place the metal bucket in an open outdoor area with no tall obstructions around it; Step S2: Place the remote sensing payload and the one-dimensional rotation mechanism in the center of the metal hopper; Step S3: Deploy the remote sensing payload reflector antenna and measure the main reflector surface data and the shape and position data between the main and secondary reflectors through photogrammetry, which are used for antenna pattern semi-physical simulation. Step S4: Select a clear, cloudless day with a full moon to conduct a moon-viewing test, and adjust the remote sensing payload so that the moon is within its field of view; Step S5: The remote sensing payload is powered on and a one-dimensional scan of the moon is achieved by rotating the reflector, while simultaneously completing the calibration of the cold source and the heat source. Step S6: Adjust the one-dimensional rotation mechanism to achieve another-dimensional scanning and detection of the moon by rotating the remote sensing payload reflector antenna; Step S7: Complete the remote sensing payload detection data acquisition work and obtain the response of lunar radiation energy in different receiving channels of the remote sensing payload; Step S8: Measure the beam pointing deviation of different channels of the remote sensing payload, and use it as a benchmark to compare the beam pointing deviation between channels obtained by the semi-physical simulation, and complete the registration work between remote sensing payload channels.
[0018] Preferably, in step S1: the metal bucket is a complete conductor with zero surface emissivity, and its height is set to 1.5-2 times the height of the remote sensing payload device to ensure complete shielding against external radiation interference.
[0019] Preferably, in step S3: using photogrammetry equipment based on multi-angle images, using geometric relationships and image matching technology, the spatial three-dimensional coordinates of the target are calculated by bundle adjustment to obtain the shape and position data of the three-reflector antenna, and using GRASP software to carry out semi-physical simulation of the antenna pattern to obtain the beam pointing deviation of the remote sensing payload channel antenna.
[0020] Preferably, in step S5: the remote sensing payload is equipped with 54GHz, 183GHz, and 425GHz receiving channels to cover the temperature and humidity detection channels of the remote sensing payload; based on the significant brightness temperature signal from actual observation data, the moon is used as a reference source for registration between the remote sensing payload channels.
[0021] Preferably, in step S6: a one-dimensional rotation mechanism enables the remote sensing payload to rotate one-dimensionally in the horizontal plane; a rotating scanning mechanism is set in the feed receiving calibration system for the remote sensing payload, which performs a 360° off-focus scan around the focal point of the first secondary reflector by rotating the reflector, and then performs a one-dimensional scan detection of the target by the main reflector; a rotating scanning mechanism is set at the feed receiving port to avoid the interference of the large torque generated by the rotating main reflector antenna.
[0022] Preferably, in step S8: using the antenna pattern obtained from the lunar observation experiment as a reference, the pointing of the remote sensing payload channels is measured through the lunar observation experiment, and the deviation between the remote sensing payload channels is measured. Comparison with the semi-physical simulation shows that the beam pointing deviation between the remote sensing payload channels is within the allowable range of the design specifications, thus verifying the feasibility of the experiment and simultaneously verifying the feasibility of using the semi-physical simulation method to conduct channel registration on the ground after the satellite enters orbit.
[0023] Compared with existing technologies, this invention has the following advantages: It establishes a registration test device for remote sensing payload channels under real working conditions such as full aperture and full link. Using the moon as a reference source, the microwave beam pointing of the remote sensing payload is actually measured, and the deviation between channels is corrected to ensure the validity of microwave remote sensing data. At the same time, the feasibility of the registration scheme between on-orbit remote sensing payload channels is verified. Attached Figure Description
[0024] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the structure of the present invention.
[0025] Figure 2 This is a diagram showing the registration test results between remote sensing payload channels of the present invention.
[0026] Figure 3 This is a diagram showing the registration test results between remote sensing payload channels of the present invention.
[0027] Figure 4 This is a flowchart of the method for registration between remote sensing payload channels according to the present invention.
[0028] The figure shows: 1. Metal bucket; 2. Remote sensing payload; 3. One-dimensional rotating mechanism. Detailed Implementation
[0029] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.
[0030] like Figure 1 , Figure 2 As shown, a registration device and method for inter-channel remote sensing payloads includes: a metal hopper 1, a remote sensing payload 2, and a one-dimensional rotation mechanism 3; the metal hopper 1 has its opening facing upwards. The one-dimensional rotation mechanism 3 is housed within the metal hopper 1. The remote sensing payload 2 is housed within the metal hopper 1 and is positioned on the rotating end of the one-dimensional rotation mechanism 3.
[0031] The working principle of this application is as follows: the metal bucket 1 provides a good electromagnetic shielding environment for the remote sensing payload 2. Its sidewalls are inclined outward from bottom to top, which can effectively isolate external radiation interference and expand the detection field of view of the remote sensing payload 2. The one-dimensional rotation mechanism 3 drives the remote sensing payload 2 to achieve 360° scanning detection in the horizontal plane, and the remote sensing payload 2 completes 360° scanning in the vertical plane through the rotating reflector at the feed port. The two work together to achieve all-dimensional target detection.
[0032] Specifically, the metal bucket 1 provides a good shielding environment for the remote sensing payload 2, and the sidewalls of the metal bucket 1 are inclined outward from bottom to top to provide a larger detection field of view for the remote sensing payload 2.
[0033] In one embodiment, the one-dimensional rotation mechanism 3 is located at the center of the bottom of the metal hopper 1. The one-dimensional rotation mechanism 3 includes a base, a drive motor, and a turntable. The base is housed at the inner bottom of the metal hopper 1. The drive turntable is horizontally positioned, with its axis vertically rotatably connected to the base. The drive motor is fixed to the base, and its output shaft is coaxially connected to the turntable. The remote sensing payload 2 is placed above the turntable. The one-dimensional rotation mechanism 3 enables the remote sensing payload 2 to perform 360° scanning detection in the horizontal plane, providing one-dimensional target detection.
[0034] In one embodiment, the remote sensing payload 2 is a real-aperture radiometer with an offset-fed Cassegrain three-reflector antenna, a microwave remote sensing instrument that achieves 360° scanning detection in the vertical plane by setting a rotating reflector on the feed port surface. The cold source field of view is set to 210°-230°, the hot source field of view is set to 310°-330°, and the remote sensing detection field of view is set to 40°-140°.
[0035] This application also provides a method for registration between remote sensing payload channels, using a remote sensing payload channel registration device, the steps of which include: Step S1: Place the metal bucket 1 in an open outdoor area with no tall obstructions around it.
[0036] Step S2: Place the remote sensing payload 2 and the one-dimensional rotation mechanism 3 in the center of the metal bucket 1.
[0037] Step S3: Deploy the reflector antenna of remote sensing payload 2, and measure the main reflector surface data and the positional data between the main and secondary reflectors through photogrammetry, which are used for semi-physical simulation of the antenna pattern.
[0038] Step S4: Select a clear, cloudless day with a full moon to conduct a moon-viewing test, and adjust the remote sensing payload 2 so that the moon is within its field of view.
[0039] Step S5: The remote sensing payload 2 is powered on and performs a one-dimensional scan of the moon by rotating the reflector, while simultaneously completing the calibration of the cold source and the heat source.
[0040] Step S6: Adjust the one-dimensional rotation mechanism 3 to achieve another-dimensional scanning and detection of the moon by rotating the reflector antenna of the remote sensing payload 2.
[0041] Step S7: Complete the data acquisition work of remote sensing payload 2 and obtain the response of lunar radiation energy in different receiving channels of remote sensing payload 2.
[0042] Step S8: Measure the beam pointing deviation of different channels of remote sensing payload 2, and use it as a benchmark to compare the beam pointing deviation between channels obtained by the semi-physical simulation, and complete the registration work between channels of remote sensing payload 2.
[0043] In step S1: the metal bucket 1 is a complete conductor with zero surface emissivity, and its height is set to 1.5-2 times the height of the remote sensing payload 2 device to ensure complete shielding against external radiation interference.
[0044] In step S3: using photogrammetry equipment based on multi-angle images, and using geometric relationships and image matching technology, the three-dimensional spatial coordinates of the target (the target is placed on the surface of the reflector antenna) are calculated by bundle adjustment to obtain the shape and position data of the three-reflector antenna. The antenna pattern semi-physical simulation is carried out using GRASP software to obtain the beam pointing deviation of the two-channel antenna of the remote sensing payload.
[0045] In step S5: Remote sensing payload 2 is equipped with 54GHz, 183GHz, and 425GHz receiving channels, covering the temperature and humidity detection channels of remote sensing payload 2. Based on the significant brightness temperature signal from actual observation data, the moon can be used as a reference source for inter-channel registration of remote sensing payload 2.
[0046] In step S6: the one-dimensional rotation mechanism 3 enables the remote sensing payload 2 to rotate one-dimensionally in the horizontal plane. The remote sensing payload 2 is equipped with a rotating scanning mechanism within the feed receiving calibration system. This mechanism uses a rotating reflector to perform a 360° off-focus scan around the focal point of the first secondary reflector (hyperbolic surface), and then uses the main reflector to perform a one-dimensional scan of the target. The rotating scanning mechanism is positioned at the feed receiving port to avoid interference from the large torque generated by the rotating main reflector antenna.
[0047] In step S8: using the antenna pattern obtained from the lunar observation experiment as a reference, the pointing of channel 2 of the remote sensing payload is measured through the lunar observation experiment, and the deviation between channels 2 of the remote sensing payload is measured. Comparison with the semi-physical simulation shows that the beam pointing deviation between channels 2 of the remote sensing payload is within the allowable range of the design specifications, thus verifying the feasibility of the experiment. Simultaneously, it verifies the feasibility of using the semi-physical simulation method to conduct channel registration on the ground after the satellite enters orbit.
[0048] In one embodiment, this application also provides a method for registration between remote sensing payload channels.
[0049] In this embodiment, the fully conductive metal bucket 1 is placed in an open outdoor area, free from tall obstacles. The remote sensing payload 2 is placed inside the metal bucket 1 on a one-dimensional rotating mechanism 3, with the remote sensing antenna pointing upwards. This ensures that the metal bucket 1 can shield against radiation interference entering the antenna's side lobes and back lobes. Figure 1 As shown.
[0050] The lunar observation experiment was conducted on a clear, full moon day, ensuring that the moon was within the scanning field of view of remote sensing payload 2, remote sensing payload 2 was powered on, the rotating reflector of remote sensing payload 2 was in scanning mode, and the one-dimensional scanning mechanism was in a state of readiness for adjustment.
[0051] After the remote sensing payload 2 has stabilized, data is collected from each point within the detection area. The sampling period of the remote sensing payload 2 is 5ms, and the scanning period of the scanning mirror is 3.6s. Data collection begins at +40°, and the data collection area is within the range of +40° to +140°.
[0052] Adjust the one-dimensional rotation mechanism 3, rotate horizontally at 10° intervals, repeat the data acquisition work of remote sensing payload 2, and complete the 360° lunar observation exploration in the horizontal direction.
[0053] like Figure 2 As shown, after data acquisition is completed, data processing is performed. The beam pointing obtained from the semi-physical simulation antenna pattern is used as a reference and compared with the beam pointing of each channel obtained from the data acquired by remote sensing payload 2. Based on the data comparison deviation, the beam pointing between the channels of remote sensing payload 2 is registered and corrected.
[0054] In summary, this invention fills a gap in the prior art and establishes a registration test device for two channels of a remote sensing payload under real-world operating conditions, including full-aperture and full-link operation. Using the moon as a reference source, the microwave beam pointing of the two remote sensing payloads is actually measured, and channel deviations are corrected to ensure the validity of the microwave remote sensing data. Simultaneously, the feasibility of the registration scheme for the two channels of the on-orbit remote sensing payloads is verified.
[0055] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.
[0056] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.
Claims
1. A registration device between remote sensing payload channels, characterized in that, include: The metal bucket (1), the remote sensing payload (2), and the one-dimensional rotating mechanism (3) are arranged in the metal bucket (1), the remote sensing payload (2) is arranged in the metal bucket (1), and the one-dimensional rotating mechanism (3) is arranged on the rotating end of the one-dimensional rotating mechanism (3).
2. The remote sensing payload inter-channel registration device according to claim 1, characterized in that, The sidewall of the metal bucket (1) is inclined outward from bottom to top.
3. The remote sensing payload inter-channel registration device according to claim 1, characterized in that, The one-dimensional rotating mechanism (3) is located at the center of the bottom of the metal bucket (1).
4. The remote sensing payload inter-channel registration device according to claim 3, characterized in that, The remote sensing payload (2) is a real aperture radiometer with an offset Cassegrain three-reflector antenna, with the cold source field of view set to 210°-230°, the hot source field of view set to 310°-330°, and the remote sensing detection field of view set to 40°-140°.
5. A method for registration between remote sensing payload channels, employing the remote sensing payload channel registration device according to any one of claims 1-4, characterized in that the steps include... include: Step S1: Place the metal bucket (1) in an open outdoor area with no tall obstructions around it; Step S2: Place the remote sensing payload (2) and the one-dimensional rotation mechanism (3) at the center of the metal bucket (1); Step S3: Deploy the remote sensing payload (2) reflector antenna, and complete the measurement of the main reflector surface data and the shape and position data between the main and secondary reflectors through photogrammetry, which is used for antenna pattern semi-physical simulation; Step S4: Select a clear, cloudless day with a full moon for the moon observation test, and adjust the remote sensing payload (2) so that the moon is within its field of view; Step S5: The remote sensing payload (2) is powered on and a one-dimensional scanning detection of the moon is achieved by rotating the reflector, while the two-point calibration of the cold source and the heat source is completed at the same time; Step S6: Adjust the one-dimensional rotation mechanism (3) to achieve another-dimensional scanning and detection of the moon by rotating the reflector antenna of the remote sensing payload (2); Step S7: Complete the data acquisition work of the remote sensing payload (2) and obtain the response of lunar radiation energy in different receiving channels of the remote sensing payload (2); Step S8: Measure the beam pointing deviation of different channels of the remote sensing payload (2), and use it as a benchmark to compare the beam pointing deviation between channels obtained by the semi-physical simulation, and complete the registration work between the channels of the remote sensing payload (2).
6. The method for registration between remote sensing payload channels according to claim 5, wherein in step S1: the metal bucket (1) is a complete conductor with zero surface emissivity and its height is set to 1.5-2 times the height of the remote sensing payload (2) device to ensure complete shielding against external radiation interference.
7. The method for registration between remote sensing payload channels according to claim 5, wherein in step S3: using photogrammetry equipment based on multi-angle images, using geometric relationships and image matching technology, the spatial three-dimensional coordinates of the target are calculated by bundle adjustment to obtain the shape and position data of the three-reflector antenna, and using GRASP software to carry out semi-physical simulation of the antenna pattern to obtain the beam pointing deviation of the antenna of the remote sensing payload (2) channel.
8. The method for inter-channel registration of remote sensing payloads according to claim 5, wherein in step S5: the remote sensing payload (2) is equipped with 54GHz, 183GHz and 425GHz receiving channels to cover the temperature and humidity detection channels of the remote sensing payload (2); based on the significant brightness temperature signal of the actual observation data, the moon is used as the reference source for inter-channel registration of the remote sensing payload (2).
9. The method for registration between remote sensing payload channels according to claim 5, wherein in step S6: a one-dimensional rotation mechanism (3) realizes one-dimensional rotation of the remote sensing payload (2) in the horizontal plane; a rotating scanning mechanism is set in the feed receiving calibration system for the remote sensing payload (2), and a 360° off-focus scan is achieved around the focal point of the first secondary reflector by rotating the reflector, and then a one-dimensional scan detection of the target is achieved by the main reflector; a rotating scanning mechanism is set in the feed receiving port to avoid the interference of the large torque generated by the rotating main reflector antenna.
10. The method for inter-channel registration of remote sensing payloads according to claim 5, wherein in step S8: using the antenna pattern obtained from the lunar observation experiment as a reference, the pointing of the remote sensing payload (2) channels is measured through the lunar observation experiment, and the deviation between the channels of the remote sensing payload (2) is measured. Comparison with the semi-physical simulation shows that the beam pointing deviation between the channels of the remote sensing payload (2) is within the allowable range of the design specifications, thus verifying the feasibility of the experiment and simultaneously verifying the feasibility of conducting inter-channel registration on the ground using the semi-physical simulation method after the satellite enters orbit.