Method and Device for Optimizing Mounting Surface Deformation of Multi-Star Stacked Flat Panel Satellite High-Frequency Feed Antenna

Abstract

This invention discloses a method and apparatus for optimizing the deformation of the mounting surface of a high-frequency feed antenna for multi-satellite stacked flat-panel satellite. The method includes: mounting two feed antennas coplanarly at the middle position (low response zone) of the long side of the flat-panel satellite, while satisfying structural strength, thermal control, and antenna motion envelope constraints; mounting star sensors on the nearest coplanar mounting surfaces of each feed antenna; adjusting the star sensor mounting matrix through mutual calibration of multiple star sensors, using the central star sensor as a reference; adjusting the feed antenna mounting matrix using the nearest star sensors as references; and adding fault redundancy control. This invention, through a system-level design of installation layout, on-orbit calibration, and redundancy protection, requires no additional components, is suitable for mass production and rapid networking, and solves the problems of low pointing accuracy and poor reliability of high-frequency antennas for multi-satellite stacked flat-panel satellites.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite communication, in particular to a system-level optimization method and device for high-frequency band feed antenna installation surface deformation of multi-satellite stacked flat panel satellites, which is suitable for installation and on-orbit pointing accuracy control of high-frequency band feed antennas in multi-satellite stacked flat panel satellites, especially for flat panel satellites with a large length-width ratio, and can effectively solve the pointing error problem caused by the deformation of the feed antenna installation surface, and ensure the stability and reliability of the satellite-ground communication link. BACKGROUND

[0002] With the rapid development of satellite internet technology, the demand for data transmission rate and capacity of satellite-ground communication is increasing, which promotes the development of satellite-borne antennas towards high frequency band, large aperture, high precision pointing and tracking. The beam of high frequency band antenna (such as Ka band, Q / V band) is usually a point beam, and its beam width is extremely narrow (usually only a few tenths of a degree), which makes the antenna pointing accuracy have a decisive influence on the satellite-ground signal reception quality and link transmission effectiveness - even a small pointing deviation (such as a few tens of angular seconds) can cause a significant decrease in satellite-ground signal reception strength, and even cause link interruption.

[0003] In the multi-satellite stacked flat panel satellite structure, due to the large length-width ratio of the whole satellite (the length-width ratio of some flat panel satellites can reach more than 5:1), uneven distribution of structural stiffness, and the need to withstand complex mechanical environment (such as vibration and impact during launch phase) and thermal environment (such as solar radiation and temperature change in the earth's shadow area) during on-orbit operation, the installation surface of high frequency band feed antenna is prone to deformation. In the prior art, the optimization for antenna pointing accuracy is mostly focused on the antenna structure design or on-orbit attitude adjustment of a single satellite, and there is a lack of system-level optimization scheme for multi-satellite stacking scenario:

[0004] The traditional antenna installation layout does not consider the mechanical coupling effect of multi-satellite stacking, and the feed antenna is usually installed at the long end edge area of the satellite structure. The long end edge area is easily affected by the mechanical response of the active stage, the stress release of the structural material in orbit, and the thermal deformation of the structure caused by long-term high and low temperature in orbit, which can increase the deformation of the installation surface and further increase the pointing error;

[0005] The star sensor, as a satellite attitude measurement reference, is usually installed separately from the feed antenna, and the deformation difference between the two installation surfaces will cause the deviation of attitude measurement and antenna pointing correction, further reducing the pointing accuracy;

[0006] During on-orbit adjustment, a single star sensor is mostly relied on as a reference, and there is a lack of redundancy design. Once the reference star sensor fails, the antenna pointing will be out of control;

[0007] The existing optimization scheme does not sufficiently integrate multiple constraints such as structural strength, thermal control requirements, antenna motion envelope, and star sensor field of view, and is prone to problems of losing one thing for another, for example, increasing structural stiffness to reduce the deformation of the mounting surface, resulting in the satellite being overweight, or using different surfaces and a relatively long distance for the antenna and star sensor to ensure the antenna motion range and the star sensor field of view.

[0008] Therefore, for the special structure and working environment of the multi-satellite stacked flat panel satellite, designing a method that takes into account multiple constraints and can realize system-level optimization of the mounting surface deformation system is a key prerequisite for solving the pointing accuracy problem of the high-frequency feed antenna, and is also a technical bottleneck that needs to be broken through in the current satellite communication technology field. SUMMARY

[0009] The purpose of the present application is to overcome the defects in the prior art that the deformation of the mounting surface of the high-frequency feed antenna of the multi-satellite stacked flat panel satellite leads to low pointing accuracy, poor reliability, and insufficient constraint adaptability, and to provide a system-level optimization method for the deformation of the mounting surface of the high-frequency feed antenna of the multi-satellite stacked flat panel satellite. Based on meeting multiple constraints such as the structural strength of the flat panel satellite, the thermal control requirements, the motion envelope of the feed antenna, and the field of view of the star sensor, the method realizes system-level optimization control of the deformation of the mounting surface of the feed antenna by optimizing the installation layout and the on-orbit adjustment strategy, improves the pointing accuracy and working reliability of the antenna, and ensures the stability of the satellite-ground communication link.

[0010] To achieve the above purpose, the present application adopts the following technical solutions:

[0011] The method for optimizing the deformation of the mounting surface of the high-frequency feed antenna of the multi-satellite stacked flat panel satellite comprises the following steps:

[0012] Step S1: coplanarly mounting the first feed antenna and the second feed antenna on the star sensor mounting surface, and the first feed antenna, the second feed antenna, and the star sensor mounting surface are composed of carbon fiber material to reduce the influence of thermal deformation of the structural material as much as possible;

[0013] Step S2: installing the first star sensor on the star sensor mounting surface near the first feed antenna, and installing the third star sensor on the star sensor mounting surface near the second feed antenna;

[0014] Step S3: during the on-orbit operation of the satellite, taking the second star sensor on the star sensor mounting surface as the whole-satellite attitude reference, adjusting the installation matrix of the first star sensor and the third star sensor through mutual calibration between the first star sensor, the second star sensor, and the third star sensor, and the mutual calibration process measures the deformation amount of the first feed antenna, the second feed antenna, and the star sensor mounting surface through mutual verification of the three star sensor optical axes;

[0015] Step S4: After completing the installation matrix adjustment of the first star sensor and the third star sensor, the installation matrix of the first feed antenna is adjusted based on the first star sensor, and the installation matrix of the second feed antenna is adjusted based on the third star sensor.

[0016] Further, in step S1, single-star mechanics simulation and satellite assembly mechanics simulation are performed on the overall structure of the flat plate satellite to ensure that the structural stress values of the installation areas of the first feed antenna and the second feed antenna are less than the allowable stress of the used material.

[0017] Further, in step S1, the temperature field of the flat plate satellite during on-orbit operation is simulated to simulate the temperature fluctuation range of the installation areas of the first feed antenna and the second feed antenna.

[0018] Further, in step S1, a motion envelope model of the first feed antenna and the second feed antenna is constructed to simulate the rotation angle and movement range of the first feed antenna and the second feed antenna during on-orbit operation.

[0019] Further, in step S3, the mutual verification of the starlight axes specifically includes: obtaining star position data observed by the first star sensor, the second star sensor, and the third star sensor at the same time, calculating the included angle deviation between the starlight axes of the star sensors, and correcting the installation matrix parameters of the first star sensor and the third star sensor according to the included angle deviation, so that the measurement errors of the first star sensor and the third star sensor on the deformation of the first feed antenna and the second feed antenna with respect to the star sensor mounting surface are less than a preset value.

[0020] Further, in step S4, adjusting the installation matrix of the first feed antenna and the second feed antenna specifically includes: obtaining the adjusted attitude data of the first star sensor and the third star sensor, establishing a coordinate conversion relationship between the first feed antenna and the first star sensor, and between the second feed antenna and the third star sensor, and correcting the installation matrix of the first feed antenna and the second feed antenna according to the coordinate conversion relationship, so that the pointing accuracy of the first feed antenna and the second feed antenna respectively adapts to the signal transmission and reception requirements of the first feed antenna and the second feed antenna.

[0021] Further, the flat plate satellite is a multi-star stacked structure, including at least two stacked satellite units, each satellite unit being provided with an independent first feed antenna, a second feed antenna, and a star sensor mounting surface, and the first feed antenna and the second feed antenna being mounted on the star sensor mounting surface.

[0022] Further, the method further comprises a fault redundancy control step: when the first star sensor fails, taking the third star sensor as a reference, combining the structural geometric relationship between the first feed antenna and the star sensor mounting surface, adjusting the mounting matrix of the first feed antenna; when the third star sensor fails, taking the first star sensor as a reference, combining the structural geometric relationship between the second feed antenna and the star sensor mounting surface, adjusting the mounting matrix of the second feed antenna, wherein the structural geometric relationship includes a fixed mounting angle between the feed antenna and the star sensor, a relative coordinate offset, and the parameters are pre-stored through ground calibration.

[0023] The application further provides a multi-star stacked flat panel satellite high-frequency band feed antenna mounting surface deformation optimization device, comprising: a star sensor mounting surface arranged on one side of a flat panel satellite and used for coplanar mounting of a feed antenna and a star sensor, wherein the feed antenna comprises a first feed antenna and a second feed antenna, and the star sensor comprises a first star sensor, a third star sensor and a second star sensor; and a high-bearing support column located in a middle region of the flat panel satellite and used for fixedly connecting the star sensor mounting surface and the flat panel satellite.

[0024] Further, the first feed antenna is mounted below the left side of the star sensor mounting surface; the first star sensor is located on one side of the first feed antenna and is at a distance not exceeding a preset distance threshold from the first feed antenna, so as to ensure that the first star sensor can monitor the deformation of the star sensor mounting surface around the first feed antenna in real time; the second feed antenna is mounted below the right side of the star sensor mounting surface; the third star sensor is located on one side of the second feed antenna and is at a distance not exceeding a preset distance threshold from the second feed antenna, so as to ensure that the third star sensor can monitor the deformation of the star sensor mounting surface around the second feed antenna in real time; and the second star sensor is located at one end of the star sensor mounting surface.

[0025] The application ensures that the deformation trends of the two antennas and the star sensor are consistent through coplanar mounting of the feed antennas, and provides a premise for unified calibration of the star sensor; the coplanar mounting of the feed antennas and the star sensor directly links the antenna deformation and the star sensor measurement, and the combination of the two makes the measurement-feedback link of the mounting surface deformation shorter and the error smaller; the mutual calibration of the multiple star sensors provides a high-precision mounting matrix for the first star sensor and B, and solves the problem of inaccurate reference; the nearby star sensor adjustment uses the high-precision reference to correct the pointing deviation of the QV antenna, and the two form a progressive relationship of reference calibration-error correction; the fault redundancy control of the application relies on the multiple star sensor layout (A1, B, A2) formed by the coplanar mounting of the feed antennas and the star sensor, and the coordinate correlation between the star sensors established by the mutual calibration of the multiple star sensors; at the same time, the fault redundancy control also provides reliability guarantee for on-orbit application of the preceding features, and avoids failure of the entire optimization scheme due to failure of a single component.

[0026] In order to more clearly illustrate the structural features and effects of the application, the application will be described in detail below in combination with the drawings and specific embodiments. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 A structure schematic view of a multi-satellite stacked planar satellite high-frequency band feed antenna mounting surface deformation optimization device.

[0028] Figure 2 A flow chart of a multi-satellite stacked planar satellite high-frequency band feed antenna mounting surface deformation optimization method.

[0029] Label description: 1 - planar satellite; 2 - star sensitive mounting surface; 3 - first feed antenna; 4 - first star sensor; 5 - second feed antenna; 6 - third star sensor; 7 - second star sensor; 8 - high bearing pillar. DETAILED DESCRIPTION

[0030] The application will be further described in conjunction with the drawings and related knowledge, and be clearly and completely described. Obviously, the described application is only a part of the embodiments of the application, but not all the embodiments.

[0031] The high-frequency band feed antenna is a special device for receiving high-frequency band signals and transmitting to a satellite in a satellite communication system, and the pointing accuracy directly determines the stability and reliability of the satellite feed link. The deformation of the feed antenna mounting surface is one of the main factors affecting the pointing accuracy of the satellite (especially the planar satellite with a large length-width ratio).

[0032] The purpose of the application is to provide a system-level optimization method and device for the deformation of the mounting surface of the high-frequency band feed antenna of the multi-satellite stacked planar satellite, which optimizes the mounting surface deformation at the system level on the basis of meeting the structural strength, thermal control requirements, feed antenna motion envelope and star sensitive field of view requirements of the planar satellite, so that the feed antenna maintains high pointing accuracy and establishes a stable and reliable feed communication link.

[0033] The application realizes the system-level optimization of the deformation of the mounting surface of the high-frequency band feed antenna of the multi-satellite stacked planar satellite through the cooperation of the special device design and the system-level optimization method, specifically as follows:

[0034] Referring to Figure 1 , Figure 2 , the multi-satellite stacked planar satellite high-frequency band feed antenna mounting surface deformation optimization method includes the following steps:

[0035] Step S1: The feed antenna is co-planarly installed on the basis of meeting the structural strength, thermal control requirements and feed antenna motion envelope of the flat panel satellite 1, fully utilizing the envelope space of the carrier fairing, and the first feed antenna 3 and the second feed antenna 5 are co-planarly installed on the star sensor installation surface 2. The installation position is preferably in the middle region of the long side of the flat panel satellite 1 (a region with smaller structural response), so as to reduce the deformation of the installation surface caused by the mechanical response in the main stage, realize the reference unification of the feed antenna and the star sensor installation surface, and make the deformation trends of the antenna and the star sensor completely synchronized, thereby avoiding the superposition of deformation differences caused by different installation surfaces.

[0036] In the preferred embodiment of the present application, step S1 further comprises:

[0037] The mechanical simulation is performed on the overall structure of the flat panel satellite 1 to ensure that the structural stress values of the installation regions of the first feed antenna 3 and the second feed antenna 5 are less than the allowable stress of the used material, thereby avoiding the risk of structural overload caused by mechanical load in the launch phase in advance, and avoiding permanent deformation of the installation surface or damage to the components; at the same time, the simulation optimization reduces repeated testing of the physical prototype, thereby reducing the research and development cost and the probability of later on-orbit failure.

[0038] Further, the temperature field of the flat panel satellite 1 during on-orbit operation is simulated to simulate the temperature fluctuation range of the installation regions of the first feed antenna 3 and the second feed antenna 5, accurately predict the influence of on-orbit temperature change on the thermal deformation of the installation surface, and provide a basis for subsequent thermal control design; and avoid performance degradation caused by temperature fluctuations exceeding the tolerance range of the components.

[0039] The motion model of the first feed antenna 3 and the second feed antenna 5 is constructed to simulate the rotation angle and movement range of the two during on-orbit operation, so as to check the spatial interference risk in the antenna motion envelope in advance, ensure that there is no component collision under the maximum rotation angle of the antenna in orbit, and at the same time, fully utilize the satellite space layout through the motion model optimization to adapt to the compact design requirements of multi-satellite stacking and improve the satellite load integration.

[0040] Step S2: The first star sensor 4 is installed on the star sensor installation surface on the side of the first feed antenna 3, and the third star sensor 6 is installed on the star sensor installation surface on the side of the second feed antenna 5, so that the first feed antenna and the first star sensor, and the second feed antenna 5 and the third star sensor 6 are on the same star sensor installation surface, and the deformation of the installation surface of the star sensor and the feed antenna is basically kept consistent.

[0041] The layout can ensure that the deformation data measured by the star sensor directly reflects the true state of the installation region of the feed antenna, and the correlation of the deformation measurement is improved compared with separate installation; the single-sided layout avoids signal interference between the star sensor and the feed antenna, shortens the distance between the two, provides conditions for real-time monitoring of deformation, and reduces the delay of deformation response.

[0042] Step S3: Multi-star-sensor on-orbit mutual calibration adjusts the installation matrix of the first star sensor and the third star sensor while the installation matrix satellite is in operation, taking the second star sensor 7 located on the star sensor installation surface as the whole satellite attitude reference, and adjusting the installation matrix of the first star sensor and the third star sensor through mutual calibration among the first star sensor, the second star sensor 7 and the third star sensor. The mutual calibration process is verified by mutual calibration of star sensor optical axes, and the deformation amount of the first feed antenna, the second feed antenna and the star sensor installation surface is accurately measured.

[0043] The second star sensor is installed on the same surface as other star sensors, which can reduce the deformation difference between the reference and the measurement end; the multi-star-sensor mutual calibration can offset the measurement error of a single star sensor, and improve the installation matrix adjustment accuracy.

[0044] In the preferred embodiment of the present application, the mutual calibration of star sensor optical axes specifically includes: obtaining star position data observed by the first star sensor, the second star sensor and the third star sensor at the same time, calculating the angle deviation between the optical axes of the star sensors, and correcting the installation matrix parameters of the first star sensor and the third star sensor according to the angle deviation, so that the measurement error of the deformation amount of the corresponding feed antenna and the star sensor installation surface is less than a preset value. Synchronous star position data ensures the timeliness and consistency of optical axis calibration, and targeted measurement improves the deformation correlation.

[0045] Step S4: After the installation matrix adjustment of the first star sensor and the third star sensor is completed, the installation matrix of the first feed antenna is adjusted based on the first star sensor, and the installation matrix of the second feed antenna is adjusted based on the third star sensor, further reducing the deformation influence caused by different distance star sensors, and correcting the on-orbit pointing error of the feed antenna.

[0046] The near-reference adjustment shortens the link of attitude reference-antenna correction, and targeted adjustment accurately matches the pointing accuracy of the QV antenna and the corresponding feed antenna, fully meeting the signal transmission requirements of the high-frequency band point beam antenna.

[0047] In the preferred embodiment of the present application, the adjustment process specifically includes: obtaining the adjusted attitude data of the first star sensor and the third star sensor, establishing the coordinate conversion relationship between the first feed antenna and the first star sensor, and between the second feed antenna and the third star sensor, and correcting the installation matrix of the QV antenna according to the coordinate conversion relationship, so that the pointing accuracy of the QV antenna is adapted to the signal transmission requirements of the corresponding feed antenna. The coordinate conversion relationship realizes accurate mapping of the attitude data and the antenna adjustment, and avoids link failure caused by reference signal deviation.

[0048] Preferred embodiment: Multi-star stacking adaptation and fault redundancy control

[0049] Multi-satellite stack adaptation: The flat panel satellite is a multi-satellite stack structure, including at least two stacked satellite units, each satellite unit is provided with an independent first feed antenna, a second feed antenna and a star sensor mounting surface, and the first feed antenna and the second feed antenna are mounted on the corresponding star sensor mounting surface. The independent mounting surface design avoids the mechanical coupling and deformation transmission caused by the multi-satellite stack, and the pointing accuracy of the antennas of each satellite unit does not interfere with each other, which is suitable for batch production and rapid networking deployment.

[0050] Fault redundancy control: when the first star sensor fails, the third star sensor is taken as a reference, the structural geometric relationship between the first feed antenna and the star sensor mounting surface is combined, and the installation matrix of the first feed antenna is adjusted; when the third star sensor fails, the first star sensor is taken as a reference, the structural geometric relationship between the second feed antenna and the star sensor mounting surface is combined, and the installation matrix of the second feed antenna is adjusted. The cross-redundancy design avoids the loss of control of the antenna pointing caused by the failure of a single star sensor, the structural geometric relationship provides reliable data support for fault switching, and the on-orbit working reliability of the satellite is greatly improved.

[0051] Referring to Figure 1 The application also provides a multi-satellite stack flat panel satellite high-frequency band feed antenna mounting surface deformation optimization device, which specifically comprises:

[0052] The star sensor mounting surface 2 is arranged on one side of the flat panel satellite 1 and is used for coplanarly mounting the feed antenna and the star sensor. The feed antenna (QV feed antenna) includes the first feed antenna and the second feed antenna, and the star sensor includes the first star sensor, the third star sensor and the second star sensor. The unified installation reference makes the deformation of the feed antenna and the star sensor completely synchronized, and eliminates the measurement error caused by the reference difference; the integrated layout reduces the external protruding components of the satellite, reduces the aerodynamic resistance and the risk of space interference, and simplifies the structural design.

[0053] The high-load support column 8 is located in the middle region of the flat panel satellite and is used for fixedly connecting the star sensor mounting surface 2 and the flat panel satellite 1. The middle region support makes the stress of the star sensor mounting surface uniformly distributed, avoids the non-uniform deformation caused by the edge support, and the high-load design can bear the total weight and mechanical load of the feed antenna and the star sensor, and effectively resists the vibration and impact in the launching stage.

[0054] Further, the first feed antenna is mounted below the left side of the star sensor mounting surface; the first star sensor is located on one side of the first feed antenna and is at a distance not more than a preset distance threshold from the first feed antenna, so that the first star sensor can monitor the deformation of the star sensor mounting surface around the first feed antenna in real time; the second feed antenna is mounted below the right side of the star sensor mounting surface; the third star sensor is located on one side of the second feed antenna and is at a distance not more than a preset distance threshold from the second feed antenna, so that the third star sensor can monitor the deformation of the star sensor mounting surface around the second feed antenna in real time; and the second star sensor is located at one end of the star sensor mounting surface.

[0055] Specifically, such as Figure 1 As shown, based on meeting the requirements of structural strength and thermal control, the first feeding antenna, the first star sensor, the second feeding antenna, and the third star sensor are all installed on both sides of the high-strength support column of the Y-axis of the star structure, and are in the same plane, so as to ensure that the deformation of the mounting surfaces of the feeding antenna and the star sensor is basically the same.

[0056] The first feed antenna and the first star sensor are coplanarly mounted on the X-axis of the high-load-bearing support. While meeting the requirements of the motion envelope of the first feed antenna and the field of view of the first star sensor, the installation position of the first star sensor is as close as possible to the first feed antenna. The second feed antenna and the third star sensor are coplanarly mounted on the X-axis of the high-load-bearing support. While meeting the requirements of the motion envelope of the second feed antenna and the field of view of the third star sensor, the installation position of the third star sensor is as close as possible to the second feed antenna to further reduce the impact of inconsistent deformation caused by the difference in distance between the mounting surfaces of the feed antenna and the star sensor.

[0057] When the satellite is in orbit, the second star sensor is used as the reference (satellite attitude reference). The installation matrix of the first and third star sensors is adjusted through mutual calibration of the first, second, and third star sensors (the deformation of the feed antenna mounting surface can be measured by mutual verification of the star sensor optical axes in orbit). When the first feed antenna is used in orbit, the nearest first star sensor is used as the primary reference to adjust the installation matrix of the first feed antenna, further improving the correction accuracy of the first feed antenna. When the second feed antenna is used in orbit, the nearest third star sensor is used as the primary reference to adjust the installation matrix of the second feed antenna, further improving the correction accuracy of the second feed antenna.

[0058] This invention fully utilizes the launch vehicle fairing envelope space to mount two feed antennas coplanarly at locations with minimal response on the flat-panel satellite, effectively reducing deformation of the feed antenna mounting surface caused by the mechanical response of the active segment of the multi-satellite stacked satellite assembly. Without compromising the performance requirements of the flat-panel satellite, the coplanar mounting of the feed antenna and star sensor significantly optimizes the impact of installation deformation on the feed antenna pointing direction. The coplanar mounting of the feed antenna and corresponding star sensor creates a fault redundancy mechanism; if one star sensor fails, the other can serve as an effective reference, improving the reliability of the feed antenna. Introducing a nearby star sensor as a reference allows for on-orbit adjustment of the QV antenna mounting matrix, further reducing the deformation impact of distance differences and correcting pointing errors. The introduced star sensor serves as both a feed antenna reference and a satellite attitude measurement reference, requiring no additional components, offering strong scalability and high engineering feasibility, meeting the requirements for mass production and rapid network deployment of multi-satellite stacked flat-panel satellites.

[0059] This invention effectively reduces the deformation of the feed antenna mounting surface and significantly improves the pointing accuracy of the feed antenna by using coplanar installation and close proximity layout of the feed antenna and star sensor, as well as on-orbit mutual calibration of multiple star sensors. Fault redundancy design and multi-star stacking adaptation layout enhance system reliability and versatility. Simultaneously, the device has a simple structure, high integration, and standardized process, requiring no additional components, offering strong scalability and high engineering feasibility. It can meet the needs of mass production and rapid network deployment of multi-star stacked flat-panel satellites, providing strong support for the stability and reliability of high-frequency satellite communication links.

[0060] Those skilled in the art should consider the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art, all of which fall within the protection scope of this invention.

Claims

1. A method for deformation optimization of high frequency band feed antenna mounting surface of multi-satellite stacked planar satellite, characterized in that, The method comprises the following steps: Step S1: coplanarly mounting the first feed antenna and the second feed antenna on a star sensor mounting surface, the star sensor mounting surface being located on one side of the flat panel satellite, and the first feed antenna, the second feed antenna and the star sensor mounting surface being made of carbon fiber material; Step S2: mounting a first star sensor on the star sensor mounting surface on the side of the first feed antenna, mounting a third star sensor on the star sensor mounting surface on the side of the second feed antenna, and further mounting a second star sensor on one end of the star sensor mounting surface; Step S3: during on-orbit operation of the satellite, taking the second star sensor located on the star sensor mounting surface as a whole-satellite attitude reference, adjusting the mounting matrix of the first star sensor and the third star sensor through mutual calibration among the first star sensor, the second star sensor and the third star sensor, and measuring the deformation of the first feed antenna, the second feed antenna and the star sensor mounting surface through mutual calibration of star sensor optical axes of the first star sensor, the second star sensor and the third star sensor; Step S4: after the mounting matrix adjustment of the first star sensor and the third star sensor is completed, adjusting the mounting matrix of the first feed antenna with the first star sensor as a reference, and adjusting the mounting matrix of the second feed antenna with the third star sensor as a reference.

2. The multi-satellite stack planar satellite high frequency band feed antenna installation surface deformation optimization method according to claim 1, characterized in that, In step S1, single-satellite mechanics simulation and satellite assembly mechanics simulation are performed on the overall structure of the flat panel satellite, so as to ensure that the structural stress value of the mounting area of the first feed antenna and the second feed antenna is less than the allowable stress of the material used.

3. The method of claim 1, wherein, In step S1, the temperature field of the flat panel satellite during on-orbit operation is simulated, so as to simulate the temperature fluctuation range of the mounting area of the first feed antenna and the second feed antenna.

4. The method of claim 1, wherein, In step S1, a motion envelope model of the first feed antenna and the second feed antenna is constructed, so as to simulate the rotation angle and movement range of the first feed antenna and the second feed antenna during on-orbit operation.

5. The method of claim 1, wherein, In step S3, the mutual calibration of the star sensor optical axes specifically comprises: obtaining star position data observed by the first star sensor, the second star sensor and the third star sensor at the same time, calculating the included angle deviation between the optical axes of the star sensors, correcting the mounting matrix parameters of the first star sensor and the third star sensor according to the included angle deviation, so that the measurement error of the first star sensor and the third star sensor on the deformation of the first feed antenna, the second feed antenna and the star sensor mounting surface is less than a preset value.

6. The method of claim 1, wherein, In step S4, adjusting the mounting matrix of the first feed antenna and the second feed antenna specifically comprises: obtaining the adjusted attitude data of the first star sensor and the third star sensor, establishing the coordinate conversion relationship between the first feed antenna and the first star sensor and between the second feed antenna and the third star sensor, and correcting the mounting matrix of the first feed antenna and the second feed antenna according to the coordinate conversion relationship, so that the pointing accuracy of the first feed antenna and the second feed antenna is adapted to the signal transmission and reception requirement.

7. The method of claim 1, wherein, The flat panel satellite is a multi-satellite stacked structure, comprising at least two stacked satellite units, each satellite unit being provided with an independent first feed antenna, a second feed antenna and a star sensor mounting surface.

8. The method of claim 1, wherein, Further comprising a fault redundancy control step: when the first star sensor fails, taking the third star sensor as a reference, combining the structural geometric relationship between the first feed antenna and the star sensor mounting surface, adjusting the mounting matrix of the first feed antenna; When the third star sensor fails, taking the first star sensor as a reference, combining the structural geometric relationship between the second feed antenna and the star sensor mounting surface, adjusting the mounting matrix of the second feed antenna.

9. An apparatus for implementing the method of claim 1-8 for optimizing the deformation of the high frequency band feed antenna installation surface of a multi-satellite stacked planar satellite, characterized in that, Comprise: A star sensor mounting surface is arranged on one side of the platform satellite and used for coplanar mounting of a feed antenna and a star sensor, wherein the feed antenna comprises a first feed antenna and a second feed antenna, and the star sensor comprises a first star sensor, a third star sensor and a second star sensor; a high-load support column is located in the middle region of the platform satellite and used for fixedly connecting the star sensor mounting surface and the platform satellite.

10. The apparatus of claim 9, wherein, The first star sensor is mounted on the star sensor mounting surface on one side of the first feed antenna, the third star sensor is mounted on the star sensor mounting surface on one side of the second feed antenna, and the star sensor mounting surface is further provided with the second star sensor at one end.

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