Satellite antenna profile precision control method, device and equipment and storage medium

Abstract

This invention provides a method, apparatus, electronic device, and computer-readable storage medium for precision control of satellite antenna profiles, relating to the field of spaceborne satellite technology. The precision control method includes: acquiring the array strain and key coordinates of the satellite antenna profile; inputting the array strain and key coordinates into the array structural mechanical model of the satellite antenna to evaluate the profile deviation coordinates; and performing profile precision control of the satellite antenna based on the profile deviation coordinates. This addresses at least the problems of low efficiency, poor consistency, and lag in precision adjustment in related technologies. It is suitable for antenna offset prediction and control scenarios.

Description

Technical Field

[0001] This invention relates to the field of spaceborne satellite technology, and in particular to a method, apparatus, electronic device, and computer-readable storage medium for precision control of satellite antenna profiles. Background Technology

[0002] With the rapid development of aerospace technology, the performance requirements for satellite antennas in satellite communication and remote sensing missions are increasing. Large-aperture, high-gain deployable satellite antennas have become key equipment to meet these needs. During the satellite launch phase, to accommodate the limited fairing space of the launch vehicle, the antenna needs to be foldable and retractable; after entering orbit, the antenna must be able to deploy smoothly and maintain a high-precision profile to achieve efficient signal transmission and reception. At the same time, the complex and variable space environment, including extreme temperature changes, micrometeoroid impacts, and space radiation, can adversely affect the structure and performance of the antenna.

[0003] Currently, some progress has been made in the control of the antenna profile of deployable satellite antennas. In terms of profile control, some antennas use sensors to monitor antenna deformation and actuators to passively adjust the antenna profile. In addition, some research has attempted to introduce artificial intelligence technology into antenna performance optimization, but most of this is still in the theoretical research or preliminary application stage, and a mature intelligent adaptive control system has not yet been formed.

[0004] In summary, existing mainstream passive adjustment modes (such as ground pre-compensation and material selection optimization) cannot cope with on-orbit dynamic disturbances, have low precision adjustment efficiency and poor consistency, and the sensor-control system has response lag. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to address the above-mentioned shortcomings of the prior art by providing a method, apparatus, electronic device and computer-readable storage medium for precision control of satellite antenna profile, which can achieve efficient and accurate antenna profile control.

[0006] In a first aspect, the present invention provides a method for precision control of satellite antenna profile, comprising: acquiring the array strain and critical coordinates of the satellite antenna; inputting the array strain and critical coordinates into the array structure mechanical model of the satellite antenna to evaluate the profile deviation coordinates of the satellite antenna; and performing profile precision control of the satellite antenna based on the profile deviation coordinates.

[0007] Preferably, before inputting the array strain and key coordinates of the satellite antenna into the array structure mechanical model and evaluating the satellite antenna's profile deviation coordinates, the accuracy control method for the satellite antenna profile further includes: obtaining the target load type of the satellite antenna; performing a working condition simulation of the satellite antenna based on the target load type to solve for the simulated array strain and simulated profile offset of the satellite antenna, wherein the simulated profile offset is used to characterize the displacement deviation between the key coordinates of the profile and the profile deviation coordinates; and constructing the array structure mechanical model of the satellite antenna based on the simulated array strain and simulated profile offset.

[0008] Preferably, the target load type includes at least one of the following: static load, vibration load, temperature load, and impact load. The satellite antenna is simulated based on the target load type to solve for the simulated array surface strain and simulated surface offset of the satellite antenna. Specifically, this includes: obtaining the preset load condition parameters corresponding to the target load type; simulating the satellite antenna according to the load condition parameters to solve for the simulated array surface strain and simulated surface offset of the satellite antenna.

[0009] Preferably, the satellite antenna includes at least one lateral actuator and at least one longitudinal actuator. The surface accuracy control of the satellite antenna based on surface deviation coordinates specifically includes: evaluating the ideal driving voltage of each lateral actuator and each longitudinal actuator based on their respective surface deviation coordinates; calculating the actual driving voltage of each lateral actuator and each longitudinal actuator based on their respective ideal driving voltages; and controlling the surface accuracy of the satellite antenna based on the actual driving voltages.

[0010] Preferably, the ideal driving voltage of each lateral actuator and each longitudinal actuator is evaluated based on the surface deviation coordinates of each lateral actuator and each longitudinal actuator. Specifically, this includes: calculating the offset weight of each lateral actuator and determining the ideal displacement of each lateral actuator by multiplying the offset weight by the surface deviation coordinate of each lateral actuator; determining the surface deviation coordinate of each longitudinal actuator as the ideal displacement of each longitudinal actuator; and calculating the ratio of the ideal displacement of each lateral actuator and each longitudinal actuator to a preset displacement coefficient to obtain the ideal driving voltage of each lateral actuator and each longitudinal actuator.

[0011] Preferably, based on the ideal driving voltage of each lateral actuator and each longitudinal actuator, the actual driving voltage of each lateral actuator and each longitudinal actuator is calculated respectively. Specifically, this includes: evaluating the attenuation coefficient of each lateral actuator and each longitudinal actuator; calculating the ratio of the ideal driving voltage of each lateral actuator and each longitudinal actuator to the attenuation coefficient, and obtaining the actual driving voltage of each lateral actuator and each longitudinal actuator.

[0012] Preferably, the attenuation coefficients of each lateral actuator and each longitudinal actuator are evaluated, specifically including: obtaining the historical actual output displacement and historical actual driving voltage of each lateral actuator and each longitudinal actuator; multiplying the historical actual driving voltage of each lateral actuator and each longitudinal actuator by a preset displacement coefficient to obtain the historical ideal displacement of each lateral actuator and each longitudinal actuator; and calculating the ratio of the historical actual output displacement of each lateral actuator and each longitudinal actuator to its historical ideal displacement to obtain the attenuation coefficient of each lateral actuator and each longitudinal actuator.

[0013] Secondly, the present invention also provides a precision control device for satellite antenna profiles, comprising a first acquisition module, an evaluation module, and a precision control module. The first acquisition module is used to acquire the array strain force and key coordinates of the satellite antenna profile. The evaluation module is used to input the array strain force and key coordinates of the satellite antenna profile into the array structural mechanical model of the satellite antenna and evaluate the profile deviation coordinates of the satellite antenna. The precision control module is used to perform profile precision control on the satellite antenna based on the profile deviation coordinates.

[0014] Thirdly, the present invention also provides an electronic device, including a memory and a processor, wherein the memory stores a computer program, and the processor is configured to run the computer program to implement the precision control method for the satellite antenna profile provided in the first aspect above.

[0015] Fourthly, the present invention also provides a computer-readable storage medium having a computer program stored thereon, wherein when the computer program is executed by a processor, it implements the precision control method for the satellite antenna profile provided in the first aspect.

[0016] This invention provides a method, apparatus, electronic device, and computer-readable storage medium for precision control of satellite antenna profiles. By analyzing the interference mechanism of the space environment through a mechanical model of the satellite antenna array structure, and incorporating the coupling effect of strain and spatial coordinates into deviation calculations, it significantly reduces profile deviation assessment and control errors, improving the profile accuracy of the satellite antenna and thus enhancing signal transmission and reception efficiency. Therefore, this invention enables efficient and accurate antenna profile control. Attached Figure Description

[0017] Figure 1 This is a flowchart of a method for controlling the precision of a satellite antenna profile according to Embodiment 1 of the present invention;

[0018] Figure 2 This is an example diagram of a satellite antenna in Embodiment 1 of the present invention;

[0019] Figure 3 This is an example diagram of the back of the satellite antenna in Embodiment 1 of the present invention;

[0020] Figure 4 This is a schematic diagram of the structure of a satellite antenna profile precision control device according to Embodiment 2 of the present invention. Detailed Implementation

[0021] To enable those skilled in the art to better understand the technical solution of the present invention, the embodiments of the present invention will be further described in detail below with reference to the accompanying drawings.

[0022] It is understood that the specific embodiments and accompanying drawings described herein are merely for explaining the invention and are not intended to limit the invention.

[0023] It is understood that, without conflict, the various embodiments and features in the embodiments of the present invention can be combined with each other.

[0024] It is understood that, for ease of description, only the parts related to the present invention are shown in the accompanying drawings, while the parts unrelated to the present invention are not shown in the drawings.

[0025] It is understood that each unit or module involved in the embodiments of the present invention may correspond to only one entity structure, or may be composed of multiple entity structures, or multiple units or modules may be integrated into one entity structure.

[0026] It is understood that, without conflict, the functions and steps marked in the flowcharts and block diagrams of this invention may occur in a different order than that marked in the accompanying drawings.

[0027] It is understood that the flowcharts and block diagrams of this invention illustrate the possible architecture, functions, and operations of systems, apparatuses, devices, and methods according to various embodiments of this invention. Each block in the flowchart or block diagram may represent a unit, module, program segment, or code, containing executable instructions for implementing the specified function. Furthermore, each block or combination of blocks in the block diagram and flowchart can be implemented using a hardware-based system to achieve the specified function, or using a combination of hardware and computer instructions.

[0028] It is understood that the units and modules involved in the embodiments of the present invention can be implemented by software or by hardware. For example, the units and modules can be located in a processor.

[0029] Example 1:

[0030] like Figure 1 As shown, this embodiment provides a method for precision control of satellite antenna profiles. The method for precision control of satellite antenna profiles includes:

[0031] S101, obtain the array strain and key coordinates of the satellite antenna.

[0032] In this embodiment, the satellite antenna is as follows: Figure 2 or Figure 3 As shown, it includes, but is not limited to: antenna array 1, support frame, drive module, sensing module, and control module. The support frame includes, but is not limited to: support truss 21 and central load-bearing cylinder 22. The drive module includes, but is not limited to: lateral actuator 31, longitudinal actuator 32, and actuator drive circuit. The sensing module includes, but is not limited to: strain sensor. The strain sensor is located near the longitudinal actuator of antenna array 1 and at key stress-bearing parts of support truss 21. The control module is located inside central load-bearing cylinder 22 and is connected to the drive module and sensing module respectively. Therefore, in this embodiment, the strain sensor detects the array strain force of antenna array 1 and the truss strain force of support truss 21 to obtain the array strain force of satellite antenna and send it to the control module. In addition, the control module also obtains the key coordinates of the satellite antenna profile. The key coordinates of the profile refer to the three-dimensional absolute coordinates of key points on the back side of antenna array 1 when it is in the initial installation state before satellite antenna launch.

[0033] It should be noted that the antenna array 1 is fixed to the support truss 21, which is connected in pairs via hinges. The bottom of the support truss 21 is rigidly connected to the central support cylinder 22, and the lower end of the central support cylinder 22 is connected to the satellite body. The sensing module also includes a displacement sensor and a temperature sensor. The displacement sensor is integrated on the lateral actuator 31 and the longitudinal actuator 32 to detect the actual output displacement of the lateral actuator 31 and the longitudinal actuator 32; the temperature sensor is set on the key stress-bearing parts to detect the ambient temperature.

[0034] S102 inputs the array strain and key coordinates of the surface into the array structure mechanical model of the satellite antenna to evaluate the surface deviation coordinates of the satellite antenna.

[0035] In this embodiment, the surface deviation coordinates refer to the difference between the actual position (current three-dimensional coordinates) of the satellite antenna and its designed position (ideal three-dimensional coordinates). After the control module obtains the array strain and key surface coordinates of the satellite antenna, it also receives the operating parameters of the lateral actuator 31 and the longitudinal actuator 32 fed back by the drive module. The array strain, key surface coordinates, and operating parameters are input into the array structure mechanical model of the satellite antenna for integrated analysis to generate the surface deviation coordinates of the lateral actuator 31 and the longitudinal actuator 32. These coordinates are then transmitted to the drive module to drive the lateral actuator 31 and the longitudinal actuator 32 to perform displacement adjustment, maintaining the surface accuracy of the antenna array 1. The operating parameters include, but are not limited to, the drive voltage.

[0036] The array strain, key surface coordinates, and operating parameters are input into the array structure mechanical model of the satellite antenna for integrated analysis to generate the surface deviation coordinates of the transverse actuator 31 and the longitudinal actuator 32. Specifically, this includes: inputting the array strain and operating parameters into the array structure mechanical model of the satellite antenna to predict the surface offset of the satellite antenna; superimposing the surface offset with the key surface coordinates to calculate the current three-dimensional coordinates of the satellite antenna; and calculating the surface deviation coordinates of the satellite antenna based on the current three-dimensional coordinates and the ideal three-dimensional coordinates of the satellite antenna under the current on-orbit operating conditions. In this embodiment, taking the total number of key surface coordinates as M as an example, the surface deviation coordinate ∆X={(∆X_m, ∆Y_m, ∆Z_m)|m=1,…,M}, where ∆X_m, ∆Y_m, and ∆Z_m represent the specific values ​​of the m-th surface deviation coordinate in three different directions. This embodiment utilizes a structural mechanics model of the antenna array combined with real-time array strain to accurately calculate the displacement of key points on the back side of the antenna array. By superimposing these displacements with the key coordinates of the antenna array and comparing them with the ideal three-dimensional coordinates, the shape deviation coordinates of each key point on the back side of the antenna array can be accurately obtained. This provides crucial deviation quantification data for the precision control of the antenna array shape, which in turn drives the lateral and longitudinal actuators to directionally adjust the antenna array shape. This corrects local deviations in the antenna array shape and significantly improves the targeting and effectiveness of the shape control.

[0037] It should be noted that the current three-dimensional coordinates refer to the actual position coordinates under real-world operating conditions (such as load, temperature changes, and material deformation). Ideal three-dimensional coordinates refer to the antenna's position in a perfectly unbiased state, typically determined based on the antenna's design parameters and performance requirements.

[0038] Optionally, in S102: before inputting the array strain and key coordinates of the antenna profile into the array structure mechanical model of the satellite antenna to evaluate the antenna profile deviation coordinates, the accuracy control method for the satellite antenna profile also includes:

[0039] S104, Obtain the target payload type of the satellite antenna.

[0040] Specifically, the target load type includes at least one of the following: static load, vibration load, temperature load, and impact load.

[0041] In this embodiment, load type refers to the category of loads that the satellite antenna may experience throughout its entire lifecycle (from ground manufacturing, transportation, launch to on-orbit operation) and that have a significant impact on structural strength and stability. Static loads refer to loads acting on the antenna structure in a static state, typically caused by gravity, static pressure, or other constant forces; they are constant over time and do not change. Vibration loads refer to loads caused by mechanical vibration or other dynamic factors; they are typically periodic and may be caused by launch, operation, or external environments (such as wind or earthquakes); vibration loads can affect the fatigue and stability of the antenna structure. Temperature loads refer to stress and deformation caused by temperature changes; satellites experience extreme temperature changes in orbit, leading to material expansion and contraction, thus generating temperature loads. Impact loads refer to high-intensity loads applied over a short period, typically caused by sudden external events (such as vibrations, collisions, or other transient events during launch); their duration is short, but their intensity can be very high. Therefore, this embodiment determines one or more target load types that the satellite antenna may be affected by by considering the satellite antenna's communication workload, power consumption, duration, and operating conditions.

[0042] S105, perform working condition simulation of satellite antenna based on target load type, and solve for the simulated array surface strain and simulated surface offset of satellite antenna. The simulated surface offset is used to characterize the displacement deviation between the key coordinates of the surface and the deviation coordinates of the surface.

[0043] In this embodiment, the stress distribution of the satellite antenna structure under the target load type corresponding to the working conditions (such as gravity, wind load, vibration, temperature change, actuator driving force) is simulated by the Finite Element Analysis (FEA) simulation tool. The stress peak area and the key force transmission node, i.e. the key stress part, can be directly located, and the simulated array surface strain and simulated surface offset of the satellite antenna can be solved.

[0044] Specifically, S105: Perform a working condition simulation of the satellite antenna based on the target load type, and solve for the simulated array surface strain and simulated profile offset of the satellite antenna, including steps S1051-S1052:

[0045] S1051, Obtain the preset load condition parameters corresponding to the target load type.

[0046] S1052, based on the load conditions, the satellite antenna is simulated to solve for the simulated array surface strain and simulated surface offset.

[0047] In this embodiment, the corresponding load condition parameters are designed based on the target load type. The satellite antenna under the load condition parameters is simulated using finite element analysis simulation tools, and the simulated array surface strain and simulated key point displacement of the satellite antenna under the load condition parameters are detected.

[0048] It should be noted that when simulating a satellite antenna under load conditions, the structural design parameters of the satellite antenna should also be consistent. These structural design parameters include, but are not limited to: material property parameters, component geometric dimension parameters, connection constraint parameters between components, sensor arrangement parameters, and actuator arrangement parameters.

[0049] S106. Based on the simulated array strain and simulated surface offset, a mechanical model of the satellite antenna array structure is constructed.

[0050] In this embodiment, a mapping relationship is established between multiple load condition parameters, simulated array strain, and simulated surface offset, thus constructing a mechanical model of the satellite antenna array structure. In addition, before satellite launch, this embodiment divides several typical on-orbit conditions based on the full life cycle of the satellite antenna structure. For each typical on-orbit condition, electromagnetic simulation is performed to determine the ideal beam performance that the satellite antenna structure needs to achieve under that condition. Combined with the key coordinates of the simulated surface and the simulated surface offset, the three-dimensional coordinates of the satellite antenna that can meet the ideal beam performance are derived, which correspond to the ideal three-dimensional coordinates under the typical on-orbit conditions.

[0051] It should be noted that this embodiment also calculates the strain error rate based on the actual and simulated surface strain, and the offset error rate based on the simulated and actual surface offsets. It then determines whether the strain error rate is greater than or equal to a strain error threshold, and whether the offset error rate is greater than or equal to a offset error threshold. If both the strain error rate and offset error rate are less than the strain error threshold, the surface structural mechanical model is not optimized. If both the strain error rate and offset error rate are greater than or equal to the strain error threshold and the displacement error rate is greater than or equal to the displacement error threshold, the surface structural mechanical model is corrected and optimized based on the actual surface strain and actual key point displacements. The strain error threshold ranges from 1% to 3%, and the offset error threshold ranges from 0.5% to 2%. This embodiment uses a strain error threshold of 2% and an offset error threshold of 1% as an example. This embodiment captures the stress changes of the antenna array structure in real time under the real-time on-orbit environment and updates the displacement deviation data of key points on the back side. This enables dynamic closed-loop correction of the antenna array surface accuracy, greatly improving control robustness and ensuring the communication and detection performance of the satellite antenna structure during on-orbit operation.

[0052] S103 controls the surface accuracy of the satellite antenna based on the surface deviation coordinates.

[0053] Specifically, the satellite antenna includes at least one lateral actuator and at least one longitudinal actuator.

[0054] In this embodiment, both the lateral actuator 31 and the longitudinal actuator have bidirectional displacement output capability. One end of the lateral actuator 31 is connected to the support truss 21, and the other end is connected to the central load-bearing cylinder 22. The lateral actuator 31 is used to output horizontal displacement to correct in-plane deformation. One end of the longitudinal actuator 32 is fixed to the support truss 21, and the other end is connected to the reinforcing rib on the back of the antenna array 1. The longitudinal actuator 32 is used to output vertical displacement to correct out-of-plane deformation. The actuator drive circuit is located in the circuit compartment on the side of the central load-bearing cylinder 22 and is used to provide drive voltage for the lateral actuator 31 and the longitudinal actuator 32. This embodiment takes four lateral actuators 31 and one longitudinal actuator 32 at each of the four corners of the back of each antenna array as an example.

[0055] Specifically, S103: Control the surface accuracy of the satellite antenna based on the surface deviation coordinates, including steps S1031-S1033:

[0056] S1031, based on the surface deviation coordinates of each lateral actuator and each longitudinal actuator, evaluate the ideal drive voltage of each lateral actuator and each longitudinal actuator respectively.

[0057] In this embodiment, the surface deviation coordinates of the lateral actuator refer to the values ​​in the lateral direction (usually the X and Y directions) related to the surface deviation of the satellite antenna, and the surface deviation coordinates of the longitudinal actuator refer to the values ​​in the longitudinal direction (usually the Z direction) related to the surface deviation of the satellite antenna. Taking the m-th surface deviation coordinate (∆X_m, ∆Y_m, ∆Z_m) of the satellite antenna as an example, the surface deviation coordinates of the lateral actuator are (∆X_m, ∆Y_m), and the surface deviation coordinates of the longitudinal actuator are ∆Z_m. The ideal driving voltage refers to the voltage value theoretically required for the lateral and longitudinal actuators of the satellite antenna to reach their designed positions or ideal surface deviation coordinates.

[0058] Specifically, S1031: Based on the surface deviation coordinates of each lateral actuator and each longitudinal actuator, the ideal driving voltage of each lateral actuator and each longitudinal actuator is evaluated, including: calculating the offset weight of each lateral actuator, and determining the ideal displacement of each lateral actuator by multiplying the offset weight by the surface deviation coordinate of each lateral actuator; determining the surface deviation coordinate of each longitudinal actuator as the ideal displacement of each longitudinal actuator; calculating the ratio of the ideal displacement of each lateral actuator and each longitudinal actuator to a preset displacement coefficient, and obtaining the ideal driving voltage of each lateral actuator and each longitudinal actuator.

[0059] In this embodiment, because the strain sensor is arranged close to the longitudinal actuator, it can accurately feed back the out-of-plane deformation corresponding to the key points on the back side. Therefore, the surface deviation coordinates of a single longitudinal actuator 32 are accurately measured. That is, its corresponding ideal displacement, for example: the first Ideal displacement of the longitudinal actuator 32 and the ideal displacement Enter formula The first one can be calculated. The ideal drive voltage for a longitudinal actuator, where... This indicates the preset displacement coefficient.

[0060] Calculating the ideal displacement of a lateral actuator requires considering the mutual influence between lateral actuators within the antenna array area covered by the same support truss segment. Therefore, for each lateral actuator within the antenna array area covered by the same support truss segment, an offset weight needs to be assigned to the surface deviation coordinates of the lateral actuator in order to calculate a more accurate ideal displacement. For example: Let the first... The corresponding area of ​​each lateral actuator Inside The first lateral actuator, the... There are one lateral actuator For each surface deviation coordinate, then according to the formula Calculate the first Offset weight of each lateral actuator ,in, , Indicates the first The first lateral actuator The coordinates of the surface deviation are then used to calculate the first surface deviation coordinate. Ideal displacement of a lateral actuator Similarly, in the first... Calculation of the ideal drive voltage for the first longitudinal actuator, the first Ideal drive voltage for a lateral actuator .

[0061] S1032, based on the ideal drive voltage of each lateral actuator and each longitudinal actuator, calculate the actual drive voltage of each lateral actuator and each longitudinal actuator respectively.

[0062] In this embodiment, the actual driving voltage refers to the voltage value actually supplied to the lateral actuator and the longitudinal actuator in actual operation, after taking into account all non-ideal factors.

[0063] Specifically, S1032: Based on the ideal driving voltage of each lateral actuator and each longitudinal actuator, calculate the actual driving voltage of each lateral actuator and each longitudinal actuator, including: evaluating the attenuation coefficient of each lateral actuator and each longitudinal actuator; calculating the ratio of the ideal driving voltage of each lateral actuator and each longitudinal actuator to the attenuation coefficient, and obtaining the actual driving voltage of each lateral actuator and each longitudinal actuator.

[0064] In this embodiment, the damping coefficient of the actuator is determined according to the formula... and formula Calculate the actual driving voltages of the m-th lateral actuator and the m-th longitudinal actuator, where, Let be the attenuation coefficient of the m-th longitudinal actuator. Let be the attenuation coefficient of the b-th lateral actuator. This embodiment considers the actual situation of actuator thrust attenuation and introduces actuator attenuation coefficients for both lateral and longitudinal actuators. The actual displacement adjustment is calculated with the goal of minimizing surface deviation, and the actuators are driven to form a closed-loop control. This avoids the problem of insufficient output displacement leading to increased surface deviation after the performance of the lateral and longitudinal actuators degrades. It effectively solves the problem of decreased surface accuracy caused by actuator performance degradation throughout the antenna's lifespan, ensuring the antenna's high-precision performance in orbit for extended periods.

[0065] Specifically, the attenuation coefficients of each lateral actuator and each longitudinal actuator are evaluated, including: obtaining the historical actual output displacement and historical actual driving voltage of each lateral actuator and each longitudinal actuator; multiplying the historical actual driving voltage of each lateral actuator and each longitudinal actuator by a preset displacement coefficient to obtain the historical ideal displacement of each lateral actuator and each longitudinal actuator; and calculating the ratio of the historical actual output displacement of each lateral actuator and each longitudinal actuator to its historical ideal displacement to obtain the attenuation coefficient of each lateral actuator and each longitudinal actuator.

[0066] In this embodiment, the historical actual output displacement of the lateral actuator or the longitudinal actuator is used. and historical actual driving voltage Enter formula Calculate the attenuation coefficient of the lateral or longitudinal actuator. The displacement coefficient can be determined by several experiments (applying a series of driving voltages to a single actuator, measuring the ideal displacement under no-load and no-loss conditions corresponding to the driving voltage, and performing a linear fitting of the ideal displacement and the driving voltage, with the slope of the line being the displacement coefficient k).

[0067] S1033 controls the surface accuracy of the satellite antenna based on the actual driving voltage.

[0068] It should be noted that when there is a deviation in the shape of the antenna array in a local area, the shape can also be adjusted locally by using the lateral actuator and the longitudinal actuator.

[0069] This embodiment provides a method for precision control of satellite antenna profiles. By analyzing the mechanical model of the satellite antenna array structure, the mechanism of interference from the space environment is analyzed. The coupling effect of strain and spatial coordinates is incorporated into the deviation calculation, which significantly reduces the profile deviation assessment error and control error, improves the profile precision of the satellite antenna, thereby improving signal transmission and reception efficiency and achieving efficient and accurate antenna profile control.

[0070] Example 2:

[0071] like Figure 4 As shown, this embodiment provides a precision control device for satellite antenna profiles, including a first acquisition module 41, an evaluation module 42, and a precision control module 43. The first acquisition module 41 is used to acquire the array strain and key coordinates of the satellite antenna profile. The evaluation module 42 is used to input the array strain and key coordinates of the satellite antenna profile into the array structure mechanical model of the satellite antenna and evaluate the profile deviation coordinates of the satellite antenna. The precision control module 43 is used to perform profile precision control on the satellite antenna based on the profile deviation coordinates.

[0072] Optionally, the precision control device for the satellite antenna profile further includes: a second acquisition module 44, a simulation module 45, and a construction module 46. The second acquisition module 44 is used to acquire the target load type of the satellite antenna. The simulation module 45 is used to perform working condition simulation of the satellite antenna based on the target load type, and solve for the simulated array strain and simulated profile offset of the satellite antenna. The simulated profile offset is used to characterize the displacement deviation between the key coordinates of the profile and the deviation coordinates of the profile. The construction module 46 is used to construct the array structure mechanical model of the satellite antenna based on the simulated array strain and simulated profile offset.

[0073] Specifically, the simulation module 45 includes: an acquisition unit 451 and a simulation unit 452. The acquisition unit 451 is used to acquire preset load condition parameters corresponding to the target load type. The simulation unit 452 is used to simulate the satellite antenna according to the load condition parameters and solve for the simulated array surface strain and simulated surface offset of the satellite antenna.

[0074] Specifically, the precision control module 43 includes: an evaluation unit 431, a calculation unit 432, and a precision control unit 433. The evaluation unit 431 is used to evaluate the ideal driving voltage of each lateral actuator and each longitudinal actuator based on the surface deviation coordinates of each lateral actuator and each longitudinal actuator. The calculation unit 432 is used to calculate the actual driving voltage of each lateral actuator and each longitudinal actuator based on the ideal driving voltage of each lateral actuator and each longitudinal actuator. The precision control unit 433 is used to perform surface precision control of the satellite antenna based on the actual driving voltage.

[0075] Specifically, the evaluation unit 431 includes: a first calculation subunit, a determination subunit, and a second calculation subunit. The first calculation subunit is used to calculate the offset weight of each lateral actuator and determine the ideal displacement of each lateral actuator by multiplying the offset weight by the profile deviation coordinate of each lateral actuator. The determination subunit is used to determine the profile deviation coordinate of each longitudinal actuator as the ideal displacement of each longitudinal actuator. The second calculation subunit is used to calculate the ratio of the ideal displacement of each lateral actuator and each longitudinal actuator to a preset displacement coefficient to obtain the ideal driving voltage of each lateral actuator and each longitudinal actuator.

[0076] Specifically, the calculation unit 432 includes an evaluation subunit and a third calculation subunit. The evaluation subunit is used to evaluate the attenuation coefficient of each lateral actuator and each longitudinal actuator. The third calculation subunit is used to calculate the ratio of the ideal driving voltage of each lateral actuator and each longitudinal actuator to the attenuation coefficient, so as to obtain the actual driving voltage of each lateral actuator and each longitudinal actuator.

[0077] Specifically, the evaluation subunit includes: an acquisition minimum unit, a product minimum unit, and a calculation minimum unit. The acquisition minimum unit is used to acquire the historical actual output displacement and historical actual driving voltage of each lateral actuator and each longitudinal actuator. The product minimum unit is used to multiply the historical actual driving voltage of each lateral actuator and each longitudinal actuator by a preset displacement coefficient to obtain the historical ideal displacement of each lateral actuator and each longitudinal actuator. The calculation minimum unit is used to calculate the ratio of the historical actual output displacement of each lateral actuator and each longitudinal actuator to its historical ideal displacement to obtain the attenuation coefficient of each lateral actuator and each longitudinal actuator.

[0078] Understandably, the satellite antenna profile precision control device provided above executes the satellite antenna profile precision control method corresponding to Embodiment 1 provided above. Therefore, the beneficial effects it can achieve can be referred to the beneficial effects of the scheme corresponding to the satellite antenna profile precision control method of Embodiment 1 above, which will not be repeated here.

[0079] Example 3:

[0080] This embodiment also provides an electronic device, including a memory and a processor. The memory stores a computer program, and the processor is configured to run the computer program to implement the precision control method for the satellite antenna profile in Embodiment 1 above.

[0081] Example 4:

[0082] This embodiment also provides a computer-readable storage medium storing a computer program thereon. When the computer program is executed by a processor, it implements the precision control method for the satellite antenna profile in Embodiment 1 above.

[0083] It is understood that the above embodiments are merely exemplary implementations used to illustrate the principles of the present invention, and the present invention is not limited thereto. For those skilled in the art, various modifications and improvements can be made without departing from the spirit and essence of the present invention, and these modifications and improvements are also considered to be within the scope of protection of the present invention.

Claims

1. A method for precision control of satellite antenna profile, characterized in that, include: Obtain the array strain and key coordinates of the satellite antenna. By inputting the array strain and key surface coordinates into the array structure mechanical model of the satellite antenna, the surface deviation coordinates of the satellite antenna are evaluated. The satellite antenna's profile accuracy is controlled based on the profile deviation coordinates.

2. The method for controlling the precision of satellite antenna profile according to claim 1, characterized in that, Before inputting the array strain and key surface coordinates into the array structure mechanical model of the satellite antenna to evaluate the surface deviation coordinates of the satellite antenna, the following steps are also included: Obtain the target payload type of the satellite antenna; The satellite antenna is subjected to working condition simulation based on target load type. The simulated array surface strain and simulated surface offset of the satellite antenna are solved. The simulated surface offset is used to characterize the displacement deviation between the key coordinates of the surface and the deviation coordinates of the surface. Based on the simulated array strain and simulated surface offset, a structural mechanical model of the satellite antenna array is constructed.

3. The method for controlling the precision of satellite antenna profile according to claim 2, characterized in that, The target load type includes at least one of the following: static load, vibration load, temperature load, and impact load. The aforementioned simulation of the satellite antenna based on the target load type, and the determination of the simulated array surface strain and simulated surface offset, specifically includes: Obtain the preset load condition parameters corresponding to the target load type; The satellite antenna is simulated based on the load conditions to solve for the simulated array surface strain and simulated surface offset.

4. The method for controlling the precision of satellite antenna profile according to claim 1, characterized in that, The satellite antenna includes at least one lateral actuator and at least one longitudinal actuator. The method of controlling the surface accuracy of the satellite antenna based on the surface deviation coordinates specifically includes: Based on the surface deviation coordinates of each lateral actuator and each longitudinal actuator, the ideal driving voltage of each lateral actuator and each longitudinal actuator is evaluated respectively. Based on the ideal driving voltage of each lateral actuator and each longitudinal actuator, the actual driving voltage of each lateral actuator and each longitudinal actuator is calculated respectively. The satellite antenna's profile accuracy is controlled based on the actual driving voltage.

5. The method for controlling the precision of satellite antenna profile according to claim 4, characterized in that, The process of evaluating the ideal drive voltage for each lateral and longitudinal actuator based on the surface deviation coordinates of each actuator includes: Calculate the offset weight of each lateral actuator, and determine the ideal displacement of each lateral actuator by multiplying the offset weight by the surface deviation coordinate of each lateral actuator. The surface deviation coordinates of each longitudinal actuator are determined as the ideal displacement of each longitudinal actuator; Calculate the ratio of the ideal displacement of each lateral actuator and each longitudinal actuator to the preset displacement coefficient to obtain the ideal driving voltage of each lateral actuator and each longitudinal actuator.

6. The method for controlling the accuracy of satellite antenna profile according to claim 4, characterized in that, The step of calculating the actual driving voltage of each lateral actuator and each longitudinal actuator based on the ideal driving voltage of each lateral actuator and each longitudinal actuator specifically includes: The attenuation coefficients of each lateral actuator and each longitudinal actuator were evaluated. Calculate the ratio of the ideal driving voltage to the attenuation coefficient for each lateral actuator and each longitudinal actuator to obtain the actual driving voltage for each lateral actuator and each longitudinal actuator.

7. The method for controlling the accuracy of satellite antenna profile according to claim 6, characterized in that, The evaluation of the attenuation coefficients of each lateral actuator and each longitudinal actuator specifically includes: Obtain the historical actual output displacement and historical actual drive voltage of each lateral actuator and each longitudinal actuator; The historical actual driving voltage of each lateral actuator and each longitudinal actuator is multiplied by the preset displacement coefficient to obtain the historical ideal displacement of each lateral actuator and each longitudinal actuator. Calculate the ratio of the historical actual output displacement of each lateral actuator and each longitudinal actuator to its historical ideal displacement to obtain the attenuation coefficient of each lateral actuator and each longitudinal actuator.

8. A precision control device for the shape of a satellite antenna, characterized in that, It includes a first acquisition module, an evaluation module, and a precision control module. The first acquisition module is used to acquire the array strain and key coordinates of the satellite antenna. The evaluation module is used to input the array strain and key surface coordinates into the satellite antenna's array structural mechanical model to evaluate the satellite antenna's surface deviation coordinates. The precision control module is used to control the surface precision of the satellite antenna based on the surface deviation coordinates.

9. An electronic device, characterized in that, The device includes a memory and a processor, wherein the memory stores a computer program and the processor is configured to run the computer program to implement a precision control method for a satellite antenna profile as described in any one of claims 1 to 7.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements a method for precision control of satellite antenna profile as described in any one of claims 1 to 7.

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