On-orbit assembly antenna module profile precision adjustment method, system and equipment based on active actuator layout determination criterion and storage medium
Through the method of determining criteria based on the layout of active actuators in the rail assembly antenna, the module position and active actuators distribution are analyzed, the adjustment sequence is determined and the adjustment amount is calculated, the problem of antenna pattern accuracy adjustment is solved, and more efficient adjustment effect is achieved and lower cost and energy consumption is achieved.
Patent Information
- Application Number
- CN202411647057.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-18
- Publication Date
- 2025-03-11
AI Technical Summary
The profile accuracy adjustment of the on-rail assembly antenna is limited by the layout and number of active actuators, resulting in a decrease in adjustment accuracy, an increase in manufacturing cost and an increase in energy consumption.
By a method of determining criteria based on the active actuator layout, the module position and number and distribution of active actuators are analyzed, the adjustment sequence is determined, and the length and angle adjustment amount of the active actuator are calculated to minimize the number of active actuators and improve the profile accuracy.
It significantly reduces the proportion of active actuators, reduces hardware investment and energy consumption, improves the profile accuracy of the antenna, and shortens the adjustment time.
Smart Images
Figure CN119598728A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the field of profile precision adjustment of on-orbit assembled antenna modules, and in particular to a profile precision adjustment method, system, device and storage medium for on-orbit assembled antenna modules based on active actuator layout determination criteria. Background Art
[0002] In-orbit assembled antennas have the advantages of large caliber and high flexibility, and have become the focus of spacecraft technology research in recent years.
[0003] The on-orbit assembled antenna consists of multiple identical modules and actuators connecting the modules. The actuators include active actuators and passive actuators. During the manufacturing and assembly stages, due to the influence of inevitable random errors, each module deviates from the ideal position, and the surface accuracy of the antenna decreases. In order to improve the surface accuracy, it is necessary to adjust the length and angle of the active actuator to make the module as close to the ideal position as possible. The modules are connected and coupled to each other through actuators. When the active actuator connected to a module is adjusted, the position of the module on the other side of the actuator will be affected. The mutual influence of the modules makes it difficult to adjust the antenna surface accuracy.
[0004] Compared with passive actuators, active actuators have a more complex structure and consume power when actuated. If active actuators are used, it will cause weight and structural redundancy on the one hand, and increase the power demand of the antenna on the other hand. The layout of the active actuator affects the effect of adjusting the antenna profile accuracy.
[0005] In order to realize the on-orbit assembly of antenna modules and achieve good adjustment effects, while considering the impact of manufacturing costs and energy consumption, it is necessary to study new antenna adjustment methods, clarify the module adjustment sequence and the layout of active actuators, calculate the length and angle adjustment of the active actuators, and use as few active actuators as possible to achieve the adjustment of each antenna module. Summary of the invention
[0006] In response to the problems mentioned in the prior art, the present invention proposes a method, system, device and storage medium for adjusting the profile accuracy of an on-orbit assembled antenna module based on the active actuator layout determination criteria, which can clarify the distribution and number of active actuators, adjust the antenna module in a certain order, and improve the antenna profile accuracy.
[0007] In order to achieve the above object, the present invention adopts the following technical solution: The present invention provides a method for adjusting the profile accuracy of an on-orbit assembled antenna module based on an active actuator layout determination criterion, comprising the following steps: S1. Analyze the module positions and the number and distribution of active actuators between modules based on the mathematical model of the on-orbit assembled antenna; S2. Obtain the module coordinates of the physical antenna, take the central module as the reference, and select any inner module in sequence to start adjustment; S3, calculating the adjustment target position of the module to be adjusted, and calculating the length adjustment amount and angle adjustment amount of the active actuator of the module according to the adjustment target position; S4. Repeat step S3 to adjust each module in the physical antenna to obtain the surface accuracy of the adjusted physical antenna.
[0008] As a further improvement of the present invention, the specific process of step S1 is: Determine the position of the current module, and obtain the displacement matrix and angle change matrix of the adjacent module according to the length change and angle change of the actuator between the current module and the adjacent module; By analyzing the rank of the displacement matrix, we can find that the three active actuators between the current module and the adjacent modules are used to adjust the length; By analyzing the rank of the angle variation matrix, it is found that the two active actuators between the current module and the adjacent module are used to adjust the angle; Minimize the number of active actuators based on the distribution of modules.
[0009] As a further improvement of the present invention, the displacement matrix of adjacent modules is:
[0010] Where: is the component of the direction vector of the actuator; is the length change of the actuator; The angle variation matrix is:
[0011] Where: The adjacent surface of the inner ring module is The plane is perpendicular to the surface and points to the direction of the outer ring module. axis, , Indicates the actuator The change in the direction vector Towards and Projection of the surface.
[0012] As a further improvement of the present invention, the process of minimizing the number of active actuators is: According to the number of adjacent edges between the outer module and the inner module, the outer modules are divided into the first type of outer modules and the second type of outer modules; The first type of outer layer module selects three actuators as active actuators; The second type of outer module selects three actuators as active actuators.
[0013] As a further improvement of the present invention, the specific process of step S3 is: S31, obtaining the actual node coordinates of the module to be adjusted, solving the optimal offset distance of the module to be adjusted by the least square method, and obtaining the target node coordinates of the module to be adjusted; S32, obtaining the target node coordinates of the inner ring module adjacent to the module to be adjusted, calculating the adjustment amount of the active actuator according to the target node coordinates of the module to be adjusted, the actual node coordinates and the target node coordinates of the inner ring module, and completing the adjustment of the module to be adjusted.
[0014] As a further improvement of the present invention, the adjustment amount of the active actuator calculated in step S32 is specifically:
[0015] Where: The length adjustment amount of the main actuator; The direction vector of the active actuator before adjustment; is the direction vector after the active actuator is adjusted;
[0016] Where: Active actuator The amount of angle adjustment of the surface; represents the solution of the vector inner product, Indicates the modulus length of the corresponding vector to be solved;
[0017] Where: Active actuator The amount of angle adjustment of the surface; represents the solution of the vector inner product, It means to solve the modulus length of the corresponding vector.
[0018] As a further improvement of the present invention, the adjusted surface accuracy obtained in step S4 is verified, and the initial surface accuracy is compared with the adjusted surface accuracy. If the adjusted surface accuracy is less than the initial surface accuracy, the surface accuracy adjustment of the on-orbit assembled antenna module is completed.
[0019] A system for adjusting the profile accuracy of an on-orbit assembled antenna module based on an active actuator layout determination criterion, comprising: Analysis module, which analyzes the module positions and the number and distribution of active actuators between modules based on the mathematical model of the on-orbit assembled antenna; Get the module, get the module coordinates of the physical antenna, take the central module as the reference, and select any inner module in sequence to start adjustment; The first adjustment module calculates the adjustment target position of the module to be adjusted, and calculates the length adjustment amount and angle adjustment amount of the active actuator of the module according to the adjustment target position; The second adjustment module repeats step S3 to adjust each module in the physical antenna to obtain the surface accuracy of the adjusted physical antenna.
[0020] A device for adjusting the profile accuracy of an antenna module assembled on-orbit based on the active actuator layout determination criteria, characterized in that it includes a processor and a memory, wherein when the processor executes a computer program stored in the memory, it implements the method for adjusting the profile accuracy of an antenna module assembled on-orbit based on the active actuator layout determination criteria as described above.
[0021] A computer-readable storage medium is used to store a computer program, wherein when the computer program is executed by a processor, the method for adjusting the profile accuracy of an on-orbit assembled antenna module based on an active actuator layout determination criterion as described above is implemented.
[0022] Compared with the prior art, the present invention has achieved the following technical effects: In response to the problems caused by the excessive number of active actuators between on-orbit assembled antenna modules, such as reduced adjustment accuracy, soaring manufacturing costs and high energy consumption, the present invention provides a module position determination criterion, and gives a calculation formula for the module position when the actuator has length and angle changes, and constructs it in a matrix form. Through matrix analysis, the minimum number of actuators required to implement length adjustment and angle adjustment can be determined, which significantly reduces the proportion of active actuators in the actuators. Not only does it reduce the hardware investment, but it also greatly shortens the adjustment time, and the manufacturing cost and energy consumption are also reduced, thereby achieving optimization effects in many aspects.
[0023] In view of the fact that each module may not be adjusted to the target position by relying on the length adjustment of the active actuator, the present invention provides a strategy to select some actuators in the active actuator that performs active length adjustment to perform angle adjustment, and comprehensively adjust the length and angle so that the module can be accurately adjusted to the target position, thereby achieving more accurate module positioning. BRIEF DESCRIPTION OF THE DRAWINGS
[0024] Figure 1 It is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the antenna module sub-rings assembled on-orbit according to the present invention; Figure 3 It is a schematic diagram of the layout of the actuators between the antenna module units assembled on-orbit according to the present invention; Figure 4 It is a schematic diagram of the local coordinate system between modules of the present invention; Figure 5This is a schematic diagram of the connection relationship between the actuators of the upper units of the first type of outer module of the on-orbit assembled antenna of the present invention; Figure 6 A schematic diagram of the connection relationship between the actuators of the upper units of the second type of outer module of the on-orbit assembled antenna of the present invention; Figure 7 It is a schematic diagram of the layout of active and passive actuators between adjacent modules of the present invention; Figure 8 A schematic diagram of the adjustment sequence of the on-orbit assembly antenna module of the present invention; Fig. 9 This is a schematic diagram of the layout of the upper active actuator of the on-orbit assembled antenna module of the present invention; Fig.10 This is a schematic diagram of the layout of the lower active actuator of the on-orbit assembled antenna module of the present invention; Fig.11 Schematic diagram of the actual profile and the best approximation profile of the present invention; Fig.12 Adjust the flow chart for the module of the present invention; Fig.13 This is the error cloud diagram of each module of the on-orbit assembled antenna before adjustment; Fig.14 This is the error cloud diagram of each module of the on-orbit assembled antenna after adjustment by the present invention. DETAILED DESCRIPTION
[0025] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.
[0026] The present invention will be further explained below with reference to the accompanying drawings and specific embodiments: Step 1: According to the mathematical model of the on-orbit assembly antenna, except for the central module, the modules are layered from the inside to the outside, and the modules are connected by actuators. The actuators can provide angle changes in two planes and length changes along the actuator direction. The position of the adjacent module is determined by the position of the current module and the connected actuator. Length With direction If the current module position is determined, the actuator length change is considered first. , calculate a point on the adjacent module Displacement : (1) Where: Represents the components of the actuator's direction vector.
[0027] Consider an actuator with a hinge between two modules There is a change in direction , calculate the adjacent modules in and The angle through which the face is rotated is: (2) Where: The adjacent surface of the inner ring module is The plane is perpendicular to the surface and points to the direction of the outer ring module. axis, , Indicates the actuator The change in the direction vector Towards and Projection of the surface.
[0028] Step 2: Analyze the rank of formula (1), the matrix Any row in represents the component of the actuator direction vector in a certain direction, which cannot be eliminated, so the matrix Rank With the augmented matrix Rank satisfy: (3) Therefore, the formula (3) is satisfied. If there is more than one group, and all four actuators are active actuators, precise adjustment cannot be achieved. Therefore, three of them are selected as active actuators for active length adjustment, and the remaining one is a passive actuator without active length adjustment. Formula (1) is rewritten as: (4) Step 3: Analyze the rank of formula (2), the matrix Any row in represents the projection of the actuator direction vector onto a certain surface and cannot be eliminated, so the matrix Rank With the augmented matrix Rank satisfy: (5) Therefore, the formula (2) is satisfied. If there is more than one group, and all four actuators are adjusted in angle, precise adjustment cannot be achieved. Therefore, two of the actuators are selected for angle adjustment, and the remaining two are not actively adjusted in angle. Formula (2) is rewritten as: (6) Step 4: According to the number of adjacent edges with the inner modules, the outer modules are divided into two categories: the first category has 1 adjacent edge with the inner modules and 4 connected actuators; the second category has 2 adjacent edges with the inner modules and 8 connected actuators.
[0029] Step 5: For the first type of outer module, consider adjusting the length. Since the upper layer of the module is the working surface, higher precision requirements are required. According to the three active actuators for adjusting the length and the two active actuators for adjusting the angle obtained in steps 2 and 3, the number of active actuators is minimized. Therefore, two actuators are selected in the upper layer as active actuators, one of which is used to adjust the length and the other is used to adjust the length and angle. One actuator is selected in the lower layer as the active actuator, which can adjust the length and angle.
[0030] Taking the direction of the center line connecting the inner module and the outer module as the axis, select the actuator on the right side of the axis in the lower layer as the active actuator, and its sequence is: ; Considering the adjustment of the angle, select the lower active actuator and the upper active actuator distributed diagonally with it to adjust the angle, and the sequence is .
[0031] Step 6: For the second type of outer layer modules, according to the three active actuators for adjusting the length and the two active actuators for adjusting the angle obtained in steps 2 and 3, the number of active actuators is minimized. Therefore, three of the eight actuators are selected as active actuators. It is stipulated that the modules close to the right side in the inner layer are selected. At this time, the layout of the active actuators of the second type of outer layer modules is the same as that of the first type of outer layer modules.
[0032] Step 7: Measure the coordinates of the upper nodes of each module of the physical antenna , taking the center module as the reference, start adjusting from the rightmost module of the first ring.
[0033] Step 8: Set the current module to be adjusted to , whose inner loop module is , module The actual node coordinates of the upper and lower layers are and , compared with the ideal position, the antenna profile accuracy is: (7) Where: Representation Module The upper node The coordinates of .
[0034] To reduce the module error, solve the module Due to the effect of error, the ideal profile often cannot be completely adjusted to the ideal profile, so the best approximation profile of the actual profile to the ideal profile can be obtained. There is a certain difference between the actual profile and the best approximation profile. Axis distance , for the module , use the least squares method to solve its Axis offset distance , the module Move to the best approximation position, that is, the position with the minimum surface accuracy. At this time, the module The coordinates of the upper and lower target nodes are and ,in: (8) (9) Step 9: When the inner ring module B is adjusted to the upper target position and the lower target location , outer ring module The actual location is and , the target location is and , module With inner ring module The active actuator sequence between , active actuator sequence for angle adjustment , with the active actuator located on the upper layer Take 2 as an example, the direction vectors before and after adjustment are: (10) (11) Where: Indicates the active actuator before adjustment The direction vector, Indicates the active actuator after adjustment The direction vector of .
[0035] Therefore, the adjustment amount of the direction vector is: (12) First solve for the active actuator exist and The angle of the face is determined by constructing a local coordinate system according to step 1. The normal vector of the face is , using the normal vector and Direction calculation and The normal vector of the face is as follows: (13) (14) Calculate and adjust the front and rear direction vectors respectively and Projection of a surface: (15) (16) (17) (18) Active Actuator exist and The rotation angle of the face is: (19) (20) The length adjustment of the active actuator is: (twenty one) Where: represents the solution of the vector inner product, It means to solve the modulus length of the corresponding vector.
[0036] Step 10: After the adjustment of the current module is completed, the next module to be adjusted is selected in a counterclockwise order from the inner ring to the outer ring, and steps 8 to 9 are repeated until all modules are adjusted, and the profile accuracy of the adjusted antenna is calculated.
[0037] The adjustment effect of the present invention is further illustrated below in conjunction with a simulation example: The on-orbit assembled antenna is used as an adjustment example for simulation adjustment. Figure 1 The antenna structure assembled on-orbit is shown, which consists of 37 modules. In addition to the central module, the antenna is divided into 3 rings, marked with different colors, such as Figure 2 shown.
[0038] Figure 3 As shown, any two modules A and B are connected by 4 actuators. Articulation, to determine the number of actuators required for the module rotation angle for analysis.
[0039] Figure 4 As shown, the adjacent surface of the inner ring module is defined as The plane is perpendicular to the surface and points to the direction of the outer ring module. Axis, after the above analysis, determine the module The displacement and rotation angle require 3 active actuators for length adjustment and 2 active actuators for angle adjustment.
[0040] Figure 5 As shown in the figure, the number of adjacent edges between the outer module and the inner module of the first type is 1, and the number of connected actuators is 4. Considering the adjustment of the length, since the upper layer is the working surface, the accuracy requirement is higher, so the two actuators in the upper layer are both active actuators. The direction of the center line connecting the inner module and the outer module is the axis, and the actuator on the right side of the axis is selected as the active actuator in the lower layer. The sequence is ; Considering the adjustment of the angle, select the lower active actuator and the upper active actuator distributed diagonally with it to adjust the angle, and the sequence is .
[0041] Figure 6 As shown in the figure, the number of adjacent edges between the outer layer module and the inner layer module of the second type is 2, the number of connected actuators is 8, and 3 of the 8 actuators are selected as active actuators. It is stipulated that the module close to the right side in the inner layer is selected. At this time, the layout of the active actuators of the second type of modules is the same as that of the first type. Figure 7 As shown, the active actuators between modules are represented by dashed lines, and the passive actuators are represented by dotted lines. like Figure 8 As shown in the figure, the position of the modules is confirmed from the inside to the outside. Starting from the central module, the position of the outer modules can be confirmed in sequence along the direction of the dotted line. According to the order of module position confirmation, the distribution of the active actuators on the upper and lower layers of the modules (indicated by the dotted lines) are as follows: Fig. 9 , Fig.10 shown.
[0042] Fig.11 As shown in the figure, due to factors such as errors, the actual profile often cannot be completely adjusted to the ideal profile. It is a more feasible method to use the best approximation profile of the current module as the target position. The relationship between the actual profile, the ideal profile and the best approximation profile.
[0043] Fig.12 Shown is a flow chart of antenna precision profile adjustment according to the present invention.
[0044] In this embodiment, the module radius is 5m, the height is 1m, and after adding random errors, the antenna surface accuracy is 8.95mm. There are 108 active actuators in total. Fig.12 The adjustment is performed according to the flowchart shown in the figure. After the adjustment, the profile accuracy of the antenna is 3.46mm. The error cloud diagrams of each module of the antenna before and after the adjustment are as follows: Fig.13 , Fig.14 As shown, it can be explained that when the method of the present invention is used for adjustment, the surface accuracy of the antenna can be improved.
[0045] Based on the same inventive concept, an embodiment of the present invention further provides an on-orbit assembled antenna module profile accuracy adjustment system based on active actuator layout determination criteria. Since the principle of solving the problem by the on-orbit assembled antenna module profile accuracy adjustment system based on active actuator layout determination criteria is similar to the aforementioned on-orbit assembled antenna module profile accuracy adjustment method based on active actuator layout determination criteria, the implementation of the on-orbit assembled antenna module profile accuracy adjustment system based on active actuator layout determination criteria can refer to the implementation of the on-orbit assembled antenna module profile accuracy adjustment method based on active actuator layout determination criteria, and the repeated parts will not be repeated here.
[0046] In specific implementation, the on-orbit assembled antenna module profile accuracy adjustment system based on the active actuator layout determination criterion provided in the embodiment of the present invention specifically includes: Analysis module, which analyzes the module positions and the number and distribution of active actuators between modules based on the mathematical model of the on-orbit assembled antenna; Get the module, get the module coordinates of the physical antenna, take the central module as the reference, and select any inner module in sequence to start adjustment; The first adjustment module calculates the adjustment target position of the module to be adjusted, and calculates the length adjustment amount and angle adjustment amount of the active actuator of the module according to the adjustment target position; The second adjustment module repeats step S3 to adjust each module in the physical antenna to obtain the surface accuracy of the adjusted physical antenna.
[0047] Correspondingly, an embodiment of the present invention further provides an on-orbit assembled antenna module profile accuracy adjustment device based on active actuator layout determination criteria, comprising a processor and a memory, wherein the processor implements an on-orbit assembled antenna module profile accuracy adjustment method based on active actuator layout determination criteria as provided in an embodiment of the present invention when executing a computer program stored in the memory.
[0048] For more specific processes of the above method, please refer to the corresponding contents disclosed in the aforementioned embodiments, which will not be repeated here.
[0049] Accordingly, an embodiment of the present invention further provides a computer-readable storage medium for storing a computer program, wherein, when the computer program is executed by a processor, the method for adjusting the profile accuracy of an on-orbit assembled antenna module based on the active actuator layout determination criterion as provided in an embodiment of the present invention is implemented.
[0050] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the systems, devices, and storage media disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the description is relatively simple, and the relevant parts can be referred to the method part.
[0051] Professionals may further appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or a combination of the two. In order to clearly illustrate the interchangeability of hardware and software, the composition and steps of each example have been generally described in the above description according to function. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professionals and technicians may use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application.
[0052] The steps of the method or algorithm described in conjunction with the embodiments disclosed herein may be implemented directly using hardware, a software module executed by a processor, or a combination of the two. The software module may be placed in a random access memory (RAM), a memory, a read-only memory (ROM), an electrically programmable ROM, an electrically erasable programmable ROM, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art.
[0053] Finally, it should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "comprise", "include" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.
[0054] The above is a detailed introduction to the method, system, device and storage medium for adjusting the profile accuracy of the on-orbit assembled antenna module based on the active actuator layout determination criterion provided by the present invention. Specific examples are used in this article to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea; at the same time, for general technical personnel in this field, according to the idea of the present invention, there will be changes in the specific implementation method and application scope. In summary, the content of this specification should not be understood as a limitation on the present invention.
Claims
1. A method for adjusting the profile accuracy of an on-orbit assembled antenna module based on the active actuator layout determination criterion, characterized in that: The following steps are involved: S1. Analyze the module positions and the number and distribution of active actuators between modules based on the mathematical model of the on-orbit assembled antenna; S2. Obtain the module coordinates of the physical antenna, take the central module as the reference, and select any inner module in sequence to start adjustment; S3, calculating the adjustment target position of the module to be adjusted, and calculating the length adjustment amount and angle adjustment amount of the active actuator of the module according to the adjustment target position; S4. Repeat step S3 to adjust each module in the physical antenna to obtain the surface accuracy of the adjusted physical antenna.
2. According to claim 1, a method for adjusting the profile accuracy of an on-orbit assembled antenna module based on the active actuator layout determination criterion is characterized in that: The specific process of step S1 is: Determine the position of the current module, and obtain the displacement matrix and angle change matrix of the adjacent module according to the length change and angle change of the actuator between the current module and the adjacent module; By analyzing the rank of the displacement matrix, we can find that the three active actuators between the current module and the adjacent modules are used to adjust the length; By analyzing the rank of the angle variation matrix, it is found that the two active actuators between the current module and the adjacent module are used to adjust the angle; Minimize the number of active actuators based on the distribution of modules.
3. According to claim 2, a method for adjusting the profile accuracy of an on-orbit assembled antenna module based on the active actuator layout determination criterion is characterized in that: The displacement matrix of adjacent modules is: Where: is the component of the direction vector of the actuator; is the length change of the actuator; The angle variation matrix is: Where: The adjacent surface of the inner ring module is The plane is perpendicular to the surface and points to the direction of the outer ring module. axis, , Indicates the actuator The change in the direction vector Towards and Projection of the surface.
4. According to claim 2, a method for adjusting the profile accuracy of an on-orbit assembled antenna module based on the active actuator layout determination criterion is characterized in that: The procedure for minimizing the number of active actors is: According to the number of adjacent edges between the outer module and the inner module, the outer modules are divided into the first type of outer modules and the second type of outer modules; The first type of outer layer module selects three actuators as active actuators; The second type of outer module selects three actuators as active actuators.
5. According to claim 1, a method for adjusting the profile accuracy of an on-orbit assembled antenna module based on the active actuator layout determination criterion is characterized in that: The specific process of step S3 is: S31, obtaining the actual node coordinates of the module to be adjusted, solving the optimal offset distance of the module to be adjusted by the least square method, and obtaining the target node coordinates of the module to be adjusted; S32, obtaining the target node coordinates of the inner ring module adjacent to the module to be adjusted, calculating the adjustment amount of the active actuator according to the target node coordinates of the module to be adjusted, the actual node coordinates and the target node coordinates of the inner ring module, and completing the adjustment of the module to be adjusted.
6. According to claim 5, a method for adjusting the profile accuracy of an on-orbit assembled antenna module based on the active actuator layout determination criterion is characterized in that: The adjustment amount of the active actuator is calculated in step S32 as follows: Where: The length adjustment amount of the main actuator; The direction vector of the active actuator before adjustment; is the direction vector after the active actuator is adjusted; Where: Active actuator The amount of angle adjustment of the surface; represents the solution of the vector inner product, Indicates the modulus length of the corresponding vector to be solved; Where: Active actuator The amount of angle adjustment of the surface; represents the solution of the vector inner product, It means to solve the modulus length of the corresponding vector.
7. According to claim 1, a method for adjusting the profile accuracy of an on-orbit assembled antenna module based on the active actuator layout determination criterion is characterized in that: Verify the adjusted surface accuracy obtained in step S4, compare the initial surface accuracy with the adjusted surface accuracy, and if the adjusted surface accuracy is less than the initial surface accuracy, the surface accuracy adjustment of the on-orbit assembled antenna module is completed.
8. A system for adjusting the profile accuracy of an on-orbit assembled antenna module based on the active actuator layout determination criterion, characterized in that: include: Analysis module, which analyzes the module positions and the number and distribution of active actuators between modules based on the mathematical model of the on-orbit assembled antenna; Get the module, get the module coordinates of the physical antenna, take the central module as the reference, and select any inner module in sequence to start adjustment; The first adjustment module calculates the adjustment target position of the module to be adjusted, and calculates the length adjustment amount and angle adjustment amount of the active actuator of the module according to the adjustment target position; The second adjustment module repeats step S3 to adjust each module in the physical antenna to obtain the surface accuracy of the adjusted physical antenna.
9. An on-orbit assembled antenna module profile accuracy adjustment device based on active actuator layout determination criteria, characterized in that: The method comprises a processor and a memory, wherein the processor implements the method for adjusting the profile accuracy of an on-orbit assembled antenna module based on the active actuator layout determination criterion as described in any one of claims 1 to 7 when executing the computer program stored in the memory.
10. A computer-readable storage medium, characterized in that: Used to store a computer program, wherein when the computer program is executed by a processor, the method for adjusting the profile accuracy of an on-orbit assembled antenna module based on an active actuator layout determination criterion as described in any one of claims 1 to 7 is implemented.