Satellite-borne antenna rod piece length acquisition method and device, electronic equipment and storage medium

Abstract

The invention provides a satellite-borne antenna rod piece length obtaining method and device, electronic equipment and a storage medium. The method comprises the following steps: acquiring the aperture length and the focal length of the spaceborne antenna; determining the number of layers of rod piece nodes of a paraboloid where the spaceborne antenna is located according to the caliber length; obtaining an error value of a triangular unit in the spaceborne antenna, wherein the triangular unit is composed of three rod pieces of the spaceborne antenna; and iteratively adjusting the position and the length of each layer of rod piece in the spaceborne antenna according to the error value to obtain the target length and the node position of each layer of rod piece. According to the embodiment, the positions and the lengths of the rod pieces on each layer are iteratively adjusted, so that the rod pieces on the same layer have the same length, the length consistency of the rod pieces is improved, and the precision of the spaceborne antenna is improved.

Description

Technical Field

[0001] The present disclosure relates to the field of wireless communication technology, and in particular to a method, device, electronic device and storage medium for obtaining the length of a satellite-borne antenna rod. Background Art

[0002] Existing satellite-borne antennas are usually constructed using rods of different lengths, resulting in high production costs and low antenna accuracy. Summary of the invention

[0003] The present disclosure provides a method, device, electronic device and storage medium for obtaining the length of a satellite-borne antenna rod to solve the above-mentioned technical problems.

[0004] According to a first aspect of the present disclosure, a method for obtaining the length of a satellite-borne antenna rod is provided, the method comprising:

[0005] Get the aperture length and focal length of the satellite antenna;

[0006] Determine the number of layers of the rod nodes of the parabola where the satellite-borne antenna is located according to the aperture length;

[0007] Obtaining an error value of a triangular unit in the satellite antenna, wherein the triangular unit is composed of three rods of the satellite antenna;

[0008] The position and length of each layer of rods in the satellite antenna are iteratively adjusted according to the error value to obtain the target length and node position of each layer of rods.

[0009] Optionally, determining the number of layers of rod nodes of the parabola where the satellite-borne antenna is located according to the aperture length includes:

[0010] Determine a target caliber range within which the caliber length lies;

[0011] The target number of layers is determined according to the matching relationship between the aperture range and the number of layers and the target aperture range, and is used as the number of layers of the rod nodes of the parabola where the satellite-borne antenna is located.

[0012] Optionally, obtaining an error value of a triangular unit in the satellite antenna includes:

[0013] Get the square error value of each triangle element;

[0014] Obtaining the integral value of the square error values ​​of all triangular units of the parabola to obtain an integral error value;

[0015] Get the area of ​​each triangular unit;

[0016] Obtaining the integral value of the area of ​​all triangular units of the parabola to obtain an area integral value;

[0017] A square root of the error integral value and the area integral ratio is obtained as an error value of a triangular unit in the satellite antenna.

[0018] Optionally, iteratively adjusting the position and length of each layer of rods in the satellite antenna according to the error value to obtain a target length and a node position of each layer of rods includes:

[0019] Obtaining the length range of each layer of rods in the satellite-borne antenna and the floating range of each node in a preset direction;

[0020] Determine the constraints of the global optimization algorithm;

[0021] The error value, the length range of each layer of rods and the floating variation range of each node are input into the global optimization model to obtain the target length and node position of each layer of rods output by the global optimization model.

[0022] Optionally, the global optimization algorithm includes one of a genetic algorithm and a particle swarm optimization algorithm.

[0023] According to a second aspect of the present disclosure, a device for obtaining the length of a satellite-borne antenna rod is provided, the device comprising:

[0024] The length and focal length acquisition module is used to obtain the aperture length and focal length of the satellite antenna;

[0025] A node layer number determination module, used to determine the number of layers of the rod node of the parabola where the satellite-borne antenna is located according to the aperture length;

[0026] An error value acquisition module, used to acquire an error value of a triangular unit in the satellite antenna, wherein the triangular unit is composed of three rods of the satellite antenna;

[0027] The length and position acquisition module is used to iteratively adjust the position and length of each layer of rods in the satellite antenna according to the error value to obtain the target length and node position of each layer of rods.

[0028] Optionally, the node layer number determination module includes:

[0029] A target aperture determination unit, used to determine a target aperture range within which the aperture length lies;

[0030] The node layer number determination unit is used to determine the target layer number according to the matching relationship between the aperture range and the layer number and the target aperture range, as the layer number of the rod node of the parabola where the satellite-borne antenna is located.

[0031] Optionally, the error value acquisition module includes:

[0032] A square error obtaining unit, used to obtain the square error value of each triangle unit;

[0033] An error integral acquisition unit, used to acquire the integral value of the square error values ​​of all the triangular units of the parabola to obtain an error integral value;

[0034] A face element area acquisition unit, used to obtain the area of ​​each triangle element;

[0035] An area integral obtaining unit, used to obtain the integral value of the area of ​​all triangular units of the parabola to obtain an area integral value;

[0036] The error value acquisition unit is used to obtain the square root of the error integral value and the area integral ratio as the error value of the triangular unit in the satellite antenna.

[0037] Optionally, the length position acquisition module includes:

[0038] A floating range acquisition unit, used to acquire the length range of each layer of rods in the satellite-borne antenna and the floating range of each node in a preset direction;

[0039] The constraint condition determination unit is used to determine the constraint conditions of the global optimization algorithm;

[0040] The length position acquisition unit is used to input the error value, the length range of each layer of rods and the floating variation range of each node into the global optimization model to obtain the target length and node position of each layer of rods output by the global optimization model.

[0041] Optionally, the global optimization algorithm includes one of a genetic algorithm and a particle swarm optimization algorithm.

[0042] According to a third aspect of the present disclosure, there is provided an electronic device, including:

[0043] Processor and memory;

[0044] The memory is used to store a computer program executable by the processor;

[0045] The processor is configured to execute the computer program in the memory to implement the method as described in any one of the first aspects.

[0046] Optionally, each node of the satellite-borne antenna includes a connecting member and a plurality of rod members; the rod members are movably connected to the connecting member via a ball joint element.

[0047] According to a fourth aspect of the present disclosure, a non-transitory computer-readable storage medium is provided, and when an executable computer program in the storage medium is executed by a processor, the method described in any one of the first aspects can be implemented.

[0048] The technical solution provided by the embodiments of the present disclosure may have the following beneficial effects:

[0049] The scheme provided in this embodiment can obtain the aperture length and focal length of the satellite antenna; then, determine the number of layers of the rod node of the parabola where the satellite antenna is located according to the aperture length; then, obtain the error value of the triangular unit in the satellite antenna, the triangular unit is composed of three rods of the satellite antenna; finally, iteratively adjust the position and length of each layer of rods in the satellite antenna according to the error value to obtain the target length and node position of each layer of rods. In this way, this embodiment iteratively adjusts the position and length of each layer of rods so that the rods in the same layer have the same length, improves the consistency of the rod length, and is conducive to improving the accuracy of the satellite antenna.

[0050] It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Figure 1 This is a schematic diagram of a connecting member and a rod member being separated according to an embodiment of the present disclosure.

[0052] Figure 2 The present invention is a schematic diagram of a connecting member and a rod member combined into a ball joint element according to an embodiment of the present invention.

[0053] Figure 3 The diagram is a schematic diagram of a parabolic mesh surface of a satellite-borne antenna according to an embodiment of the present disclosure.

[0054] Figure 4 The figure is a schematic diagram of the projection of a parabolic mesh surface with five layers of nodes according to an embodiment of the present disclosure.

[0055] Figure 5 The figure is a schematic projection diagram of a parabolic mesh surface with 6 nodes according to an embodiment of the present disclosure.

[0056] Figure 6 A schematic diagram of obtaining geometric freedom according to an embodiment of the present disclosure.

[0057] Figure 7 The present invention is a flowchart of a method for obtaining the length of a satellite-borne antenna rod according to an embodiment of the present invention.

[0058] Figure 8 The present invention is a flowchart of an error value of a triangle unit according to an embodiment of the present invention.

[0059] Fig. 9 The diagram is a schematic diagram of dividing a triangular unit into three face elements according to an embodiment of the present disclosure.

[0060] Fig.10The present invention is a flow chart of a particle swarm optimization algorithm according to an embodiment of the present invention.

[0061] Fig.11 The present invention is a flowchart of a genetic algorithm according to an embodiment of the present invention.

[0062] Fig.12 The present invention is a schematic diagram of a device for obtaining the length of a satellite-borne antenna rod according to an embodiment of the present invention. DETAILED DESCRIPTION

[0063] Exemplary embodiments will be described in detail herein, examples of which are shown in the accompanying drawings. When the following description refers to the drawings, the same numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present disclosure. Instead, they are merely examples of devices consistent with some aspects of the present disclosure as detailed in the appended claims.

[0064] The present disclosure provides a method, device, electronic device and storage medium for obtaining the length of a satellite-borne antenna rod. The above-mentioned method for obtaining the length of a satellite-borne antenna rod can be used to obtain a satellite-borne antenna or to assist in optimizing a satellite-borne antenna.

[0065] The disclosed embodiment provides a satellite antenna having a parabolic mesh surface. One of the inventive concepts of this embodiment is to divide the parabolic mesh surface into a plurality of triangular meshes; the edges of the triangular meshes are rods, and the nodes of the triangular meshes are formed by spherical joint elements.

[0066] See also Figure 1 The ball joint element includes a connecting member 11 and a rod 12. The connecting member 11 includes a plurality of spherical grooves 111, and a ball 121 is provided at both ends of the rod 12. After the rod 12 is inserted into the connecting member 11, a ball 121 is formed. Figure 2 The ball joint element 13 is shown. Figure 2 The spherical joint element can reflect the connection between the layers and show C6 symmetry. In one example, the length of the connecting rod of the node in the 2nd layer of the i-th layer is unified as l 1i , and the length of the connecting rod between the i-th layer and the next layer (i+1 or i-1) is uniformly l 2i Thus, the parabolic network of the satellite antenna in this embodiment can be Figure 3 It can be understood that in this embodiment, visual stretching processing is performed in the Z-axis direction of the satellite antenna, so as to clearly display the triangular mesh.

[0067] See also Figure 3 The parabolic mesh of the satellite antenna can be equivalent to a geometric body formed by unjoined triangular pieces. In this way, this example can optimize the geometric characteristics of the geometric body and improve the efficiency of the manufacturing process.

[0068] In this embodiment, the number of layers of the triangular mesh can be determined according to the aperture length of the satellite antenna. The principle of setting the number of layers of the triangular mesh can be: the aperture length is 1m as the starting value, and one layer of nodes is added for every 0.4-0.6m increase in the aperture length, that is, one layer of triangular mesh is added, and the initial value of the number of layers of the triangular mesh is 2 layers. The starting value of 1m and the increase in length of 0.4-0.6m can be set according to the specific scenario, and the corresponding scheme falls within the protection scope of this disclosure.

[0069] For example, if the aperture length of the satellite antenna is 2.5 meters and a layer is added every 0.5 meters, the satellite antenna can be set up with 5 layers of triangular grids, such as Figure 4 For example, if the aperture length of the satellite antenna is 2.5 meters and one layer is added every 0.5 meters, the satellite antenna can be set up with 6 layers of triangular grids, such as Figure 5 The examples are layers 1 to 6.

[0070] In this embodiment, see Figure 6 ,right Figure 3 The degrees of freedom calculation of the parabolic mesh or geometric body of the example spaceborne antenna includes:

[0071] (1) Assume that n points in the i-th layer are fixed (taking n=6 as an example), forming l 1i The rods are connected to form an n-gon.

[0072] (2) For each edge connecting two nodes, we can find a point with a distance l from the two points. ei , an isosceles triangle is formed that rotates around its edge, and the degree of freedom is 1. Counting all n edges, n degrees of freedom are generated.

[0073] (3) For the case where the i+1th layer is n+k points, k (k is less than n) nodes can be selected in the i-th layer to generate a length of l 2i Count all k points generated, resulting in 2k degrees of freedom.

[0074] (4) For the n+k points generated in the i+1th layer, connect them to form a side length of l 1(i+1) A polygon, at this time n+k constraints are introduced.

[0075] From the above content, it can be seen that the number of degrees of freedom between layers is equal to the number of nodes. At the same time, considering that the number of nodes does not decrease as the number of layers of the geometry increases, there will be no over-constraint phenomenon. Considering that the degrees of freedom of a tetrahedron are 6 and the outermost layer has 3 points, the degree of freedom of the entire system is 3 more than the number of nodes in the outermost layer: the redundancy of degrees of freedom provides the possibility for the folding process of the system mechanism; if the spatial coordinates of the outermost m nodes are fixed, 3m additional constraints can be introduced, and the system will have 2m-3 over-constraints.

[0076] In one example, the point arrangement scheme for each layer is designed according to the extension characteristics of the quadratic function, and the corresponding points for each layer are as follows: Figure 4 and Figure 5 As shown in the figure, the number of nodes in the 5-layer triangular mesh solution is [6, 12, 24, 36, 36]; the number of nodes in the 6-layer triangular mesh solution is [6, 12, 24, 36, 48, 48]. When laying the 5-layer solution, there are 115 nodes and 39 independent degrees of freedom. If the fixed mesh node is further constrained, 33 degrees of freedom can be constrained. This design allows a certain degree of flexibility while ensuring the stability of the structure.

[0077] In addition, in this example, we also need to pay attention to the impact of the reduction in the number of parts on the overall design. By adopting the method of building with standard parts, the number of parts required can be greatly reduced. For example, in the traditional design, each rod and connector is different, requiring 56 different rods and 19 different connectors (under C6 symmetry); while the 5-layer solution in this example only requires 10 different rods and 3 different connectors, which not only simplifies the production process, but also reduces costs and assembly difficulty.

[0078] Based on the above content, the embodiment of the present disclosure also provides a method for obtaining the length of a satellite-borne antenna rod. Figure 7 , including steps 71 to 74.

[0079] In step 71, the aperture length and focal length of the satellite-borne antenna are obtained.

[0080] In this embodiment, the aperture length and focal length of the satellite antenna can be obtained. Considering that the aperture length and focal length of the satellite antenna have been determined when designing the satellite antenna, the designer can input them into the electronic device and read the above data from the specified position of the electronic device.

[0081] In step 72, the number of layers of the rod nodes of the parabola where the satellite-borne antenna is located is determined according to the aperture length.

[0082] In this embodiment, the number of layers of the rod node of the parabola where the satellite antenna is located can be determined according to the aperture length, that is, the target aperture range where the aperture length is located can be determined; then, the target number of layers can be determined according to the matching relationship between the aperture range and the number of layers and the target aperture range, as the number of layers of the rod node of the parabola where the satellite antenna is located. It can be understood that the above embodiment describes a scheme for determining the number of layers of the rod node according to the aperture length of the satellite antenna. For details, please refer to the content of the above embodiment, which will not be repeated here.

[0083] In step 73, an error value of a triangular unit in the satellite antenna is obtained, where the triangular unit is composed of three rods of the satellite antenna.

[0084] In this embodiment, the error value of the triangular unit in the satellite antenna can be obtained, see Figure 8 , including steps 81 to 85.

[0085] In step 81, the square error value of each triangle unit is obtained.

[0086] Considering that each triangular element of the satellite antenna is in a triangular shape, a triangular linear interpolation finite element unit can be used for simulation in this step. Fig. 9 As shown, based on any unit P in the triangular unit, each triangular unit can be divided into three face elements A1, A2 and A3, and the corresponding areas are interpolated and calculated, as shown in formula (1).

[0087]

[0088] In formula (1), A i represents the projection area of ​​the corresponding triangle on the xoy plane, z i represents the function value of the corresponding node, where is the coordinate value in the z direction of the corresponding node, and A represents the projection area of ​​the triangular unit. After the fourth-order six-point (the highest order of the square of the quadratic term is 4th) finite element discretization, the function surface integral can be converted into a weighted calculation of the number of points.

[0089] Table 1 Fourth-order six-point integral table

[0090] Points i <![CDATA[W i ]]> <![CDATA[ξ 1 ]]> <![CDATA[ξ 2 ]]> <![CDATA[ξ 3 ]]> 1 0.109952 0.81685 0.09157 0.09157 2 0.109952 0.09157 0.81685 0.09157 3 0.109952 0.09157 0.09157 0.81685 4 0.223382 0.10810 0.44595 0.44595 5 0.223382 0.44595 0.10810 0.44595 6 0.223382 0.44595 0.44595 0.10810

[0091] The specific calculation is as follows, where J represents the Jacobian matrix, which is a constant for a triangular patch, that is, the projection area of ​​the triangle is shown in formula (2).

[0092]

[0093] In formula (2), f() represents the function, J represents the Jacobian matrix; represents the spatial position (x, y, z) of each point on the parabola (each point in the i-th triangular unit); ξ 1i ,ξ 2i ,ξ 3i They represent the vertices of the i-th triangle unit, and their values ​​are shown in Table 1; W i Represents the weight of each vertex; The three vertices of the i-th triangle unit are used to determine each point within the triangle unit.

[0094] The coordinates of each point in the triangular unit of the parabola are obtained by processing with a standard function, as shown in formula (3).

[0095]

[0096] In formula (3), f1 represents the focal length, and x and y represent the horizontal and vertical coordinates of each point in the triangle, respectively.

[0097] The square error value of any triangle patch can be calculated using formula (4).

[0098]

[0099] In formula (4), e e represents the square error value, z * Represents the standard coordinates of each point on the parabola on the Z axis. Represents interpolated coordinates.

[0100] In step 82, the integral value of the square error values ​​of all the triangular elements of the parabola is obtained to obtain the error integral value.

[0101] In this step, the integral value of the square error value of all triangular units of the parabola is obtained to obtain the error integral value ∑ e e e .

[0102] In step 83, the area of ​​each triangle unit is obtained.

[0103] In this embodiment, the area of ​​each triangular unit is obtained as shown in formula (5).

[0104]

[0105] In formula (5), S e Represents the area integral of the triangular element.

[0106] In step 84, the integral value of the area of ​​all triangular units of the parabola is obtained to obtain the area integral value.

[0107] In this embodiment, the integral value of the area of ​​all triangle units is the area integral value ∑ e S e .

[0108] In step 85, a square root of the error integral value and the area integral ratio is obtained as an error value of a triangular unit in the satellite antenna.

[0109] In this step, the RMS error value of the triangular unit in the satellite antenna is shown in formula (6).

[0110]

[0111] It is understandable that in this embodiment, by combining the integral results of all triangular units, the overall RMS value can be calculated. This method not only improves the accuracy of antenna profile design, but also provides an effective error evaluation method, which helps to optimize the antenna design process.

[0112] In step 74, the position and length of each layer of rods in the satellite antenna are iteratively adjusted according to the error value to obtain the target length and node position of each layer of rods.

[0113] In this embodiment, the length range of each layer of rods and the floating range of each node in a preset direction (such as the Z axis) can be preset, as shown in Table 2.

[0114] Table 2

[0115] Optimization variables Reference range <![CDATA[The length l of the rods in each layer 1 ,l]]> 0.3～1.2m <![CDATA[Floating amount tol of the z coordinate 1 , tol 2 (except for the first layer)]]> -0.1～0.1m

[0116] In this embodiment, a global optimization algorithm may be preset, and the global optimization algorithm may include one of a genetic algorithm and a particle swarm optimization algorithm.

[0117] Taking the particle swarm optimization algorithm as an example, the particle swarm optimization algorithm can imitate the foraging behavior of bird flocks and insect swarms. Each particle is attracted by the optimal position found, and is also attracted by the optimal position found by other individuals. After several steps, the particles will gather around certain positions. After iterations, the position where all particles gather together is the optimization result. In this example, the particle swarm optimization algorithm can be applied to the satellite antenna design optimization process. By adding a penalty function term to the objective function to solve the dilemma of local optimal solutions when solving multi-peak problems, the effect of quickly converging to find the global optimal solution with a small amount of calculation is achieved. In this example, the steps of the particle swarm optimization algorithm are as follows: Fig.10As shown, it includes: first initializing the particle swarm; then calculating the fitness of each particle. Among them, the particle is equivalent to the node, and the fitness of the particle is equivalent to the length of the rod. After obtaining the new particle position and fitness, the new position pbest and the new fitness gbest can be updated. Then, it is determined whether the above new position pbest and the new fitness gbest meet the stop condition. If not, the new position pbest and the new fitness gbest are re-iteratively calculated; if they are satisfied, the iterative process ends.

[0118] Taking genetic algorithm as an example, it gradually approaches the optimal solution by iteratively modifying the solution population. It is suitable for solving problems with constraints and has good effects on multi-peak problems and discrete variable problems. The steps of genetic algorithm are as follows: Fig.11 As shown, it includes: first determine the parameter range and initialize the population P(t), which is equivalent to setting the number of layers of nodes and the length of the rods of the parabola mesh. Then score the individuals based on fitness to determine whether the stopping criteria are met. If they are met, the algorithm stops and the length of each rod and the position of the node are obtained. If the stopping criteria are not met, the parent is selected, that is, the node position and the length of the rod are updated, and the elite individual is selected. If it is, the offspring is generated. If it is not an elite individual, the two individuals are crossed or the single individual is mutated and then the offspring is generated, and the iteration continues.

[0119] After determining the global optimization algorithm, this embodiment may add constraints to the unconstrained objective function, as shown in Table 3.

[0120] Table 3

[0121]

[0122] In this embodiment, when the global optimization algorithm adopts a genetic algorithm, the constraints can be written as nonlinear constraint functions as the @nonlcon parameter input, and the genetic algorithm optimizer ga provided by MATLAB can directly process the constraints using the Lagrange multiplier method; if the global optimization algorithm adopts a particle swarm optimization algorithm, the penalty function method is required to add the constraints to the objective function, and the particle swarm function provided by MATLAB is used for optimization.

[0123] Based on the above content, it can be known that this embodiment can obtain the length range of each layer of rods in the satellite antenna and the floating amount range of each node in the preset direction, and determine the constraint conditions of the global optimization algorithm. Finally, the above error value, the length range of each layer of rods and the floating variation range of each node are input into the global optimization model to obtain the target length and node position of each layer of rods output by the global optimization model.

[0124] It should be noted that when inputting variables of the global optimization algorithm, each variable can be normalized to have better processing efficiency without changing the final result. Taking the particle swarm optimization algorithm as an example, the number of particles is set to 950-1100, which can ensure that the optimal solution is obtained without the iteration speed being too slow. Taking the genetic algorithm as an example, the offspring scale is set to 200-500, such as 300, which can ensure that the optimal solution is obtained without the iteration speed being too slow. In order to improve efficiency, the global optimization algorithm in this example can choose the mode of parallel iterative processing of the genetic algorithm and the particle swarm optimization algorithm to increase the iteration speed.

[0125] The scheme provided in this embodiment can obtain the aperture length and focal length of the satellite antenna; then, determine the number of layers of the rod node of the parabola where the satellite antenna is located according to the aperture length; then, obtain the error value of the triangular unit in the satellite antenna, the triangular unit is composed of three rods of the satellite antenna; finally, iteratively adjust the position and length of each layer of rods in the satellite antenna according to the error value to obtain the target length and node position of each layer of rods. In this way, this embodiment iteratively adjusts the position and length of each layer of rods so that the rods in the same layer have the same length, improves the consistency of the rod length, and is conducive to improving the accuracy of the satellite antenna.

[0126] Based on the satellite antenna rod length acquisition method provided in the embodiment of the present disclosure, the embodiment of the present disclosure also provides a satellite antenna rod length acquisition device, see Fig.12 , the device comprises:

[0127] The length and focal length acquisition module 1201 is used to obtain the aperture length and focal length of the satellite-borne antenna;

[0128] A node layer number determination module 1202 is used to determine the number of layers of the rod node of the parabola where the satellite antenna is located according to the aperture length;

[0129] The error value acquisition module 1203 is used to acquire the error value of the triangular unit in the satellite antenna, where the triangular unit is composed of three rods of the satellite antenna;

[0130] The length and position acquisition module 1204 is used to iteratively adjust the position and length of each layer of rods in the satellite antenna according to the error value to obtain the target length and node position of each layer of rods.

[0131] Optionally, the node layer number determination module includes:

[0132] A target aperture determination unit, used to determine a target aperture range within which the aperture length lies;

[0133] The node layer number determination unit is used to determine the target layer number according to the matching relationship between the aperture range and the layer number and the target aperture range, as the layer number of the rod node of the parabola where the satellite-borne antenna is located.

[0134] Optionally, the error value acquisition module includes:

[0135] A square error obtaining unit, used to obtain the square error value of each triangle unit;

[0136] An error integral acquisition unit, used to acquire the integral value of the square error values ​​of all the triangular units of the parabola to obtain an error integral value;

[0137] A face element area acquisition unit, used to obtain the area of ​​each triangle element;

[0138] An area integral obtaining unit, used to obtain the integral value of the area of ​​all triangular units of the parabola to obtain an area integral value;

[0139] The error value acquisition unit is used to obtain the square root of the error integral value and the area integral ratio as the error value of the triangular unit in the satellite antenna.

[0140] Optionally, the length position acquisition module includes:

[0141] A floating range acquisition unit, used to acquire the length range of each layer of rods in the satellite-borne antenna and the floating range of each node in a preset direction;

[0142] The constraint condition determination unit is used to determine the constraint conditions of the global optimization algorithm;

[0143] The length position acquisition unit is used to input the error value, the length range of each layer of rods and the floating variation range of each node into the global optimization model to obtain the target length and node position of each layer of rods output by the global optimization model.

[0144] Optionally, the global optimization algorithm includes one of a genetic algorithm and a particle swarm optimization algorithm.

[0145] It should be noted that the system embodiment provided in this embodiment corresponds to the above method embodiment. For details, please refer to the contents of the above method embodiments, which will not be repeated here.

[0146] The present disclosure also provides an electronic device, including:

[0147] Processor and memory;

[0148] The memory is used to store a computer program executable by the processor;

[0149] The processor is used to execute the computer program in the memory to implement the above method.

[0150] The embodiments of the present disclosure also provide a non-transitory computer-readable storage medium, which can implement the above-mentioned method when an executable computer program in the storage medium is executed by a processor.

[0151] Those skilled in the art will readily appreciate other embodiments of the present disclosure after considering the specification and practicing the disclosure disclosed herein. The present disclosure is intended to cover any variations, uses, or adaptations that follow the general principles of the present disclosure and include common knowledge or customary techniques in the art that are not disclosed in the present disclosure. The description and examples are to be considered exemplary only, and the true scope and spirit of the present disclosure are indicated by the following claims.

[0152] It should be understood that the present disclosure is not limited to the exact structures that have been described above and shown in the drawings, and that various modifications and changes may be made without departing from the scope thereof. The scope of the present disclosure is limited only by the appended claims.

Claims

1. A method for obtaining the length of a satellite-borne antenna rod, characterized in that: The method comprises: Get the aperture length and focal length of the satellite antenna; Determine the number of layers of the rod nodes of the parabola where the satellite-borne antenna is located according to the aperture length; Obtaining an error value of a triangular unit in the satellite antenna, wherein the triangular unit is composed of three rods of the satellite antenna; The position and length of each layer of rods in the satellite antenna are iteratively adjusted according to the error value to obtain the target length and node position of each layer of rods.

2. The method according to claim 1, characterized in that Determining the number of layers of the rod nodes of the parabola where the satellite-borne antenna is located according to the aperture length includes: Determine a target caliber range within which the caliber length lies; The target number of layers is determined according to the matching relationship between the aperture range and the number of layers and the target aperture range, and is used as the number of layers of the rod nodes of the parabola where the satellite-borne antenna is located.

3. The method according to claim 1, characterized in that Obtaining an error value of a triangular unit in the satellite-borne antenna includes: Get the square error value of each triangle element; Obtaining the integral value of the square error values ​​of all triangular units of the parabola to obtain an error integral value; Get the area of ​​each triangular unit; Obtaining the integral value of the area of ​​all triangular units of the parabola to obtain an area integral value; A square root of the error integral value and the area integral ratio is obtained as an error value of a triangular unit in the satellite antenna.

4. The method according to claim 1, characterized in that: Iteratively adjusting the position and length of each layer of rods in the satellite antenna according to the error value to obtain the target length and node position of each layer of rods, including: Obtaining the length range of each layer of rods in the satellite-borne antenna and the floating range of each node in a preset direction; Determine the constraints of the global optimization algorithm; The error value, the length range of each layer of rods and the floating variation range of each node are input into the global optimization model to obtain the target length and node position of each layer of rods output by the global optimization model.

5. The method according to claim 4, characterized in that The global optimization algorithm includes one of a genetic algorithm and a particle swarm optimization algorithm.

6. A device for obtaining the length of a satellite-borne antenna rod, characterized in that: The device comprises: The length and focal length acquisition module is used to obtain the aperture length and focal length of the satellite antenna; A node layer number determination module, used to determine the number of layers of the rod node of the parabola where the satellite-borne antenna is located according to the aperture length; An error value acquisition module, used to acquire an error value of a triangular unit in the satellite antenna, wherein the triangular unit is composed of three rods of the satellite antenna; The length and position acquisition module is used to iteratively adjust the position and length of each layer of rods in the satellite antenna according to the error value to obtain the target length and node position of each layer of rods.

7. The device according to claim 6, characterized in that The node layer number determination module includes: A target aperture determination unit, used to determine a target aperture range within which the aperture length lies; The node layer number determination unit is used to determine the target layer number according to the matching relationship between the aperture range and the layer number and the target aperture range, as the layer number of the rod node of the parabola where the satellite-borne antenna is located.

8. The device according to claim 6, characterized in that The error value acquisition module comprises: A square error obtaining unit, used to obtain the square error value of each triangle unit; An error integral acquisition unit, used to acquire the integral value of the square error values ​​of all the triangular units of the parabola to obtain an error integral value; A face element area acquisition unit, used to obtain the area of ​​each triangle element; An area integral obtaining unit, used to obtain the integral value of the area of ​​all triangular units of the parabola to obtain an area integral value; The error value acquisition unit is used to obtain the square root of the error integral value and the area integral ratio as the error value of the triangular unit in the satellite antenna.

9. The device according to claim 6, characterized in that The length position acquisition module comprises: A floating range acquisition unit, used to acquire the length range of each layer of rods in the satellite-borne antenna and the floating range of each node in a preset direction; The constraint condition determination unit is used to determine the constraint conditions of the global optimization algorithm; The length position acquisition unit is used to input the error value, the length range of each layer of rods and the floating variation range of each node into the global optimization model to obtain the target length and node position of each layer of rods output by the global optimization model.

10. The device according to claim 9, characterized in that The global optimization algorithm includes one of a genetic algorithm and a particle swarm optimization algorithm.

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