A satellite solar wing deployment hinge stiffness optimization method and system

Abstract

The present invention relates to the field of satellite technology, and in particular to a method and system for optimizing the stiffness of a satellite solar wing deployment hinge. The method comprises: obtaining a solar wing deployment model; using a gradient-based optimization algorithm and combining it with an objective function to calculate the relative stiffness between all hinges, normalizing the relative stiffness between all hinges using the expected deployment time of the solar wing, and calculating the stiffness value of each hinge; and obtaining a candidate hinge product corresponding to each hinge; respectively adding structures and stiffness of multiple groups of candidate hinge products to the solar wing deployment model, and performing simulation calculations, determining the candidate hinge product corresponding to the optimal simulation calculation result as the final selected hinge product, and simulating the stiffness of different hinges, which is equivalent to being verified in the design stage, determining the selection of hinge products, and improving the reliability of the satellite.

Description

Background Art

[0002] With the rapid development of the commercial aerospace industry in recent years, the demand for low-orbit small satellites has become increasingly greater; at the same time, the integration of satellite payloads and equipment has become increasingly higher, and the power consumption has also increased, and the demand for the solar wing illumination area has continued to increase; in order to reduce the envelope size of the satellite and increase the solar wing storage ratio, multi-fold solar wings are becoming more and more common in small satellites.

[0003] For traditional multi-fold solar panels, the synchronous deployment mechanism can be used to effectively plan the deployment path to avoid interference or collision with the satellite cabin and other equipment during the deployment process, which would have an adverse effect on the solar panels. However, the solar panels of small satellites are relatively small in area and the deployment time is short. The use of a synchronous deployment mechanism will significantly increase the weight of the small satellite. At the same time, adding a series unit will also reduce the reliability of the system.

[0004] Currently, most small satellites, especially microsatellites weighing less than 100kg, do not use a synchronous deployment mechanism for their solar panels. Instead, they are deployed through a few sets of hinges. However, if the hinge stiffness is not designed, there will be certain risks during the deployment process. Currently, the selection of hinge stiffness is often based solely on experience, which requires a large number of design iterations and is difficult to verify during the design stage. Summary of the invention

[0005] The technical problem to be solved by the present invention is to provide a method and system for optimizing the stiffness of a satellite solar wing deployment hinge in view of the deficiencies in the prior art.

[0006] The technical solution of a satellite solar wing deployment hinge stiffness optimization method of the present invention is as follows:

[0007] Modeling the deployment process of a solar wing installed on a satellite to obtain a solar wing deployment model;

[0008] The stiffness of the root hinge of the solar wing and each inter-panel hinge is taken as an optimization design variable and assigned with initial values ​​respectively;

[0009] A gradient-based optimization algorithm is used to calculate the relative stiffness of all hinges, including the root hinge of the solar wing and all inter-panel hinges, in combination with the objective function.

[0010] Using the expected deployment time of the solar wing, the relative stiffness between all hinges is normalized to calculate the stiffness value of each hinge;

[0011] According to the stiffness value of each hinge, corresponding selection is made to obtain the hinge products to be selected corresponding to each hinge;

[0012] In the solar wing deployment model, the structures and stiffness of multiple groups of hinge products to be selected are added to the solar wing deployment model respectively, and simulation calculations are performed to obtain multiple simulation calculation results. The optimal simulation calculation result is determined from all the simulation calculation results, and a group of hinge products to be selected corresponding to the optimal simulation calculation result is determined as the hinge products finally selected.

[0013] The technical solution of a satellite solar wing deployment hinge stiffness optimization system of the present invention is as follows:

[0014] It includes modeling module, calculation module, normalization module, selection module, simulation module and determination module;

[0015] The modeling module is used to: model the deployment process of the solar wing installed on the satellite to obtain a solar wing deployment model, and use the stiffness of the root hinge of the solar wing and each inter-plate hinge as optimization design variables, and assign initial values ​​to each of them;

[0016] The calculation module is used to: calculate the relative stiffness between all hinges based on the gradient optimization algorithm and in combination with the objective function, all hinges including the root hinge of the solar wing and all inter-panel hinges;

[0017] The normalization module is used to: perform normalization processing on the relative stiffness between all hinges using the expected unfolding time of the solar wing, and calculate the stiffness value of each hinge;

[0018] The selection module is used for:

[0019] According to the stiffness value of each hinge, corresponding selection is made to obtain the hinge products to be selected corresponding to each hinge;

[0020] The simulation module is used to: in a solar wing deployment model, add the structures and stiffnesses of multiple groups of hinge products to be selected to the solar wing deployment model, perform simulation calculations, and obtain multiple simulation calculation results;

[0021] The determination module is used to determine the optimal simulation calculation result from all simulation calculation results, and determine a group of hinge products to be selected corresponding to the optimal simulation calculation result as the hinge products finally selected. The beneficial effects of the present invention are as follows:

[0022] The solar wing can be deployed through several sets of hinges without using a synchronous deployment mechanism and without increasing the weight of the satellite. Moreover, through the simulation of the stiffness of different hinges, it is equivalent to being verified in the design stage, determining the choice of hinge products, improving the reliability of the satellite, and ultimately achieving nearly synchronous deployment of the solar wings. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0024] Figure 1 A schematic diagram of a flow chart of a method for optimizing the stiffness of a satellite solar wing deployment hinge according to an embodiment of the present invention;

[0025] Figure 2 is a schematic diagram of a tri-fold solar wing in a folded state;

[0026] Figure 3 A schematic diagram of a tri-fold solar wing being unfolded;

[0027] Figure 4 is a schematic diagram of a fully unfolded tri-fold solar wing;

[0028] Figure 5 This is a structural schematic diagram of a satellite solar wing deployment hinge stiffness optimization system according to an embodiment of the present invention. DETAILED DESCRIPTION

[0029] like Figure 1 As shown, a satellite solar wing deployment hinge stiffness optimization method according to an embodiment of the present invention comprises the following steps:

[0030] S1. Modeling the deployment process of a solar wing installed on a satellite to obtain a solar wing deployment model;

[0031] S2, taking the stiffness of the root hinge of the solar wing and each inter-panel hinge as optimization design variables and assigning initial values ​​respectively;

[0032] S3, a gradient-based optimization algorithm is used to calculate the relative stiffness of all hinges in combination with the objective function, including the root hinge of the solar wing and all inter-panel hinges;

[0033] S4. Using the expected deployment time of the solar wing, normalize the relative stiffness between all hinges to calculate the stiffness value of each hinge;

[0034] S5. Select the hinge according to the stiffness value of each hinge to obtain the hinge product to be selected corresponding to each hinge;

[0035] S6. In the solar wing deployment model, the structures and stiffness of multiple groups of hinge products to be selected are added to the solar wing deployment model respectively, and simulation calculations are performed to obtain multiple simulation calculation results, and the optimal simulation calculation result is determined from all the simulation calculation results, and a group of hinge products to be selected corresponding to the optimal simulation calculation result is determined as the hinge product finally selected.

[0036] The solar wing can be deployed through several sets of hinges without using a synchronous deployment mechanism and without increasing the weight of the satellite. Moreover, through the simulation of the stiffness of different hinges, it is equivalent to being verified in the design stage, determining the choice of hinge products, improving the reliability of the satellite, and ultimately achieving nearly synchronous deployment of the solar wings.

[0037] Optionally, in the above technical solution, the objective function is a first function, and the first function is: E represents the asynchrony index of the entire deployment process of the solar wing, i represents the i-th preset moment in the deployment process of the solar wing, and E i Indicates that in E i At time k, the asynchrony index of the sun's expansion i Indicates E i The preset weight coefficient N represents the number of preset moments;

[0038] Alternatively, the objective function is the second function, which is:

[0039]

[0040] Wherein, E represents the asynchrony index of the entire deployment process of the solar wing, i represents the i-th preset moment in the deployment process of the solar wing, and E i Indicates that in E i At time k, the asynchrony index of the sun's expansion i Indicates E i The preset weight coefficient, N represents the number of preset moments, λ represents the amplification factor, T s represents the time taken for the solar wing to be fully unfolded obtained through simulation calculation, and T represents the expected unfolding time for the solar wing to be fully unfolded.

[0041] Optionally, in the above technical solution, in S3, the gradient-based optimization algorithm is combined with the objective function to calculate the relative stiffness between all hinges, including:

[0042] When the objective function is the first function, the stiffness of the root hinge is kept unchanged, and the gradient-based optimization algorithm is used until E is optimized to the minimum value, and the relative stiffness between all hinges is obtained;

[0043] Alternatively, when the objective function is the second function, the gradient-based optimization algorithm is used until E is optimized to a minimum value, thereby obtaining the relative stiffness between all hinges.

[0044] Optionally, in the above technical solution, in S4, the relative stiffness between all hinges is normalized using the expected deployment time of the solar wing, and the stiffness value of each hinge is calculated, including:

[0045] S40, using the expected deployment time of the solar wing, and according to the relative stiffness between all hinges, the stiffness of each hinge is enlarged or reduced in the same proportion, and the stiffness value of each hinge is calculated. Specifically:

[0046] Optionally, in the above technical solution, the gradient optimization algorithm is a gradient descent method or a stochastic gradient method.

[0047] Taking a tri-fold solar wing as an example, a satellite solar wing unfolding hinge stiffness optimization method of the present invention is described. The tri-fold solar wing in the folded state is as follows: Figure 2 As shown, the three-fold solar wing is unfolding. Figure 3 As shown, the fully unfolded tri-fold sun wing is as follows Figure 4 As shown:

[0048] The tri-fold solar wing includes three solar wing panels, a solar wing pressing seat and a solar wing hinge, wherein the solar wing panel includes a solar wing substrate and a battery patch, the solar wing pressing seat includes a solar wing pressing and releasing device unit, the solar wing hinge includes a root hinge and an inter-panel hinge, the root hinge and the inter-panel hinge use torsion springs with a certain stiffness coefficient, the tri-fold solar wing includes three groups of hinges, specifically including a group of root hinges and two groups of inter-panel hinges, a group of root hinges includes at least one root hinge, the root hinges in the same group of root hinges are the same, and the inter-panel hinges in the same group of inter-panel hinges are the same.

[0049] The three solar wing panels are respectively recorded as the first solar wing panel, the second solar wing panel and the third solar wing panel. A group of root hinges are evenly arranged on one side of the first solar wing panel, and the other side of the first solar wing panel is connected to the second solar wing panel through a group of evenly arranged inter-panel hinges, and each inter-panel hinge in the group of inter-panel hinges is recorded as the first inter-panel hinge. The other side of the second solar wing panel is connected to the third solar wing panel through a group of evenly arranged inter-panel hinges, and each inter-panel hinge in the group of inter-panel hinges is recorded as the second inter-panel hinge.

[0050] In the present invention, a group of root hinges includes two root hinges, and each group of inter-plate hinges includes two inter-plate hinges, namely, two first inter-plate hinges and two second inter-plate hinges.

[0051] Figure 3In the figure, A1 represents the unfolding angle of the root hinge, 2×A2 represents: the angle between the first solar wing panel and the second solar wing panel, that is, the unfolding angle of the hinge between the first panels, 2×A3 represents: the angle between the second solar wing panel and the third solar wing panel, that is, the unfolding angle of the hinge between the second panels. In this case, after the unfolding is completed, the final unfolding angle of the root hinge is 90°, that is, the maximum value of A1 is 90°, the unfolding angle of the hinge between the first panels and the unfolding angle of the hinge between the second panels are finally 180°, that is, the maximum value of 2×A2 is 180°, the maximum value of 2×A3 is 180°, and the maximum values ​​of A2 and A3 are 90°.

[0052] For the solar wing deployment system of the three-fold solar wing system, if no special design is carried out, the designer will often choose the stiffness of each group of hinges to be close; however, for each group of hinges, the load (moment of inertia) is different, and the entire deployment process path is unpredictable. In the absence of a synchronous deployment mechanism, there is a risk of interference or collision between the solar wing and the satellite cabin and other equipment. The present invention takes the stiffness of the root hinge and the inter-plate hinge as the optimization object, and the approximately synchronous deployment of the solar wing as the optimization design goal, and carries out related optimization design work. Specifically, it includes the following steps:

[0053] S100, modeling the deployment process of a solar wing installed on a satellite, such as a tri-fold solar wing, to obtain a solar wing deployment model, specifically modeling the deployment process of the solar wing by using multi-body dynamics software such as ADAMS or Matlab;

[0054] S101, taking the stiffness of the root hinge of the solar wing and each inter-panel hinge as optimization design variables, and assigning initial values ​​to each of them, and specifically determining the initial value of each hinge based on actual experience;

[0055] S102, designing an objective function according to specific needs. The present invention takes synchronous expansion as a design goal, and this is also true in most cases. Specifically designing an objective function for synchronous expansion optimization;

[0056] The objective function is the first function, which is: E represents the asynchrony index of the entire deployment process of the solar wing, i represents the i-th preset moment in the deployment process of the solar wing, and E i Indicates that in E i At time k, the asynchrony index of the sun's expansion i Indicates E i The preset weight coefficient N represents the number of preset moments;

[0057] Among them, when the solar wing is Figures 2 to 4 When the three-fold solar wing is in i =(A 1 -A 2 )2 +(A 2 -A 3 ) 2 +(A 3 -A 1 ) 2 ;

[0058] When the solar wing is an n-fold solar wing and the final unfolding angle of the root hinge is 90°, the final unfolding angle of all inter-panel hinges is 180°. n is a positive integer, indicating the number of solar panels. When i=n, ​​A i+1 =A 1 .

[0059] In general, it can be considered that in the unfolding process, the closer to the final unfolding state, that is, the fully unfolded state, the smaller the preset weight coefficient is. For example, the preset weight coefficient can be set as a function of time exponential decay, such as the function is: α represents the preset coefficient, which can be set according to actual conditions.

[0060] S103, when the objective function is the first function, the stiffness of the root hinge is kept unchanged, and the gradient-based optimization algorithm is used until E is optimized to a minimum value, and the relative stiffness between all hinges is obtained. All hinges include the root hinge of the solar wing and all inter-panel hinges;

[0061] In other words, the goal of optimization is to minimize E by optimizing the hinge stiffness. Ideally, it is optimized to zero.

[0062] Among them, since the deployment time of the solar wing is uncertain, if all the hinge stiffnesses are optimized variables, there are infinite sets of solutions. Therefore, we fix the root hinge stiffness, that is, keep the stiffness of the root hinge unchanged. At this time, the stiffness of the root hinge is the initial value set in S100. Only the stiffness of the hinges between each plate is optimized until E is optimized to the minimum value, and the relative stiffness between all hinges is obtained.

[0063] S104, using the expected deployment time of the solar wing, normalize the relative stiffness between all hinges, and calculate the stiffness value of each hinge, specifically:

[0064] Using the expected deployment time of the solar wing, according to the relative stiffness between all hinges, the stiffness of each hinge is enlarged or reduced in the same proportion, and the stiffness value of each hinge is calculated. Specifically:

[0065] First, the expected deployment time of the solar wing is T. The relative stiffness of the root hinge is a, the relative stiffness of the first inter-plate hinge is b, and the relative stiffness of the second inter-plate hinge is c. The time taken for the solar wing to be fully deployed is T calculated by simulation. s;

[0066] Then, design the magnification and reduction factor, i.e., the normalization factor m. If T s >T, then m>1; conversely, if T s <T, then m<1. Adjust the stiffness of the root hinge to ma, the stiffness of the first inter-plate hinge to mb, and the stiffness of the second inter-plate hinge to mc in the same proportion. At this time, the time taken for the solar panel to fully deploy obtained through simulation calculation is T s1 , and continue to judge the size relationship between T s1 and T, and then continue to adjust the magnification and reduction factor m.

[0067] By adjusting the magnification and reduction factor, the normalization factor m that achieves the desired deployment time can be finally obtained T , that is, the stiffness value of the root hinge can be obtained as m T a, the stiffness value of the first inter-plate hinge is m T b, and the stiffness value of the second inter-plate hinge is m T c.

[0068] Among them, the optimization algorithm for the gradient is the gradient descent method or the stochastic gradient method, and other gradient algorithms can also be selected according to the actual situation.

[0069] S105. Make corresponding selections according to the stiffness value of each hinge to obtain the candidate hinge products corresponding to each hinge. For example, if the calculated stiffness value of a certain hinge is 190 N*mm / rad, and the stiffness value of the existing hinge product in the current suitable selection is 185 N*mm / rad, then this hinge is determined as the candidate hinge product.

[0070] S106. In the solar panel deployment model, add the structures and stiffnesses of multiple groups of candidate hinge products to the solar panel deployment model respectively, and perform simulation calculations to obtain multiple simulation calculation results. Determine the optimal simulation calculation result from all the simulation calculation results, and determine the group of candidate hinge products corresponding to the optimal simulation calculation result as the finally selected hinge products.

[0071] For example, when the number of candidate hinge products corresponding to the root hinge is two, the same first inter-plate hinge and second inter-plate hinge are selected, and the number of candidate hinge products corresponding to each is two, then there are a total of 4 groups of candidate hinge products, which are:

[0072] The first group includes: the first hinge product to be selected corresponding to the root hinge, the first hinge product to be selected corresponding to the first inter-board hinge and the second inter-board hinge, the second group includes: the first hinge product to be selected corresponding to the root hinge, the second hinge product to be selected corresponding to the first inter-board hinge and the second inter-board hinge, the third group includes: the second hinge product to be selected corresponding to the root hinge, the first hinge product to be selected corresponding to the first inter-board hinge and the second inter-board hinge, the fourth group includes: the second hinge product to be selected corresponding to the root hinge, the second hinge product to be selected corresponding to the first inter-board hinge and the second inter-board hinge.

[0073] The structure and stiffness of each group of hinge products to be selected are added to the solar wing deployment model, and simulation calculations are performed to obtain multiple simulation calculation results. The optimal simulation calculation result is determined from all simulation calculation results. The specific determination process is determined by those skilled in the art according to actual conditions and will not be described in detail here. By simulating the solar wing deployment process, the hinge selection is finally determined according to the results, and sufficient safety margin is ensured.

[0074] At this point, installing the finally selected hinge product on the solar wing can achieve nearly synchronous unfolding of the solar wing with high reliability.

[0075] In another embodiment, when optimizing variables, in principle, all hinge stiffnesses can be optimized variables. In this case, the expected deployment time of the solar wing needs to be taken as an optimization constraint or added to the objective function, and optimization of E can also be achieved. Therefore, S103 can be modified as follows:

[0076] The objective function is the second function, which is:

[0077]

[0078] Wherein, E represents the asynchrony index of the entire deployment process of the solar wing, i represents the i-th preset moment in the deployment process of the solar wing, and E i Indicates that in E i At time k, the asynchrony index of the sun's expansion i Indicates E i The preset weight coefficient, N represents the number of preset moments, λ represents the amplification factor, T s represents the time taken for the solar wing to be fully unfolded obtained through simulation calculation, and T represents the expected unfolding time for the solar wing to be fully unfolded.

[0079] The beneficial effects of the present invention are as follows:

[0080] 1) It can effectively reduce the mass of small satellite solar panels and achieve nearly synchronous deployment, reduce one series unit, and only deploy the solar panels through hinges, thereby improving system reliability;

[0081] 2) By optimizing the hinge design, the solar wing can be deployed almost synchronously, reducing the risk of the deployment process. The hinge stiffness can be automatically analyzed and selected, greatly reducing design iterations. Through multi-body dynamics analysis, the risk of interference or collision between the solar wing and the satellite cabin and other equipment during the deployment process can be evaluated during the design stage.

[0082] In the above embodiments, although the steps are numbered S1, S2, etc., these are only specific embodiments given in the present application. Those skilled in the art may adjust the execution order of S1, S2, etc. according to actual conditions, which is also within the scope of protection of the present invention. It can be understood that in some embodiments, some or all of the above embodiments may be included.

[0083] like Figure 5 As shown, a satellite solar wing deployment hinge stiffness optimization system 200 according to an embodiment of the present invention includes a modeling module 210, a calculation module 220, a normalization module 230, a selection module 240, a simulation module 250 and a determination module 260;

[0084] The modeling module 210 is used to: model the deployment process of the solar wing installed on the satellite to obtain a solar wing deployment model, and use the stiffness of the root hinge of the solar wing and each inter-plate hinge as optimization design variables, and assign initial values ​​to them respectively;

[0085] The calculation module 220 is used to: calculate the relative stiffness between all hinges based on the gradient optimization algorithm and in combination with the objective function, all hinges including the root hinge of the solar wing and all inter-panel hinges;

[0086] The normalization module 230 is used to: perform normalization processing on the relative stiffness between all hinges using the expected deployment time of the solar wing, and calculate the stiffness value of each hinge;

[0087] The selection module 240 is used to: perform corresponding selection according to the stiffness value of each hinge to obtain a hinge product to be selected corresponding to each hinge;

[0088] The simulation module 250 is used to: in the solar wing deployment model, respectively add the structures and stiffnesses of multiple groups of hinge products to be selected to the solar wing deployment model, and perform simulation calculations to obtain multiple simulation calculation results;

[0089] The determination module 260 is used to determine the optimal simulation calculation result from all simulation calculation results, and determine a group of hinge products to be selected corresponding to the optimal simulation calculation result as the hinge products finally selected.

[0090] The solar wing can be deployed through several sets of hinges without using a synchronous deployment mechanism and without increasing the weight of the satellite. Moreover, through the simulation of the stiffness of different hinges, it is equivalent to being verified in the design stage, determining the choice of hinge products, improving the reliability of the satellite, and ultimately achieving nearly synchronous deployment of the solar wings.

[0091] Optionally, in the above technical solution, the objective function is a first function, and the first function is: E represents the asynchrony index of the entire deployment process of the solar wing, i represents the i-th preset moment in the deployment process of the solar wing, and E i Indicates that in E i At time k, the asynchrony index of the sun's expansion i Indicates E i The preset weight coefficient N represents the number of preset moments;

[0092] Alternatively, the objective function is the second function, which is:

[0093]

[0094] Wherein, E represents the asynchrony index of the entire deployment process of the solar wing, i represents the i-th preset moment in the deployment process of the solar wing, and E i Indicates that in E i At time k, the asynchrony index of the sun's expansion i Indicates E i The preset weight coefficient, N represents the number of preset moments, λ represents the amplification factor, T s represents the time taken for the solar wing to be fully unfolded obtained through simulation calculation, and T represents the expected unfolding time for the solar wing to be fully unfolded.

[0095] Optionally, in the above technical solution, the calculation module is specifically used for:

[0096] When the objective function is the first function, the stiffness of the root hinge is kept unchanged, and the gradient-based optimization algorithm is used until E is optimized to the minimum value, and the relative stiffness between all hinges is obtained;

[0097] Alternatively, when the objective function is the second function, the gradient-based optimization algorithm is used until E is optimized to a minimum value, thereby obtaining the relative stiffness between all hinges.

[0098] Optionally, in the above technical solution, the normalization module is specifically used for:

[0099] Using the expected deployment time of the solar wing and the relative stiffness between all hinges, the stiffness of each hinge is enlarged or reduced in the same proportion to calculate the stiffness value of each hinge.

[0100] Optionally, in the above technical solution, the gradient optimization algorithm is a gradient descent method or a stochastic gradient method.

[0101] The above-mentioned parameters and steps for each unit module to implement the corresponding functions in the satellite solar wing deployment hinge stiffness optimization system 200 of the present invention can refer to the parameters and steps in the embodiment of a satellite solar wing deployment hinge stiffness optimization method above, and will not be repeated here.

[0102] An electronic device according to an embodiment of the present invention comprises a memory, a processor and a program stored in the memory and running on the processor, wherein when the processor executes the program, the steps of any of the above-mentioned methods for optimizing the stiffness of a satellite solar wing unfolding hinge are implemented.

[0103] Among them, the electronic device can be a computer, a mobile phone, etc., and correspondingly, its program is a computer software or a mobile phone APP, etc., and the above-mentioned parameters and steps in an electronic device of the present invention can refer to the parameters and steps in the embodiment of a satellite solar wing deployment hinge stiffness optimization method mentioned above, which will not be repeated here.

[0104] Those skilled in the art will appreciate that the present invention may be implemented as a system, method or computer program product.

[0105] Therefore, the present disclosure may be specifically implemented in the following forms, namely: it may be completely hardware, it may be completely software (including firmware, resident software, microcode, etc.), or it may be a combination of hardware and software, generally referred to herein as a "circuit", "module" or "system". In addition, in some embodiments, the present invention may also be implemented in the form of a computer program product in one or more computer-readable media, and the computer-readable medium contains computer-readable program code.

[0106] Any combination of one or more computer-readable media can be used. Computer-readable media can be computer-readable signal media or computer-readable storage media. Computer-readable storage media can be, for example, but not limited to, electrical, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices or devices, or any combination of the above. More specific examples (non-exhaustive list) of computer-readable storage media include: electrical connections with one or more wires, portable computer disks, hard disks, random access memories (RAM), read-only memories (ROM), erasable programmable read-only memories (EPROM or flash memory), optical fibers, portable compact disk read-only memories (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination of the above. In this document, computer-readable storage media can be any tangible medium containing or storing a program, which can be used by an instruction execution system, device or device or used in combination with it.

[0107] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A satellite solar wing deployment hinge stiffness optimization method, characterized in that: include: Modeling the deployment process of a solar wing installed on a satellite to obtain a solar wing deployment model; The stiffness of the root hinge of the solar wing and each inter-panel hinge is taken as an optimization design variable and assigned with initial values ​​respectively; A gradient-based optimization algorithm is used to calculate the relative stiffness of all hinges, including the root hinge of the solar wing and all inter-panel hinges, in combination with the objective function. Using the expected deployment time of the solar wing, the relative stiffness between all hinges is normalized to calculate the stiffness value of each hinge; According to the stiffness value of each hinge, corresponding selection is made to obtain the hinge products to be selected corresponding to each hinge; In the solar wing deployment model, the structures and stiffness of multiple groups of hinge products to be selected are added to the solar wing deployment model respectively, and simulation calculations are performed to obtain multiple simulation calculation results, and the optimal simulation calculation result is determined from all the simulation calculation results, and a group of hinge products to be selected corresponding to the optimal simulation calculation result is determined as the hinge product finally selected; The objective function is a first function, which is: E represents the asynchrony index of the entire deployment process of the solar wing, i represents the i-th preset moment in the deployment process of the solar wing, and E i Indicates that in E i At time k, the asynchrony index of the sun's expansion i Indicates E i The preset weight coefficient N represents the number of preset moments; Alternatively, the objective function is a second function, and the second function is: Wherein, E represents the asynchrony index of the entire deployment process of the solar wing, i represents the i-th preset moment in the deployment process of the solar wing, and E i Indicates that in E i At time k, the asynchrony index of the sun's expansion i Indicates E i The preset weight coefficient, N represents the number of preset moments, λ represents the amplification factor, T s represents the time taken for the solar wing to be fully unfolded obtained through simulation calculation, and T represents the expected unfolding time for the solar wing to be fully unfolded.

2. A satellite solar wing deployment hinge stiffness optimization method according to claim 1, characterized in that: A gradient-based optimization algorithm is used to calculate the relative stiffness between all hinges in combination with an objective function, including: When the objective function is the first function, the stiffness of the root hinge is kept unchanged, and the gradient-based optimization algorithm is used until E is optimized to a minimum value, thereby obtaining the relative stiffness between all hinges; Alternatively, when the objective function is the second function, the gradient-based optimization algorithm is used until E is optimized to a minimum value, thereby obtaining the relative stiffness between all hinges.

3. A satellite solar wing deployment hinge stiffness optimization method according to any one of claims 1 to 2, characterized in that: Using the expected deployment time of the solar wing, the relative stiffness between all hinges is normalized to calculate the stiffness value of each hinge, including: By using the expected unfolding time of the solar wing and according to the relative stiffness between all hinges, the stiffness of each hinge is enlarged or reduced in the same proportion, and the stiffness value of each hinge is calculated.

4. A satellite solar wing deployment hinge stiffness optimization method according to any one of claims 1 to 2, characterized in that: The gradient optimization algorithm is a gradient descent method or a stochastic gradient method.

5. A satellite solar wing deployment hinge stiffness optimization system, characterized in that: It includes modeling module, calculation module, normalization module, selection module, simulation module and determination module; The modeling module is used to: model the deployment process of the solar wing installed on the satellite to obtain a solar wing deployment model, and use the stiffness of the root hinge of the solar wing and each inter-plate hinge as optimization design variables, and assign initial values ​​to each of them; The calculation module is used to: calculate the relative stiffness between all hinges based on the gradient optimization algorithm and in combination with the objective function, all hinges including the root hinge of the solar wing and all inter-panel hinges; The normalization module is used to: perform normalization processing on the relative stiffness between all hinges using the expected unfolding time of the solar wing, and calculate the stiffness value of each hinge; The selection module is used to: perform corresponding selection according to the stiffness value of each hinge to obtain a hinge product to be selected corresponding to each hinge; The simulation module is used to: in a solar wing deployment model, add the structures and stiffnesses of multiple groups of hinge products to be selected to the solar wing deployment model, perform simulation calculations, and obtain multiple simulation calculation results; The determination module is used to: determine the optimal simulation calculation result from all simulation calculation results, and determine a group of hinge products to be selected corresponding to the optimal simulation calculation result as the hinge products finally selected; The objective function is a first function, which is: E represents the asynchrony index of the entire deployment process of the solar wing, i represents the i-th preset moment in the deployment process of the solar wing, and E i Indicates that in E i At time k, the asynchrony index of the sun's expansion i Indicates E i The preset weight coefficient N represents the number of preset moments; Alternatively, the objective function is a second function, and the second function is: Wherein, E represents the asynchrony index of the entire deployment process of the solar wing, i represents the i-th preset moment in the deployment process of the solar wing, and E i Indicates that in E i At time k, the asynchrony index of the sun's expansion i Indicates E i The preset weight coefficient, N represents the number of preset moments, λ represents the amplification factor, T s represents the time taken for the solar wing to be fully unfolded obtained through simulation calculation, and T represents the expected unfolding time for the solar wing to be fully unfolded.

6. A satellite solar wing deployment hinge stiffness optimization system according to claim 5, characterized in that: The calculation module is specifically used for: When the objective function is the first function, the stiffness of the root hinge is kept unchanged, and the gradient-based optimization algorithm is used until E is optimized to a minimum value, thereby obtaining the relative stiffness between all hinges; Alternatively, when the objective function is the second function, the gradient-based optimization algorithm is used until E is optimized to a minimum value, thereby obtaining the relative stiffness between all hinges.

7. A satellite solar wing deployment hinge stiffness optimization system according to any one of claims 5 to 6, characterized in that: The normalization module is specifically used for: By using the expected unfolding time of the solar wing and according to the relative stiffness between all hinges, the stiffness of each hinge is enlarged or reduced in the same proportion, and the stiffness value of each hinge is calculated.

8. A satellite solar wing deployment hinge stiffness optimization system according to any one of claims 5 to 6, characterized in that: The gradient optimization algorithm is a gradient descent method or a stochastic gradient method.

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