Multidisciplinary Optimization Design Method for Overall Parameters of Space Solar Power Station

Abstract

This invention relates to a multidisciplinary optimization design method for the overall parameters of a space solar power station. Based on the space-to-ground energy conversion efficiency chain, it comprehensively analyzes the data transmission and coupling relationships between various disciplines within the space solar power station system, establishes a multidisciplinary design optimization framework and coupling relationship models for each discipline, and fully utilizes the synergistic effects generated by the interactions between different disciplines to perform hierarchical, multi-objective, and multidisciplinary iterative optimization design of the space solar power station system. By integrating knowledge from various disciplines during the design process of the space solar power station system, consolidating complex design parameters, applying effective optimization design strategies, and organizing and managing the design process, the overall optimal solution of the system is obtained, achieving weight reduction, efficiency improvement, and optimized design of the final scheme. This enables experimental verification of the space solar power station through simulation and ground-based tests.

Description

Technical Field

[0001] This invention relates to the field of space solar power stations, specifically to a multidisciplinary optimization design method for the overall parameters of a space solar power station. Background Technology

[0002] Energy is a major global challenge, and humanity urgently needs to develop inexhaustible and clean energy sources. Solar energy, as a renewable and clean energy source, will become an important way to solve future energy and environmental problems. Compared to terrestrial solar energy, space-based solar energy is not affected by seasons or day-night cycles, receives higher energy density, is unaffected by the atmosphere, and can stably transmit energy to the ground, making it more suitable for large-scale development and utilization.

[0003] Space-based solar power stations are power systems that convert solar energy into electricity in Earth orbit and then transmit it wirelessly to the ground for users. They can provide sustainable and clean energy that is not affected by seasons, weather, or day and night, and are of great significance for solving future energy problems.

[0004] However, space solar power stations are extremely complex, multidisciplinary, and ultra-large-scale engineering systems involving numerous disciplines such as structure, control, power, energy, microwave, and environment. The design of each discipline is complex and they influence each other. In addition, there are a large number of design variables and constraints, making it extremely difficult to effectively organize the various disciplines to conduct comprehensive optimization design of space solar power stations. It is almost impossible to achieve this using traditional optimization design methods. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention proposes a multidisciplinary optimization design method for the overall parameters of a space solar power station based on the full efficiency chain conversion of space-to-ground energy. Taking the maximum efficiency-to-mass ratio (efficiency / mass) of the space solar power station as the optimization objective, and under the premise of keeping the ground-received power constant, the method performs hierarchical, multi-objective, and multi-disciplinary iterative optimization of various system parameters in each discipline of the overall scheme of the space solar power station to obtain the overall optimal solution of the system, thereby obtaining the overall system design index that meets the above optimization objectives.

[0006] To achieve the above-mentioned objectives of this invention, an embodiment of this invention proposes a multidisciplinary optimization design method for the overall parameters of a space solar power station, comprising:

[0007] S1, establish a full-efficiency chain for space-based solar power stations based on sky-to-ground energy conversion;

[0008] S2, analyze the data transmission and coupling relationships between various disciplines in space solar power stations, and establish a multidisciplinary design optimization framework;

[0009] S3. Under the premise that the ground-received electrical power remains unchanged, the input and output parameters of each discipline are analyzed to obtain the coupling relationship between numerous parameters, as well as the relationship between the change of each parameter and the change of the efficiency / quality ratio of the space solar power station system, and a coupling relationship model of each discipline is established.

[0010] S4 involves performing independent local optimization on each discipline, and using the indicators related to the overall power plant design in the optimization results as input parameters for the overall global optimization of the system.

[0011] S5 uses the maximum efficiency-to-quality ratio of the space solar power station as the objective function, the coupling relationship between various disciplines as the constraint condition, and a co-evolutionary multidisciplinary design optimization algorithm to optimize the system globally.

[0012] S6, take the optimization result obtained in S5 as input, and perform local and global optimization on each subject again according to S4 and S5. After multiple iterations, until the overall global optimization efficiency-quality ratio result stability is ≤1%, thereby obtaining the optimal overall design parameter index.

[0013] S7. Based on the optimal overall design parameter index, calculate other overall design parameters and subject parameters for use in the overall parameter design scheme of the space solar power station.

[0014] In a preferred embodiment of the present invention, the total transmission efficiency η of the space solar power station full efficiency chain is: η = η1·η2·η3·η4·η5; where η1 is the solar power conversion efficiency, η2 is the space power transmission efficiency, η3 is the conversion efficiency from electrical energy to microwave / laser, η4 is the microwave / laser transmission efficiency, and η5 is the ground energy interception efficiency.

[0015] In a preferred embodiment of the present invention, η1 is determined by the properties of the solar panel; η3 is determined by the properties of the power-to-microwave conversion device; η4 is determined by the properties of the equipment during transmission, space particles, and the properties of the Earth's atmosphere. In the design process of a space solar power station, η1, η3, and η4 are constants; η2 and η5 are related to the design parameters of the space solar power station, and both determine the overall power generation efficiency. When η2 and η5 change, the various design parameters of the space solar power station also change, resulting in a change in the total weight of the space solar power station. An increase in η2 will cause a decrease in the total area of ​​the solar array and an increase in the total weight of the power reliability equipment. An increase in η5 will cause a decrease in the total area of ​​the solar array, a decrease in the total area of ​​the transmitting antenna, and an increase in the required ground-oriented control accuracy, leading to an increase in fuel consumption.

[0016] In a preferred embodiment of the present invention, the discipline with data transmission and coupling relationship in the space solar power station refers to the various space solar power station subsystems associated with it.

[0017] In a preferred embodiment of the present invention, the optimization results include the following indicators related to the overall design of the power plant: transmitting antenna area, transmitting antenna mass, antenna control accuracy, battery array control accuracy, fuel consumption mass, solar cell array area, solar cell array mass, space power transmission efficiency, and ground energy interception efficiency.

[0018] In a preferred embodiment of the present invention, the co-evolutionary multidisciplinary design optimization algorithm is as follows:

[0019] Minimize: F=f(f1(X,X1,u1)f2(X,X2,u2)f3(X,X3,u3),f4(X,X4,u4)f5(X,X5,u5))

[0020]

[0021] Among them, f i It is the i-th subsystem with data transmission and coupling relationships; u i y is the state variable vector of the i-th subsystem; ij It is the coupling function between the i-th and j-th subsystems; g i h i E is the coupling parameter of the i-th subsystem; i X is the constraint function of the i-th subsystem; X is the input variable of the subsystem.

[0022] In a preferred embodiment of the present invention, the stability of the performance-quality ratio result is calculated based on its root mean square error. When the stability is ≤1%, the optimal overall design parameter index is obtained, as follows:

[0023]

[0024] Where s is the stability, x i This is the result of the i-th global optimization.

[0025] In a preferred embodiment of the present invention, the optimal overall design parameters include total mass, total power generation efficiency, total area of ​​transmitting antenna, total area of ​​solar cell array, space power transmission efficiency, and ground interception efficiency.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] (1) Based on the full efficiency chain of space-to-ground energy conversion, a comprehensive analysis of the data transmission and coupling relationship between various disciplines in the space solar power station system is conducted. A multi-disciplinary design optimization framework and a coupling relationship model of each discipline are established. The synergistic effect generated by the interaction between different disciplines is fully utilized to carry out hierarchical, multi-objective, and multi-disciplinary iterative optimization design of the space solar power station system.

[0028] (2) By integrating knowledge from various disciplines, integrating complex design parameters, applying effective optimization design strategies, organizing and managing the design process during the design process of space solar power station system, the overall optimal solution of the system can be obtained, weight reduction, efficiency improvement and optimization design of the final scheme can be achieved, and then the experimental verification work of space solar power station can be carried out through simulation and ground test. Attached Figure Description

[0029] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1 This is a flowchart illustrating the multidisciplinary optimization design method for overall parameters of a space solar power station according to an embodiment of the present invention.

[0031] Figure 2 This is a schematic diagram of the structure of a space solar power station according to an embodiment of the present invention;

[0032] Figure 3 This is a coupling diagram of the various subsystems of the space solar power station according to an embodiment of the present invention;

[0033] Figure 4 This is a diagram showing the parameter transfer and coupling relationships in each subsystem of this invention.

[0034] Figure 5 This is a structural diagram of the co-evolutionary multidisciplinary design optimization algorithm according to an embodiment of the present invention. Detailed Implementation

[0035] The description of the embodiments in this specification should be taken in conjunction with the accompanying drawings, which should form part of the complete specification. In the drawings, the shape or thickness of the embodiments may be exaggerated and may be indicated in a simplified or convenient manner. Furthermore, parts of the various structures in the drawings will be described separately; it is worth noting that elements not shown in the figures or not described in words are in a form known to those skilled in the art.

[0036] The descriptions of the embodiments herein, including any references to directions and orientations, are for ease of description only and should not be construed as limiting the scope of the invention. The following description of preferred embodiments involves combinations of features, which may exist independently or in combination; the invention is not particularly limited to the preferred embodiments. The scope of the invention is defined by the claims.

[0037] like Figure 1As shown, the multidisciplinary optimization design method for overall parameters of a space solar power station according to an embodiment of the present invention includes:

[0038] S1, establish a full-efficiency chain for space-based solar power stations based on space-to-ground energy conversion.

[0039] The structure of the space solar power station is as follows: Figure 2 As shown, the total transmission efficiency η of the entire efficiency chain of the space solar power station is:

[0040] η = η1·η2·η3·η4·η5

[0041] In the formula, η1 is the solar power conversion efficiency, η2 is the space power transmission efficiency, η3 is the conversion efficiency from electrical energy to microwave / laser, η4 is the microwave / laser transmission efficiency, and η5 is the ground energy interception efficiency.

[0042] η1 is determined by the properties of the solar panel; η3 is determined by the properties of the power-to-microwave conversion device; η4 is determined by the properties of the equipment (such as microwave transmitting antennas) during transmission, space particles, and the properties of the Earth's atmosphere. In the design process of a space solar power station, once the above equipment is selected, η1, η3, and η4 become constants.

[0043] η2 and η5 are related to the design parameters of the space solar power station, and they determine the overall power generation efficiency. When η2 and η5 change, the various design parameters of the space solar power station also change, resulting in a change in the total weight of the space solar power station.

[0044] An increase in η2 will cause: ① a decrease in the total area of ​​the solar cell array; ② an increase in the total weight of the power reliability equipment.

[0045] An increase in η5 will cause: ① a decrease in the total area of ​​the solar array; ② a decrease in the total area of ​​the transmitting antenna; ③ an increase in fuel consumption due to the increased requirement for precise ground-based directional control.

[0046] S2 analyzes the data transmission and coupling relationships between various disciplines in space solar power plants and establishes a multidisciplinary design optimization framework.

[0047] Among them, the disciplines related to data transmission and coupling in space solar power stations refer to the various space solar power station subsystems.

[0048] S3, under the premise that the ground-received electrical power remains unchanged, analyzes the input and output parameters of each discipline, obtains the coupling relationship between numerous parameters, and the relationship between the change of each parameter and the change of the efficiency / quality ratio of the space solar power station system, and establishes a coupling relationship model for each discipline.

[0049] S4 performs independent local optimization on each discipline, and uses the indicators related to the overall power plant design in the optimization results as input parameters for the overall global optimization of the system.

[0050] Among the optimization results, the indicators related to the overall design of the power station include: transmitting antenna area, transmitting antenna mass, antenna control accuracy, battery array control accuracy, fuel consumption mass, solar cell array area, solar cell array mass, space power transmission efficiency, and ground energy interception efficiency.

[0051] S5 uses the maximum efficiency-to-mass ratio of the space solar power station as the objective function and the coupling relationship between various disciplines as the constraint condition. It employs a co-evolutionary multidisciplinary design optimization algorithm to perform global optimization of the system.

[0052] The co-evolutionary multidisciplinary design optimization algorithm is as follows:

[0053] Minimize: F=f(f1(X,X1,u1),f2(X,X2,u2),f3(X,X3,u3)f4(X,X4,u4),f5(X,X5,u5))

[0054]

[0055] Among them, f i It is the i-th subsystem with data transmission and coupling relationships; u i y is the state variable vector of the i-th subsystem (i = j = 1, 2, 3, 4, 5; i ≠ j); ij It is the coupling function between the i-th and j-th subsystems; g i h i E is the coupling parameter of the i-th subsystem; i X is the constraint function of the i-th subsystem; X is the input variable of the subsystem.

[0056] S6. Using the optimization results obtained in S5 as input, perform local and global optimization on each subject again according to S4 and S5. After multiple iterations, until the overall global optimization efficiency-quality ratio stability is ≤1%, thereby obtaining the optimal overall design parameter index.

[0057] The stability of the performance-quality ratio result is calculated based on its root mean square error. When the stability is ≤1%, the optimal overall design parameter index is obtained, as follows:

[0058]

[0059] Where s is the stability, x i This is the result of the i-th global optimization.

[0060] The optimal overall design parameters include total mass, total power generation efficiency, total area of ​​transmitting antenna, total area of ​​solar array, space power transmission efficiency, and ground interception efficiency.

[0061] S7. Based on the optimal overall design parameter index, calculate other overall design parameters and subject parameters for use in the overall parameter design scheme of the space solar power station.

[0062] like Figure 3 The image shown illustrates a typical embodiment of a MW-level space solar power station structure based on the multidisciplinary optimization design method for overall parameters of a space solar power station according to the present invention. The following description, in conjunction with... Figure 2 This method will be explained in detail.

[0063] First, based on the design of a MW-level space solar power plant, the factors affecting the plant's quality and power generation efficiency are analyzed. This analysis ultimately identifies the interconnected subsystems, including: a solar energy collection and conversion subsystem, a power transmission and management subsystem, a microwave wireless power transmission subsystem, an attitude and orbit control subsystem, and a structural subsystem. The coupling relationships between these subsystems are as follows: Figure 4 As shown.

[0064] Assuming the ground-received power is maintained at 1MW, the input and output parameters of each discipline are analyzed to obtain the coupling relationships between numerous parameters, as well as the relationship between the change of each parameter and the change of the power plant system efficiency / quality ratio, thus establishing a coupling relationship model for each discipline. The coupling relationships between the parameters of each subsystem are as follows: Figure 5 As shown.

[0065] Based on the above analysis, a multidisciplinary optimization design for the overall mission of a space-based solar power station can be performed. Since the parameters of the coupled subsystems mentioned above are interrelated, this optimization problem is a collaborative process involving multiple disciplines.

[0066] Then, the results of independent local optimization of each discipline, including: transmitting antenna area, transmitting antenna mass, antenna control accuracy, battery array control accuracy, fuel consumption mass, solar cell array area, solar cell array mass, space power transmission efficiency, and ground interception efficiency, are used as input parameters for the overall global optimization of the system. The objective function is the maximum efficiency / mass ratio of the space solar power station, with the coupling relationships between disciplines as constraints. A co-evolutionary multidisciplinary design optimization algorithm is then used to perform global optimization of the system.

[0067] The aforementioned co-evolutionary multidisciplinary design optimization algorithm, based on threshold decomposition, decomposes the complex coupled system of a space-based solar power station into a multidisciplinary system where each subsystem is relatively independent and maintains autonomy. It employs an implicit iterative strategy to coordinate the coupling consistency constraints between the subsystems. Specifically... Figure 5The complex coupled system co-evolutionary multidisciplinary design optimization algorithm shown constructs five subsystem species populations (P1, P2, P3, P4, P5) and a system solution population (Pe) to execute the algorithm. Individuals in each population (P1, P2, P3, P4, P5) represent partial solutions. Within these five populations, individuals are independent but cooperate in the evolutionary process. e Composed of five cooperating subsystems, representing the system solution, it carries the genomes of the individuals of the five subsystem species, P e Individuals in P1 compete with individuals in P2, P3, P4, and P5. While P1, P2, P3, P4, and P5 evolve independently, P... e Within the population, they continue to combine to form candidate solutions with the highest system efficiency-to-quality ratio.

[0068] Finally, when the candidate solutions satisfy the aforementioned stability ≤ 1%, the optimal overall design parameters are obtained, including: total mass, total power generation efficiency, transmitting antenna area, total solar array area, space power transmission efficiency, and ground interception efficiency. Based on the optimal overall design parameters, other overall design parameters and subject-specific parameters are calculated.

[0069] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A multidisciplinary optimization design method for the overall parameters of a space-based solar power station, characterized in that, The method includes: S1, establish a full-efficiency chain for space-based solar power stations based on sky-to-ground energy conversion; S2, analyze the data transmission and coupling relationships between various disciplines in space solar power stations, and establish a multidisciplinary design optimization framework; S3. Under the premise that the ground-received electrical power remains unchanged, the input and output parameters of each discipline are analyzed to obtain the coupling relationship between many parameters, as well as the relationship between the change of each parameter and the change of the efficiency-quality ratio of the space solar power station system, and a coupling relationship model of each discipline is established. S4 involves performing independent local optimization on each discipline, and using the indicators related to the overall power plant design in the optimization results as input parameters for the overall global optimization of the system. S5 uses the maximum efficiency-to-quality ratio of the space solar power station as the objective function, the coupling relationship between various disciplines as the constraint condition, and a co-evolutionary multidisciplinary design optimization algorithm to optimize the system globally. S6, taking the optimization results obtained in S5 as input, perform local and global optimization on each subject again according to S4 and S5. After multiple iterations, until the overall global optimization efficiency-quality ratio result stability is ≤1%, thereby obtaining the optimal overall design parameter index. S7. Based on the optimal overall design parameter index, calculate other overall design parameters and subject parameters for use in the overall parameter design scheme of the space solar power station. In S1, the total transmission efficiency of the space solar power station's full-efficiency chain for: ; in, For solar power conversion efficiency, For space power transmission efficiency, To determine the conversion efficiency from electrical energy to microwave / laser, For microwave / laser transmission efficiency, For ground energy interception efficiency; In S1, Determined by the properties of the solar panel; Determined by the properties of the power-to-microwave conversion device; The characteristics of the equipment, space particles, and Earth's atmospheric properties during transmission are determined by these factors; in the design of space solar power stations, , , It is a constant; and Related to the design parameters of the space-based solar power station, both of which determine the overall power generation efficiency; when and When changes occur, the various design parameters of the space solar power station also change, resulting in changes in the total weight of the space solar power station. Adding more solar panels will reduce the total area of ​​the solar array and increase the total weight of the power reliability equipment. Adding to the solar array will reduce the total area of ​​the solar cell array, reduce the total area of ​​the transmitting antenna, and increase the required accuracy of ground-oriented control, leading to increased fuel consumption. In S2, the disciplines with data transmission and coupling relationships in the space solar power station refer to the various space solar power station subsystems related to it.

2. The multidisciplinary optimization design method for overall parameters of a space solar power station according to claim 1, characterized in that, In S4, the optimization results include the following indicators related to the overall design of the power station: transmitting antenna area, transmitting antenna mass, antenna control accuracy, battery array control accuracy, fuel consumption mass, solar cell array area, solar cell array mass, space power transmission efficiency, and ground energy interception efficiency.

3. The multidisciplinary optimization design method for overall parameters of a space solar power station according to claim 1, characterized in that, In step S6, the stability of the performance-quality ratio result is calculated based on its root mean square error. When the stability is ≤1%, the optimal overall design parameter index is obtained, as follows: in, For stability, x i This is the result of the i-th global optimization.

4. The multidisciplinary optimization design method for overall parameters of a space solar power station according to claim 1, characterized in that, The optimal overall design parameters include total mass, total power generation efficiency, total area of ​​transmitting antenna, total area of ​​solar array, space power transmission efficiency, and ground interception efficiency.

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