Construction method of rapid spacecraft power supply and distribution system, medium and system

Abstract

The invention provides a rapid spacecraft power supply and distribution system construction method, medium and system, and the method comprises the steps: analyzing the demand index of a spacecraft power supply and distribution system according to a spacecraft development and design report; establishing a power supply and distribution type spectrum library according to requirements and type spectrum parameter indexes; matching and setting a profile spectrum according to the demand index and a power supply and distribution profile spectrum library; according to the demand indexes, the feasibility of profile spectrum setting is judged; establishing a power supply and distribution product library according to the spacecraft power supply and distribution products and the parameter indexes; selecting and distributing products according to a power pattern spectrum setting scheme and a power supply and distribution product library; and judging the feasibility of the product matching scheme, and constructing a system or re-matching until the index requirements are met. The method can cope with the characteristic of long link of the spacecraft power supply and distribution system, greatly accelerates and standardizes the overall design of the spacecraft power supply and distribution system under the condition of ensuring the reliability of the spacecraft power supply and distribution system, shortens the overall development period of the spacecraft, optimizes the system construction, ensures the long-term stable operation of the spacecraft, and completes the transformation of the power supply and distribution development mode.

Description

Technical Field

[0001] The present invention belongs to the field of spacecraft power supply and distribution systems, and specifically, relates to a construction method, medium and system of a rapid spacecraft power supply and distribution system, and in particular, to an overall construction method of a rapid spacecraft power supply and distribution system. Background Art

[0002] Driven by the development of new technologies and diversified needs for spacecraft, the number of spacecraft is increasing, the development cycle of spacecraft is shortening, and the complexity of power supply and distribution systems and products is increasing. At the current stage, with the development cycle of spacecraft power supply and distribution systems and products becoming shorter and shorter, and the development complexity becoming higher and higher, the traditional spacecraft power supply and distribution design method has the problems of low efficiency of manual design, difficult to quantify and reference the high coupling relationship between model setting and product selection, and a gap between empirical design and optimal solution design, which leads to problems such as tight development tasks, waste of product design resources, and rising development and production costs. In order to cope with the long link characteristics of the spacecraft power supply and distribution system and solve the problem of low efficiency of overall solution design, the power supply and distribution development model urgently needs to be transformed.

[0003] The power supply and distribution system of spacecraft has many products and complex parameters. The bottom-up method of building the power supply and distribution system is complicated and has poor integrity, which cannot adapt to the long link characteristics of the power supply and distribution system of spacecraft. The overall plan based on simulation needs to first establish a full-link digital model, and then the overall plan can be determined after simulation and testing meet the indicators. This construction method has high accuracy, but the initial workload is large and the design efficiency is low, which cannot meet the needs of the ever-shortening spacecraft development cycle.

[0004] According to research, rapid overall plan construction for spacecraft power supply and distribution systems is an effective way to solve these problems. Rapid overall construction of spacecraft power supply and distribution systems includes model spectrum setting and product selection. In order to ensure the long-term reliable operation of spacecraft power supply and distribution systems, these designs must be based on highly mature model spectrum structures and products and guided by the optimal solution method. Therefore, how to quickly and efficiently carry out the overall construction of spacecraft power supply and distribution systems is an important way to optimize the system structure, ensure the long-term stable operation of spacecraft, and complete the transformation of power supply and distribution research and development models. Summary of the invention

[0005] In view of the defects in the prior art, the object of the present invention is to provide a method, medium and system for constructing a rapid spacecraft power supply and distribution system.

[0006] The method for constructing a rapid spacecraft power supply and distribution system provided by the present invention comprises:

[0007] Step S1: Analyze the demand indicators of the spacecraft power supply and distribution system according to the spacecraft development and design report;

[0008] Step S2: Establish a power supply and distribution spectrum library according to demand and spectrum parameter indicators;

[0009] Step S3: Setting the spectrum according to the demand index and the power supply and distribution spectrum library to obtain a spectrum setting plan;

[0010] Step S4: judging the feasibility of the spectrum setting scheme according to the demand indicators;

[0011] Step S5: Establish a power supply and distribution product library according to spacecraft power supply and distribution products and their parameter indicators;

[0012] Step S6: Select products according to the model spectrum setting plan and the power supply and distribution product library to obtain a product selection plan;

[0013] Step S7: According to the demand indicators, determine the feasibility of the product selection plan and complete the construction.

[0014] Preferably, the spacecraft power supply and distribution system demand indicators in step S1 include orbital altitude, platform power, bus topology and bus voltage.

[0015] In step S2, based on the specific spectrum parameters involved in the development of various types of spacecraft, the spectrum parameters are classified and summarized in combination with the development requirements;

[0016] The spectrum parameter indicators include track height classification, platform power range, bus system topology and bus voltage range.

[0017] The power supply and distribution product library in step S5 includes electrical parameter indicators of mechanical solar wings, solar cells, solar wing drive mechanisms, power controllers, batteries, power converters, battery equalizers and distributors.

[0018] In the step S4, if the demand indicators are met, the product is constructed; if the demand indicators are not met, the plan is modified and the model spectrum is re-set until the demand indicators are met.

[0019] In step S7, if it is determined that the demand indicators are met, the construction is completed; if the demand indicators are not met, a new product is put into storage and the product selection is re-performed until the demand indicators are met.

[0020] Preferably, in step S3, the spectrum setting variable based on the current demand parameter of power supply and distribution and other demand parameters are coupled with variables that jointly determine the spectrum setting target quantization function;

[0021] The spectrum of step S3 is set to optimize the solution of the demand parameters, including:

[0022] make Find the solution that satisfies p0(x desn ,y coup)≤0 and q0(x desn ,y coup )=0, the minimum value of f;

[0023] Among them, f is the spectrum setting target;

[0024] n is the total amount of demand parameters;

[0025] f i Set the target for the spectrum of the i-th demand parameter;

[0026] x desn Set variables for the spectrum of required parameters;

[0027] y coup Coupling variables of spectrum setting variables and other required parameters;

[0028] p0 and q0 are the inequality constraint and equality constraint set by the spectrum respectively.

[0029] Preferably, in step S6, the product matching, matching inequality and equality constraints are selected based on the matching selection variables depending on the product matching and the coupling variables between the matching selection variables and other products;

[0030] The product selection is to optimize the product selection, including:

[0031] make Solve the problem of satisfying m0(z desn ,h coup )≤0 and n0(z desn ,h coup )=0, the minimum value of c;

[0032] Among them, c is the product selection target;

[0033] N is the number of products;

[0034] c i The product selection target for the i-th product;

[0035] z desn The optional variants for matching products;

[0036] h coup It is the coupling variable between the matching option variable and other products;

[0037] m0 and n0 are the inequality constraints and equality constraints for product matching selection respectively.

[0038] A system for constructing a rapid spacecraft power supply and distribution system according to the present invention comprises:

[0039] Module M1: Analyze the demand indicators of the spacecraft power supply and distribution system according to the spacecraft development and design report;

[0040] Module M2: Establish a power supply and distribution spectrum library based on demand and spectrum parameter indicators;

[0041] Module M3: Set the spectrum according to the demand index and the power supply and distribution spectrum library to obtain the spectrum setting plan;

[0042] Module M4: Determine the feasibility of the spectrum setting plan based on demand indicators;

[0043] Module M5: Establish a power supply and distribution product library based on spacecraft power supply and distribution products and their parameter indicators;

[0044] Module M6: Select products according to the spectrum setting plan and the power supply and distribution product library to obtain a product selection plan;

[0045] Module M7: Determine the feasibility of product options based on demand indicators and complete the construction.

[0046] Preferably, the spacecraft power supply and distribution system demand indicators in the module M1 include orbital altitude, platform power, bus topology and bus voltage;

[0047] The module M2 classifies and summarizes the spectrum parameters based on the specific spectrum parameters involved in the development of various types of spacecraft and in combination with the development requirements;

[0048] The spectrum parameter indicators include track height classification, platform power range, busbar system topology and busbar voltage range;

[0049] The power supply and distribution product library in the module M5 includes electrical parameter indicators of mechanical solar wings, solar cells, solar wing drive mechanisms, power controllers, batteries, power converters, battery equalizers and distributors;

[0050] In the step S4, if it is determined that the demand indicators are met, the product is constructed; if the demand indicators are not met, the plan is modified and the spectrum is re-set until the demand indicators are met;

[0051] In step S7, if it is determined that the demand indicators are met, the construction is completed; if the demand indicators are not met, a new product is put into storage and the product selection is re-performed until the demand indicators are met.

[0052] Preferably, in the module M3, the spectrum setting variable based on the current demand parameter of power supply and distribution and the variables coupled with other demand parameters jointly determine the spectrum setting target quantization function;

[0053] The spectrum of the module M3 is set to optimize the solution of the required parameters, including:

[0054] make Find the solution that satisfies p0(x desn ,y coup )≤0 and q0(x desn ,y coup )=0, the minimum value of f;

[0055] Among them, f is the spectrum setting target;

[0056] n is the total amount of demand parameters;

[0057] f i Set the target for the spectrum of the i-th demand parameter;

[0058] x desn Set variables for the spectrum of required parameters;

[0059] y coup Coupling variables of spectrum setting variables and other required parameters;

[0060] p0 and q0 are the inequality constraint and equality constraint set by the spectrum respectively.

[0061] Preferably, the module M6 includes product matching, matching inequality and equality constraints based on matching selection variables that depend on product matching and coupling variables between matching selection variables and other products;

[0062] The product selection is to optimize the product selection, including:

[0063] make Solve the problem of satisfying m0(z desn ,h coup )≤0 and n0(z desn ,h coup )=0, the minimum value of c;

[0064] Among them, c is the product selection target;

[0065] N is the number of products;

[0066] c i The product selection target for the i-th product;

[0067] z desn The optional variants for matching products;

[0068] h coup It is the coupling variable between the matching option variable and other products;

[0069] m0 and n0 are the inequality constraints and equality constraints for product matching selection respectively.

[0070] According to a computer-readable storage medium storing a computer program provided by the present invention, when the computer program is executed by a processor, the steps of any one of the methods for constructing a fast spacecraft power supply and distribution system provided by the present invention are implemented.

[0071] A spacecraft system provided according to the present invention comprises any one of the construction systems for the rapid spacecraft power supply and distribution system provided by the present invention, or the computer-readable storage medium storing a computer program.

[0072] Compared with the prior art, the present invention has the following beneficial effects:

[0073] 1. The present invention can, under the condition of ensuring the reliability of the spacecraft power supply and distribution system, cope with the characteristics of the long link of the spacecraft power supply and distribution system, greatly accelerate and standardize the overall construction of the spacecraft power supply and distribution system, solve the problem of low efficiency of the overall scheme design, and greatly shorten the development cycle.

[0074] 2. The present invention optimizes the system construction. The construction of the overall plan takes into account the influence of various coupling degrees, avoids excessive design, ensures the long-term stable operation of the spacecraft, and completes the transformation of the power supply and distribution development model.

[0075] 3. The present invention solves the problems of low comparison efficiency and difficulty in quantifying and introducing the coupling effects between spectrum variables and other demand indicators by using a spectrum setting target quantification function determined jointly by variables that are coupled between spectrum setting variables of current demand parameters of power supply and distribution. BRIEF DESCRIPTION OF THE DRAWINGS

[0076] 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:

[0077] Figure 1 Schematic diagram of the execution flow of the overall construction method of the fast spacecraft power supply and distribution system.

[0078] Figure 2 Schematic diagram of parameter indicators for spacecraft power supply and distribution demand analysis.

[0079] Figure 3 Schematic diagram of parameter indicators for power supply and distribution type spectral library.

[0080] Figure 4 This is a schematic diagram of the composition block diagram of the power supply and distribution product library. DETAILED DESCRIPTION

[0081] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0082] According to a method for constructing a rapid spacecraft power supply and distribution system provided by the present invention, Figure 1 For example, the following steps are included:

[0083] Step S1: Analyze the requirements of the spacecraft power supply and distribution system according to the spacecraft development and design report;

[0084] by Figure 2 For example, the spacecraft power supply and distribution system demand indicators include: orbit altitude, platform power, bus topology, and bus voltage.

[0085] Step S2: Establishing a power supply and distribution spectrum library based on comprehensive design experience and spectrum parameter indicators;

[0086] The establishment of the spectrum library is based on the specific spectrum parameters involved in the development process of various types of spacecraft, and the spectrum parameters are classified and summarized in combination with the development requirements of spacecraft. Figure 3 For example, the spectrum parameter indicators of the power supply and distribution spectrum library include: orbit altitude classification, platform power range, bus system topology, bus voltage range, etc. The establishment of the power supply and distribution spectrum library is based on the power supply and distribution spectrum parameters of various types of spacecraft. In the process of designing a spacecraft based on the spacecraft power supply and distribution system demand indicators in step S1, it can reduce repeated design work and improve design efficiency.

[0087] Step S3: setting the power spectrum according to the demand index of step S1 and the power supply spectrum library of step S2, and proposing several power supply spectrum setting schemes for spacecraft;

[0088] In order to solve the problems of low comparison efficiency in formulating traditional spectrum design schemes and difficulty in quantifying and introducing the coupling effects between spectrum variables and other demand indicators, combined with the high design complexity and high coupling degree of spacecraft power supply and distribution, an innovative spectrum setting target quantization function is proposed, which is determined by the coupling variables between spectrum setting variables based on the current demand parameters of power supply and distribution and other demand parameters.

[0089] In view of the characteristics of power supply and distribution system design as a systematic design project, the spectrum setting targets of multi-spectrum setting variable parameters are integrated to jointly determine the spacecraft power supply and distribution design, and the required parameters are optimized based on the integrated spectrum setting targets. This avoids the isolated design of parameters in the traditional spectrum setting process and improves the reliability of the spectrum design scheme.

[0090] The spectrum setting includes the optimization solution of the demand parameters. The spectrum setting variables of the demand parameters and other demand parameters have coupled variables to form inequality constraints and equality constraints, covering all constraint relationships in the process of optimizing the spectrum setting objective function, and obtaining a power supply and distribution system spectrum setting scheme that comprehensively considers multiple system demand indicators and complex coupling relationships between indicators. The process is as follows:

[0091] make Find the solution that satisfies p0(x desn ,y coup )≤0 and q0(x desn ,y coup )=0, the minimum value of f.

[0092] Among them, f is the spectrum setting target;

[0093] n is the total amount of demand parameters;

[0094] f i Set the target for the spectrum of the i-th demand parameter;

[0095] x desn Set variables for the spectrum of required parameters;

[0096] y coup Coupling variables of spectrum setting variables and other required parameters;

[0097] p0 and q0 are the inequality constraint and equality constraint set by the spectrum respectively.

[0098] Step S4: According to the demand index of step S1, the feasibility of each spectrum setting scheme is judged. If the index requirements are met, the product is constructed. If the index requirements are not met, the scheme is modified and a new spectrum is established to re-set the spectrum until the index requirements are met;

[0099] Step S5: Establish a power supply and distribution product library according to the spacecraft power supply and distribution products and their parameter indicators;

[0100] The establishment of the power supply and distribution product library is based on the specific spectrum parameters involved in the development process of various types of spacecraft, and the spectrum parameters are classified and summarized in combination with the development needs of spacecraft. Figure 4 For example, the power supply and distribution product library includes electrical parameter indicators of the following products: mechanical solar wing, solar cell, solar wing drive mechanism, power controller, battery, power converter, battery equalizer, distributor, etc. The established product library is an important selection reference library for power supply and distribution of multiple models of spacecraft, which has a positive impact on improving design efficiency.

[0101] Step S6: According to the spacecraft power supply and distribution spectrum design scheme of step S4 and the power supply and distribution product library of step 5, the selected products are matched to obtain several product matching schemes;

[0102] The comparison efficiency is low when formulating traditional product selection schemes, and the coupling effects between the product's matching selection variables and other products are difficult to quantify and introduce. Therefore, in the process of formulating product selection schemes, a product selection target quantification function is proposed. Based on the inequality and equality constraints of product matching that also depend on the matching selection variables of the product and the coupling variables between the matching selection variables and other products, all constraint relationships in the process of optimizing the product selection target function can be covered. The coupling relationships between various matching selection variables and other products are comprehensively considered, and the product selection scheme for the power supply and distribution system can be quickly constructed under the condition of ensuring reliable design quality.

[0103] The product selection includes the optimization solution of product matching, and the design process is as follows:

[0104] make Solve the problem of satisfying m0(z desn ,h coup )≤0 and n0(z desn ,h coup )=0, the minimum value of c.

[0105] Among them, c is the product selection target;

[0106] N is the number of products;

[0107] c i The product selection target for the i-th product;

[0108] z desn The optional variants for matching products;

[0109] h coup It is the coupling variable between the matching option variable and other products;

[0110] m0 and n0 are the inequality constraints and equality constraints for product matching selection respectively.

[0111] Step S7: According to the demand index of step S1, the feasibility of each product matching scheme is judged. If the index requirements are met, the design is completed. If the index requirements are not met, a new product is put into storage and the product design is re-performed until the index requirements are met.

[0112] The proposed target quantization function for spectrum setting in the present invention comprehensively considers various demand indicators in the power supply and distribution system, optimizes the demand parameters according to the spacecraft development and design report, and obtains the spectrum setting plan, which is then tested and combined with the established power supply and distribution product library to optimize the product selection. The design method proposed in the present invention is based on a high-maturity spectrum structure, and quickly and accurately completes the spectrum setting plan while comprehensively considering various indicator requirements and coupling effects, greatly improving design efficiency and ensuring high quality and reliability of the design.

[0113] The present invention also provides a system for constructing a rapid spacecraft power supply and distribution system. The system for constructing a rapid spacecraft power supply and distribution system can be implemented by executing the process steps of the method for constructing a rapid spacecraft power supply and distribution system. That is, those skilled in the art can understand the method for constructing a rapid spacecraft power supply and distribution system as a preferred implementation of the system for constructing a rapid spacecraft power supply and distribution system.

[0114] Those skilled in the art know that, in addition to realizing the system and its various devices, modules, and units provided by the present invention in a purely computer-readable program code, it is entirely possible to realize the same functions in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a hardware component, and the devices, modules, and units included therein for realizing various functions can also be regarded as structures within the hardware component; the devices, modules, and units for realizing various functions can also be regarded as both software modules for realizing the method and structures within the hardware component.

[0115] A system for constructing a rapid spacecraft power supply and distribution system according to the present invention comprises:

[0116] Module M1: Analyze the demand indicators of the spacecraft power supply and distribution system according to the spacecraft development and design report;

[0117] Module M2: Establish a power supply and distribution spectrum library based on demand and spectrum parameter indicators;

[0118] Module M3: Set the spectrum according to the demand index and the power supply and distribution spectrum library to obtain the spectrum setting plan;

[0119] Module M4: Determine the feasibility of the spectrum setting plan based on demand indicators;

[0120] Module M5: Establish a power supply and distribution product library based on spacecraft power supply and distribution products and their parameter indicators;

[0121] Module M6: Select products according to the spectrum setting plan and the power supply and distribution product library to obtain a product selection plan;

[0122] Module M7: Determine the feasibility of product options based on demand indicators and complete the construction.

[0123] In more preferred examples, the spacecraft power supply and distribution system demand indicators in the module M1 include orbital altitude, platform power, bus topology and bus voltage;

[0124] The module M2 classifies and summarizes the spectrum parameters based on the specific spectrum parameters involved in the development of various types of spacecraft and in combination with the development requirements;

[0125] The spectrum parameter indicators include track height classification, platform power range, busbar system topology and busbar voltage range;

[0126] The power supply and distribution product library in the module M5 includes electrical parameter indicators of mechanical solar wings, solar cells, solar wing drive mechanisms, power controllers, batteries, power converters, battery equalizers and distributors;

[0127] In the step S4, if it is determined that the demand indicators are met, the product is constructed; if the demand indicators are not met, the plan is modified and the spectrum is re-set until the demand indicators are met;

[0128] In step S7, if it is determined that the demand indicators are met, the construction is completed; if the demand indicators are not met, a new product is put into storage and the product selection is re-performed until the demand indicators are met.

[0129] In more preferred examples, the spectrum setting target quantization function is determined by the coupled variables between the spectrum setting variables based on the current demand parameters of power supply and distribution and other demand parameters in the module M3;

[0130] The spectrum of the module M3 is set to optimize the solution of the required parameters, including:

[0131] make Find the solution that satisfies p0(x desn ,y coup )≤0 and q0(x desn ,y coup )=0, the minimum value of f;

[0132] Among them, f is the spectrum setting target;

[0133] n is the total amount of demand parameters;

[0134] f i Set the target for the spectrum of the i-th demand parameter;

[0135] xdesn Set variables for the spectrum of required parameters;

[0136] y coup Coupling variables of spectrum setting variables and other required parameters;

[0137] p0 and q0 are the inequality constraint and equality constraint set by the spectrum respectively.

[0138] In more preferred examples, the module M6 includes product matching, matching inequality and equality constraints based on matching selection variables depending on product matching and coupling variables between matching selection variables and other products;

[0139] The product selection is to optimize the product selection, including:

[0140] make Solve the problem of satisfying m0(z desn ,h coup )≤0 and n0(z desn ,h coup )=0, the minimum value of c;

[0141] Among them, c is the product selection target;

[0142] N is the number of products;

[0143] c i The product selection target for the i-th product;

[0144] z desn The optional variants for matching products;

[0145] h coup It is the coupling variable between the matching option variable and other products;

[0146] m0 and n0 are the inequality constraints and equality constraints for product matching selection respectively.

[0147] According to a computer-readable storage medium storing a computer program provided by the present invention, when the computer program is executed by a processor, the steps of any one of the methods for constructing a fast spacecraft power supply and distribution system provided by the present invention are implemented.

[0148] A spacecraft system provided according to the present invention comprises any one of the construction systems for the rapid spacecraft power supply and distribution system provided by the present invention, or the computer-readable storage medium storing a computer program.

[0149] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A method for constructing a fast spacecraft power supply and distribution system, characterized in that: include: Step S1: Analyze the demand indicators of the spacecraft power supply and distribution system according to the spacecraft development and design report; Step S2: Establish a power supply and distribution spectrum library according to demand and spectrum parameter indicators; Step S3: Setting the spectrum according to the demand index and the power supply and distribution spectrum library to obtain a spectrum setting plan; Step S4: judging the feasibility of the spectrum setting scheme according to the demand indicators; Step S5: Establish a power supply and distribution product library according to spacecraft power supply and distribution products and their parameter indicators; Step S6: Select products according to the model spectrum setting plan and the power supply and distribution product library to obtain a product selection plan; Step S7: According to the demand indicators, determine the feasibility of the product selection plan and complete the construction.

2. The method for constructing a fast spacecraft power supply and distribution system according to claim 1, characterized in that: The spacecraft power supply and distribution system demand indicators in step S1 include orbital altitude, platform power, bus topology and bus voltage; In step S2, based on the specific spectrum parameters involved in the development of various types of spacecraft, the spectrum parameters are classified and summarized in combination with the development requirements; The spectrum parameter indicators include track height classification, platform power range, busbar system topology and busbar voltage range; The power supply and distribution product library in step S5 includes electrical parameter indicators of mechanical solar wings, solar cells, solar wing drive mechanisms, power controllers, batteries, power converters, battery equalizers and distributors; In the step S4, if it is determined that the demand indicators are met, the product is constructed; if the demand indicators are not met, the plan is modified and the spectrum is re-set until the demand indicators are met; In step S7, if it is determined that the demand indicators are met, the construction is completed; if the demand indicators are not met, a new product is put into storage and the product selection is re-performed until the demand indicators are met.

3. The method for constructing a fast spacecraft power supply and distribution system according to claim 1, characterized in that: The spectrum setting variable based on the current demand parameter of power supply and distribution in step S3 is determined by the spectrum setting target quantitative function jointly determined by the variables coupled with other demand parameters; The spectrum of step S3 is set to optimize the solution of the demand parameters, including: make Find the solution that satisfies p0(x desn ,y coup )≤0 and q0(x desn ,y coup )=0, the minimum value of f; Among them, f is the spectrum setting target; n is the total amount of demand parameters; f i Set the target for the spectrum of the i-th demand parameter; x desn Set variables for the spectrum of required parameters; y coup Coupling variables of spectrum setting variables and other required parameters; p0 and q0 are the inequality constraint and equality constraint set by the spectrum respectively.

4. The method for constructing a fast spacecraft power supply and distribution system according to claim 1, characterized in that: In step S6, the product matching is based on the matching optional variables that depend on the product matching and the coupling variables between the matching optional variables and other products, and the matching inequality and equality constraints; The product selection is to optimize the product selection, including: make Solve the problem of satisfying m0(z desn ,h coup )≤0 and n0(z desn ,h coup )=0, the minimum value of c; Among them, c is the product selection target; N is the number of products; c i The product selection target for the i-th product; z desn The optional variants for matching products; h coup It is the coupling variable between the matching option variable and other products; m0 and n0 are the inequality constraints and equality constraints for product matching selection respectively.

5. A system for constructing a rapid spacecraft power supply and distribution system, characterized in that: include: Module M1: Analyze the demand indicators of the spacecraft power supply and distribution system according to the spacecraft development and design report; Module M2: Establish a power supply and distribution spectrum library based on demand and spectrum parameter indicators; Module M3: Set the spectrum according to the demand index and the power supply and distribution spectrum library to obtain the spectrum setting plan; Module M4: Determine the feasibility of the spectrum setting plan based on demand indicators; Module M5: Establish a power supply and distribution product library based on spacecraft power supply and distribution products and their parameter indicators; Module M6: Select products according to the spectrum setting plan and the power supply and distribution product library to obtain a product selection plan; Module M7: Determine the feasibility of product options based on demand indicators and complete the construction.

6. The system for constructing a fast spacecraft power supply and distribution system according to claim 5, characterized in that: The spacecraft power supply and distribution system demand indicators in the module M1 include orbital altitude, platform power, bus topology and bus voltage; The module M2 classifies and summarizes the spectrum parameters based on the specific spectrum parameters involved in the development of various types of spacecraft and in combination with the development requirements; The spectrum parameter indicators include track height classification, platform power range, busbar system topology and busbar voltage range; The power supply and distribution product library in the module M5 includes electrical parameter indicators of mechanical solar wings, solar cells, solar wing drive mechanisms, power controllers, batteries, power converters, battery equalizers and distributors; In the step S4, if it is determined that the demand indicators are met, the product is constructed; if the demand indicators are not met, the plan is modified and the spectrum is re-set until the demand indicators are met; In step S7, if it is determined that the demand indicators are met, the construction is completed; if the demand indicators are not met, a new product is put into storage and the product selection is re-performed until the demand indicators are met.

7. The system for constructing a rapid spacecraft power supply and distribution system according to claim 5, characterized in that: The spectrum setting target quantization function determined by the spectrum setting variables based on the current demand parameters of power supply and distribution and other demand parameters coupled with other demand parameters in the module M3; The spectrum of the module M3 is set to optimize the solution of the required parameters, including: make Find the solution that satisfies p0(x desn ,y coup )≤0 and q0(x desn ,y coup )=0, the minimum value of f; Among them, f is the spectrum setting target; n is the total amount of demand parameters; f i Set the target for the spectrum of the i-th demand parameter; x desn Set variables for the spectrum of required parameters; y coup Coupling variables of spectrum setting variables and other required parameters; p0 and q0 are the inequality constraint and equality constraint set by the spectrum respectively.

8. The system for constructing a rapid spacecraft power supply and distribution system according to claim 5, characterized in that: In the module M6, the product matching, matching inequality and equality constraints based on matching option variables depending on product matching and coupling variables between matching option variables and other products; The product selection is to optimize the product selection, including: make Solve the problem of satisfying m0(z desn ,h coup )≤0 and n0(z desn ,h coup )=0, the minimum value of c; Among them, c is the product selection target; N is the number of products; c i The product selection target for the i-th product; z desn The optional variants for matching products; h coup It is the coupling variable between the matching option variable and other products; m0 and n0 are the inequality constraints and equality constraints for product matching selection respectively.

9. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the steps of the method for constructing a fast spacecraft power supply and distribution system according to any one of claims 1 to 4 are implemented.

10. A spacecraft system, characterized in that: A system for constructing a fast spacecraft power supply and distribution system comprising any one of claims 5 to 8, or a computer-readable storage medium storing a computer program as claimed in claim 9.

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