Component layout optimization method considering uniformization of component layout area

Abstract

This invention discloses a component layout optimization method considering temperature homogenization in the component layout area, relating to the field of component layout technology. The method includes: determining the satellite component layout area and its dimensions; determining the number of components to be arranged, as well as the average operating power, structure, and dimensions of each component; determining the average heat flux of the satellite component layout area and the corresponding thermally effective area of ​​each component; modeling the thermally effective area of ​​the components based on their thermally effective areas; and, based on the satellite component layout area, the components to be arranged, and their corresponding thermally effective areas, using the maximization of temperature homogenization in the satellite component layout area as the optimization objective, and employing component uniqueness constraints, component non-interference constraints, and component system centroid constraints as constraints, constructing and solving a component layout optimization model based on integer programming to obtain the position of each component in the satellite component layout area. This invention can achieve component layout optimization considering temperature homogenization in the component layout area with high optimization efficiency.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of component layout, and in particular to a component layout optimization method considering uniformization of a component layout area. BACKGROUND

[0002] Satellite layout plays a vital role in determining its on-orbit performance and function, and the purpose of satellite layout design is to arrange electronic components or devices at appropriate positions of the satellite to meet various system performance requirements, such as mass characteristics and thermal control, etc. As an important link of satellite overall design, satellite layout design directly determines the comprehensive performance, development cost, design cycle and design level of the satellite system.

[0003] In the process of satellite component layout scheme design, in order to meet specific performance requirements, the temperature field performance of the satellite layout area also needs to be considered sometimes. At present, in the process of satellite component layout optimization design, when the temperature field performance of the satellite layout area is considered, the component layout optimization design is mainly performed in the following way: the finite element analysis technology is used to accurately simulate and calculate the satellite temperature field, and the thermal simulation is embedded into the component layout optimization process to guide the design of the component layout scheme by setting the highest temperature constraint or the lowest temperature constraint or setting the minimum average temperature as an index.

[0004] However, in the actual process of satellite component layout optimization design, the simulation calculation of the satellite temperature field based on the finite element analysis technology takes a long time, and the optimization efficiency is low. At the same time, adding the temperature constraint or the temperature index into the layout optimization iteration will sharply increase the calculation cost, resulting in an increase in the cost of component layout optimization. SUMMARY

[0005] To solve the above-mentioned technical problems in the prior art, the present application provides a component layout optimization method considering uniformization of a component layout area.

[0006] The technical scheme of the present application is as follows:

[0007] A component layout optimization method considering uniformization of a component layout area is provided, which comprises the following steps:

[0008] determining a satellite component layout area and its size;

[0009] determining the number of components to be arranged, and the average working power, structure and size of each component;

[0010] determining the average heat flow of the satellite component layout area and the corresponding thermal effective area of each component according to the size of the satellite component layout area and the average working power of each component;

[0011] Based on the thermally effective area of ​​the component, the thermally effective region of the component is modeled. Based on the satellite component layout area, the component to be deployed and its corresponding thermally effective region, the optimization objective is to maximize the temperature uniformity of the satellite component layout area. The component uniqueness constraint, component non-interference constraint, and component system centroid constraint are used as constraints to construct a component layout optimization model based on integer programming.

[0012] Solve the component layout optimization model to obtain the position of each component in the satellite component layout area.

[0013] Furthermore, in some implementations, the average heat flux of the satellite component layout area is determined using the following formula:

[0014] ;

[0015] The effective thermal area of ​​the component can be determined using the following formula:

[0016] ;

[0017] in, This represents the average heat flux over the area where satellite components are arranged. This indicates the area of ​​the satellite component layout region. Indicates the number of components. Indicates the first Average operating power of each component Indicates the first The effective thermal area of ​​each component.

[0018] Furthermore, in some embodiments, the component uniqueness constraint indicates that the component can only be installed on the satellite component layout area, the component non-interference constraint indicates that there is no overlap between any two components, and the component system centroid constraint includes the constraint on the calculation method of the component system centroid position and the deviation constraint between the component system centroid position and the desired centroid position.

[0019] Furthermore, in some embodiments, the thermally effective area modeling of the components is performed based on the thermally effective area of ​​the components. Based on the satellite component layout area, the components to be deployed, and their corresponding thermally effective areas, the optimization objective is to maximize the temperature uniformity of the satellite component layout area. Constraints include component uniqueness, component non-interference, and component system centroid constraints. An integer programming-based component layout optimization model is constructed, comprising:

[0020] Select a point in the satellite component layout area as the origin of the coordinate system, construct a Cartesian coordinate system, and determine the coordinate range corresponding to the satellite component layout area.

[0021] Using the center position of the component as the component position, and based on the coordinate range corresponding to the satellite component layout area and the component size, establish the constraint expression corresponding to the component uniqueness constraint;

[0022] The Phi function is used to determine the formula for calculating the interference between any two components. Indicator variables are introduced and the large number method is combined to linearize the formula for calculating the interference, so as to obtain the constraint expression corresponding to the component non-interference constraint.

[0023] Using the center of the component as the component's centroid, and based on the component's mass and the set desired centroid position, establish the constraint expression corresponding to the component system's centroid constraint;

[0024] The Phi function is used to determine the formula for calculating the interference between the thermally effective regions of any two components. Indicator variables are introduced and the large number method is combined to linearize the formula for calculating the interference. Based on the linearization result and the set optimization objective, an optimization objective expression is established.

[0025] Based on the constraint expressions corresponding to component uniqueness constraints, component non-interference constraints, component system centroid constraints, and optimization objective expressions, a component layout optimization model based on integer programming is constructed.

[0026] Furthermore, in some embodiments, it is set that: all components are rectangular structures, and all components are rigid bodies with uniform mass distribution; the centroid of the component coincides with the geometric center of the component; the satellite component layout area is a square two-dimensional planar layout area; the lower left corner of the satellite component layout area is selected as the origin of the coordinate system, and a Cartesian coordinate system is constructed; the satellite component layout area is in the coordinate system. The length in the axial direction is The satellite component layout area is in the coordinate system The length in the axial direction is , No. The coordinates of the center of each component are , No. Each component is parallel to the coordinate system. The dimensions of the shaft are , No. Each component is parallel to the coordinate system. The dimensions of the shaft are The number of components is ;

[0027] The constraint expression corresponding to the component uniqueness constraint is:

[0028] .

[0029] Furthermore, in some implementations, the constraint expression corresponding to the component non-interference constraint is:

[0030] ;

[0031] in, Indicates the first The coordinates of the center of each component Indicates the first Each component is parallel to the coordinate system. Shaft dimensions, Indicates the first Each component is parallel to the coordinate system. Shaft dimensions, , , As an indicator variable, , It is a positive number.

[0032] Furthermore, in some implementations, the constraint expression corresponding to the centroid constraint of the component system is:

[0033] ;

[0034] in, Indicates the first The quality of each component Indicates the position coordinates of the desired centroid. Indicates the position coordinates of the centroid of the component system. and This indicates the centroid deviation in the coordinate system. Axial direction and The component along the axial direction.

[0035] Furthermore, in some implementations, the thermally effective area of ​​the component is modeled as a square, and the... The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are , No. The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are , No. The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are , No. The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are ;

[0036] The optimization objective expression is:

[0037] ;

[0038] in, For the target variable, It is a positive number. All of them are indicator variables.

[0039] Furthermore, in some implementations, the component layout optimization model based on integer programming is expressed as:

[0040] ;

[0041] in, This indicates the satellite component layout scheme. .

[0042] The main advantages of the technical solution of this invention are as follows:

[0043] The component layout optimization method of the present invention, which considers the homogenization of the component layout area, models the thermally effective area of ​​the component as a square, transforms the homogenization of the component layout area into minimizing the interference of the thermally effective area, models the minimization of the thermally effective area interference using integer programming modeling ideas, and constructs a component layout optimization model based on integer programming using integer programming modeling ideas. This method can realize the optimization solution of satellite component layout considering the homogenization of the component layout area, obtain a component layout scheme that meets the homogenization requirements, and has high optimization efficiency and short optimization time. Attached Figure Description

[0044] The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and constitute a part of this invention, illustrate exemplary embodiments of the invention and, together with their description, serve to explain the invention and do not constitute an undue limitation thereof. In the drawings:

[0045] Figure 1 A flowchart of a component layout optimization method considering temperature homogenization in the component layout area is provided for an embodiment of the present invention;

[0046] Figure 2 This is a schematic diagram of component positions on a two-dimensional planar layout area provided in an embodiment of the present invention. Detailed Implementation

[0047] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0048] The technical solutions provided by the embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0049] refer to Figure 1This invention provides a component layout optimization method that considers temperature homogenization in the component layout area. The method includes the following steps S1-S5:

[0050] Step S1: Determine the layout area and size of the satellite components.

[0051] Specifically, based on the actual satellite layout, the satellite component layout area and related size information of the satellite component layout area are determined.

[0052] Step S2: Determine the number of components to be deployed, as well as the average operating power, structure, and dimensions of each component.

[0053] Specifically, based on the actual satellite layout, the component information that needs to be arranged in the satellite component layout area is determined. The component information includes: the number of components, the average operating power of each component, and the structure and size of each component.

[0054] Step S3: Determine the average heat flux of the satellite component layout area and the corresponding thermally effective area of ​​each component based on the size of the satellite component layout area and the average operating power of each component.

[0055] Specifically, the area of ​​the satellite component layout region is defined as follows: The number of components is , No. The average operating power of each component is The average heat flux of the satellite component layout area can be calculated using the following formula:

[0056] ;

[0057] This represents the average heat flux over the area where satellite components are laid out.

[0058] Furthermore, in order for each component to achieve an average heat flux, each component must distribute heat uniformly over an area proportional to its power. Therefore, the thermally effective area of ​​each component can be calculated using the following formula:

[0059] ;

[0060] Indicates the first The effective thermal area of ​​each component.

[0061] Based on the calculation methods for the average heat flux and effective thermal area of ​​the satellite component layout area described above, it can be seen that the sum of the effective thermal areas of all components equals the area of ​​the satellite component layout area, that is:

[0062] .

[0063] Step S4: Model the thermally effective area of ​​the component based on the thermally effective area of ​​the component. Based on the satellite component layout area, the component to be deployed and its corresponding thermally effective area, take maximizing the temperature uniformity of the satellite component layout area as the optimization objective, and use component uniqueness constraint, component non-interference constraint and component system centroid constraint as constraints to construct a component layout optimization model based on integer programming.

[0064] In the actual satellite component layout optimization design process, the satellite component layout area is usually a square two-dimensional planar layout area. Therefore, in this embodiment of the invention, taking a square two-dimensional planar layout area as an example, the specific process and principle of the component layout optimization method provided by this embodiment of the invention will be explained.

[0065] In this embodiment of the invention, to facilitate satellite component layout optimization, improve optimization efficiency, and ensure the feasibility of the obtained satellite component layout scheme, the component is approximated as a square with uniform mass distribution during satellite component layout optimization. This square is the outer envelope square of the component, with the center of the square serving as the center and centroid of the component. Since the satellite component layout area is a two-dimensional planar layout area, the height of the component in the direction perpendicular to its mounting surface does not need to be considered during component layout optimization.

[0066] Furthermore, based on approximating the component as a cube, the thermally effective area of ​​the component is modeled as a square. Simultaneously, to ensure that the thermally effective area of ​​the component fits the structural dimensions of the component, the side length of the thermally effective area is determined using the following formula:

[0067] ;

[0068] and Indicates the first The two side lengths of the thermally effective region of each component and Indicates the first The two side lengths of each component.

[0069] In this embodiment of the invention, based on the common satellite component layout requirements and considering the temperature field performance of the satellite component layout area, the optimization objective includes: maximizing the temperature homogenization of the satellite component layout area. Specifically, according to the definitions of the thermally effective area and thermally effective region of the component, maximizing the temperature homogenization of the satellite component layout area is equivalent to minimizing the interference of the thermally effective region of the component.

[0070] The constraints include: component uniqueness constraint, component non-interference constraint, and component system centroid constraint. Specifically, the component uniqueness constraint means that components can only be installed on the satellite component layout area; the component non-interference constraint means that no two components overlap; the component system centroid constraint includes constraints on the calculation method of the component system centroid position and constraints on the deviation between the component system centroid position and the desired centroid position.

[0071] Furthermore, in this embodiment of the invention, based on the above definitions and settings, the thermally effective area of ​​the component is modeled according to the thermally effective area of ​​the component. Based on the satellite component layout area, the component to be arranged and its corresponding thermally effective area, the optimization objective is to maximize the temperature uniformity of the satellite component layout area. The component uniqueness constraint, component non-interference constraint, and component system centroid constraint are used as constraints to construct a component layout optimization model based on integer programming, specifically including the following steps S401-S406:

[0072] Step S401: Select a point in the satellite component layout area as the origin of the coordinate system, construct a Cartesian coordinate system, and determine the coordinate range corresponding to the satellite component layout area.

[0073] refer to Figure 2 In this embodiment of the invention, to facilitate constraint description and model construction, the lower left corner of the satellite component layout area is selected as the coordinate origin. Construct a two-dimensional Cartesian coordinate system This allows us to determine the coordinate range corresponding to the satellite component layout area.

[0074] Furthermore, based on the two-dimensional Cartesian coordinate system constructed above, the following definition is made: the satellite component layout area in the coordinate system... The length in the axial direction is The satellite component layout area is in the coordinate system The length in the axial direction is , The coordinate range corresponding to the satellite component layout area is: arrive .

[0075] Step S402: Using the center position of the component as the component position, establish the constraint expression corresponding to the component uniqueness constraint based on the coordinate range corresponding to the satellite component layout area and the component size.

[0076] Specifically, the following settings are established: all components are cubic structures, and all components are rigid bodies with uniform mass distribution; the center of mass of each component coincides with its geometric center. A two-dimensional Cartesian coordinate system is constructed based on the above. Further definition: the first The coordinates of the center of each component are , No. Each component is parallel to the coordinate system. The dimensions of the shaft are , No. Each component is parallel to the coordinate system. The dimensions of the shaft are .

[0077] Since the satellite component layout area is a two-dimensional planar layout area, when optimizing the component layout, it is not necessary to consider the height of the component in the direction perpendicular to its mounting surface. Therefore, the constraint expression corresponding to the established component uniqueness constraint can be expressed as:

[0078] .

[0079] Step S403: Use the Phi function to determine the formula for calculating the interference between any two components, introduce indicator variables and combine the method of large numbers to linearize the formula for calculating the interference, and obtain the constraint expression corresponding to the component non-interference constraint.

[0080] Specifically, the definition is: the first The component and the first The interference between the components is To ensure that there is no interference between components, the interference amount is... The following conditions must be met:

[0081] .

[0082] In this embodiment of the invention, the Phi function method is used to calculate the interference between any two components. Specifically, the two components are respectively the first... The component and the first Taking the first component as an example, define: The coordinates of the center of each component are , No. Each component is parallel to the coordinate system. The dimensions of the shaft are , No. Each component is parallel to the coordinate system. The dimensions of the shaft are The formula for calculating the interference between the two components is as follows:

[0083] ;

[0084] Expanding the absolute value operation in the above formula for calculating the interferometric amount, the formula for calculating the interferometric amount can be equivalently transformed into:

[0085] .

[0086] Furthermore, indicator variables are introduced. By linearizing the above interference calculation formula using the method of large numbers, we obtain the following equivalent constraint form, which is the constraint expression corresponding to the component non-interference constraint:

[0087] ;

[0088] These are normal numbers; the specific values ​​should be set according to the actual situation, for example... The requirement is that all inequalities in the constraint expression corresponding to the non-interference constraint of the above components must be satisfied simultaneously.

[0089] In the constraint expressions corresponding to the component non-interference constraints mentioned above, when At that time, Can be converted If the inequality If true, it means that the component non-interference constraint is satisfied; when At that time, Can be converted ,because Since the numbers are positive constants, this inequality applies regardless of whether interference occurs between components. It is always true; through constraints It is required that at least one of the four indicator variables is equal to 1, thereby satisfying the component non-interference constraint.

[0090] Step S404: Using the center of the component as the component's centroid, establish the constraint expression corresponding to the component system's centroid constraint based on the component's mass and the set desired centroid position.

[0091] Specifically, the definition is: the first The mass of each component is The expected coordinates of the centroid are Then the constraint expression corresponding to the centroid constraint of the established component system can be expressed as:

[0092] ;

[0093] Indicates the position coordinates of the centroid of the component system. and This indicates the centroid deviation in the coordinate system. Axial direction and The component along the axial direction.

[0094] Step S405: Use the Phi function to determine the formula for calculating the interference between the thermally effective regions of any two components. Introduce indicator variables and combine the method of large numbers to linearize the formula for calculating the interference. Based on the linearization result and the set optimization objective, establish the optimization objective expression.

[0095] In this embodiment of the invention, the interference between the thermally effective regions of any two components is calculated using the Phi function method.

[0096] Specifically, since the components and their corresponding thermally effective areas are all modeled as squares, based on the two-dimensional Cartesian coordinate system constructed above, the following is further defined: The thermally effective area of ​​the first component is related to the first... The interference between the thermally effective regions of each component is , No. The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are , No. The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are , No. The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are , No. The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are .

[0097] The two components are respectively the first The component and the first Taking one component as an example, the formula for calculating the interference between the thermally effective regions of two components is as follows:

[0098] ;

[0099] when If this is the case, it indicates that there is a certain distance between the two effective thermal regions. The value can roughly measure the distance between the two, by reducing This allows the two to move closer to each other; when When this occurs, it indicates that interference has occurred between the two effective thermal regions. The value can roughly measure the amount of interference between the two, by increasing... It can separate the two.

[0100] Furthermore, by expanding the absolute value operation in the above formula for calculating the interference between thermally effective regions, the formula for calculating the interference between thermally effective regions can be equivalently transformed into:

[0101] .

[0102] Furthermore, in this embodiment of the invention, since the optimization objective is to maximize the temperature homogenization of the satellite component layout area, and maximizing the temperature homogenization of the satellite component layout area is equivalent to minimizing the interference of the thermally effective area of ​​the component, the optimization objective can be expressed in the following form:

[0103] .

[0104] Furthermore, indicator variables are introduced. By linearizing the above formula for calculating the interference between thermally effective regions using the method of large numbers, and combining this linearized formula, the optimization objective can be further transformed into the following expression:

[0105] ;

[0106] For the target quantity, It is a positive number. The specific values ​​are set according to the actual situation. In the above expression of the optimization objective, all inequalities must be satisfied simultaneously to ensure that the interference of the thermally effective region of the component is minimized.

[0107] Step S406: Based on the constraint expressions corresponding to the component uniqueness constraint, the constraint expressions corresponding to the component non-interference constraint, the constraint expressions corresponding to the component system centroid constraint, and the optimization objective expression, construct a component layout optimization model based on integer programming.

[0108] Specifically, based on the above analysis, when the optimization objective is to maximize the temperature homogenization of the satellite component layout area, the constructed component layout optimization model based on integer programming is expressed as:

[0109] ;

[0110] in, This indicates the satellite component layout scheme. .

[0111] In this embodiment of the invention, during the process of constructing the component layout optimization model based on integer programming, there is no requirement for the execution order of steps S402 to S405. They can be executed sequentially according to the above order or in other orders. Different steps can also be executed synchronously.

[0112] Step S5: Solve the component layout optimization model to obtain the position of each component in the satellite component layout area.

[0113] Specifically, the existing mature mathematical programming solver is used to solve the above-constructed component layout optimization model based on integer programming to obtain the corresponding satellite component layout scheme. This allows us to obtain the position of each component within the satellite component layout area. Mathematical programming solvers, such as the SCIP optimization solver and the CPLEX optimization solver, are used in this process.

[0114] The component layout optimization method considering temperature homogenization in the component layout area provided in this invention model the thermally effective area of ​​the component as a square, transforms the temperature homogenization of the component layout area into minimizing the thermally effective area interference, models the minimization of the thermally effective area interference using integer programming modeling ideas, and constructs a component layout optimization model based on integer programming using integer programming modeling ideas. This method can achieve satellite component layout optimization solution considering temperature homogenization in the component layout area, obtain a component layout scheme that meets the temperature homogenization requirements, and has high optimization efficiency and short optimization time.

[0115] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Additionally, the terms "front," "back," "left," "right," "upper," and "lower" in this document refer to the placement shown in the accompanying drawings.

[0116] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A component layout optimization method considering temperature homogenization in the component layout area, characterized in that, include: Determine the layout area and dimensions of the satellite components; Determine the number of components to be deployed, as well as the average operating power, structure, and dimensions of each component; Based on the size of the satellite component layout area and the average operating power of each component, determine the average heat flux of the satellite component layout area and the corresponding thermally effective area of ​​each component; Based on the thermally effective area of ​​the components, a thermally effective region model is constructed. Considering the satellite component layout area, the components to be deployed, and their corresponding thermally effective regions, the optimization objective is to maximize the temperature uniformity of the satellite component layout area. Constraints include component uniqueness, component non-interference, and component system centroid constraints. An integer programming-based component layout optimization model is then built. The component uniqueness constraint indicates that components can only be installed within the satellite component layout area. The component non-interference constraint indicates that no two components overlap. The component system centroid constraint includes constraints on the calculation method of the component system centroid position and constraints on the deviation between the component system centroid position and the desired centroid position. Solve the component layout optimization model to obtain the position of each component in the satellite component layout area.

2. The component layout optimization method considering temperature homogenization in the component layout area according to claim 1, characterized in that, The average heat flux of the satellite component layout area is determined using the following formula: ； The effective thermal area of ​​the component can be determined using the following formula: ； in, This represents the average heat flux over the area where satellite components are arranged. This indicates the area of ​​the satellite component layout region. Indicates the number of components. Indicates the first Average operating power of each component Indicates the first The effective thermal area of ​​each component.

3. The component layout optimization method considering temperature homogenization in the component layout area according to claim 2, characterized in that, The process involves modeling the thermally effective area of ​​the components, and based on the satellite component layout area, the components to be deployed, and their corresponding thermally effective areas, with the optimization objective of maximizing the temperature uniformity of the satellite component layout area, and using component uniqueness constraints, component non-interference constraints, and component system centroid constraints as constraints, constructing a component layout optimization model based on integer programming, including: Select a point in the satellite component layout area as the origin of the coordinate system, construct a Cartesian coordinate system, and determine the coordinate range corresponding to the satellite component layout area. Using the center position of the component as the component position, and based on the coordinate range corresponding to the satellite component layout area and the component size, establish the constraint expression corresponding to the component uniqueness constraint; The Phi function is used to determine the formula for calculating the interference between any two components. Indicator variables are introduced and the large number method is combined to linearize the formula for calculating the interference, so as to obtain the constraint expression corresponding to the component non-interference constraint. Using the center of the component as the component's centroid, and based on the component's mass and the set desired centroid position, establish the constraint expression corresponding to the component system's centroid constraint; The Phi function is used to determine the formula for calculating the interference between the thermally effective regions of any two components. Indicator variables are introduced and the large number method is combined to linearize the formula for calculating the interference. Based on the linearization result and the set optimization objective, an optimization objective expression is established. Based on the constraint expressions corresponding to component uniqueness constraints, component non-interference constraints, component system centroid constraints, and optimization objective expressions, a component layout optimization model based on integer programming is constructed.

4. The component layout optimization method considering temperature homogenization in the component layout area according to claim 3, characterized in that, Setting: All components are rectangular prisms with uniform mass distribution, and their centers of mass coincide with their geometric centers. The satellite component layout area is a square two-dimensional planar area. The lower left corner of the satellite component layout area is selected as the origin to construct a Cartesian coordinate system. The satellite component layout area is within this coordinate system. The length in the axial direction is The satellite component layout area is in the coordinate system The length in the axial direction is , No. The coordinates of the center of each component are , No. Each component is parallel to the coordinate system. The dimensions of the shaft are , No. Each component is parallel to the coordinate system. The dimensions of the shaft are The number of components is ; The constraint expression corresponding to the component uniqueness constraint is: 。 5. The component layout optimization method considering temperature homogenization in the component layout area according to claim 4, characterized in that, The constraint expression corresponding to the component non-interference constraint is: ； in, Indicates the first The coordinates of the center of each component Indicates the first Each component is parallel to the coordinate system. Shaft dimensions, Indicates the first Each component is parallel to the coordinate system. Shaft dimensions, , , As an indicator variable, , It is a positive number.

6. The component layout optimization method considering temperature homogenization in the component layout area according to claim 5, characterized in that, The constraint expression corresponding to the centroid constraint of the component system is: ； in, Indicates the first The quality of each component Indicates the position coordinates of the desired centroid. Indicates the position coordinates of the centroid of the component system. and This indicates the centroid deviation in the coordinate system. Axial direction and The component along the axial direction.

7. The component layout optimization method considering temperature homogenization in the component layout area according to claim 6, characterized in that, Setting: The thermally active area of ​​the component is modeled as a square, the first... The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are , No. The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are , No. The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are , No. The thermally effective area of ​​each component is parallel to the coordinate system. The dimensions of the shaft are ; The optimization objective expression is: ； in, For the target variable, It is a positive number. All of them are indicator variables.

8. The component layout optimization method considering temperature homogenization in the component layout area according to claim 7, characterized in that, The component layout optimization model based on integer programming is represented as follows: ； in, This indicates the satellite component layout scheme. .

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