CN-121859450-B - Satellite assembly layout-cabin plate structure integrated optimization design method based on thermal metamaterial

CN121859450BCN 121859450 BCN121859450 BCN 121859450BCN-121859450-B

Abstract

The invention discloses a satellite component layout-cabin board structure integrated optimization design method based on thermal metamaterial, which belongs to the technical field of satellite thermal management and comprises the steps of carrying out geometric description on components, carrying out interference calculation among the components, selecting a planar four-node rectangular unit discrete design domain, representing a component temperature field as an interpolation relation of node temperature, converting a design optimization target and constraint into a standard optimization column, searching an optimal component layout scheme, carrying out satellite cabin board structure topology optimization design according to a thermal metamaterial design thought, determining a thermal metamaterial function type, dividing a local cabin board design domain, carrying out discrete design on each design unit, carrying out topology optimization design on the discrete design units, searching a microstructure with the highest matching degree of macroscopic equivalent heat conduction tensor and a design unit center position theory heat conduction tensor, and assembling the microstructure to obtain a cabin board structure. The invention can realize global thermal management and local thermal management of the satellite cabin.

Inventors

ZHAO YONG
Huo Senlin
Du Bingxiao
SONG XIN
CONG WEI
DU YIYU
YANG JINXIAO
XIAO XIAO

Assignees

中国人民解放军国防科技大学

Dates

Publication Date: 20260512
Application Date: 20250801

Claims (10)

1. The satellite component layout-cabin plate structure integrated optimization design method based on the thermal metamaterial is characterized by comprising the following steps of: geometrically describing a two-dimensional component with a regular geometric shape based on a parameterized level set function, constructing a two-dimensional projection of a three-dimensional shape of the satellite component by using a Heaviside function, and performing interference calculation between the satellite components; selecting a plane four-node rectangular unit discrete design domain based on a steady-state heat conduction balance equation, and representing a satellite component temperature field as an interpolation relation of node temperatures; Encrypting and refining grids of the satellite assembly boundary by utilizing a multi-resolution finite element method, so as to realize analysis and evaluation of a corresponding temperature field; optimizing targets and constraints according to the distribution requirements of the satellite cabin temperature field and the layout requirements of the components; converting the optimization target and constraint into a standard optimization list, acquiring sensitivity of an objective function and the constraint to design variables by adopting an automatic differentiation technology, and searching an optimal component layout scheme by adopting a gradient optimization algorithm; Carrying out topological optimization design of a satellite cabin board structure based on the design thought of the thermal metamaterial, determining the functional type of the thermal metamaterial and dividing a local cabin board design domain according to the obtained optimal component layout scheme and the requirement of key components on the satellite cabin board on local thermal control functional characteristics; Dispersing the design domain to obtain a plurality of design units, and calculating a theoretical heat conduction tensor value at the center position of each expected design unit based on transformation heat; Dispersing each design unit, carrying out topological optimization design on the dispersed design units, and searching a microstructure with highest matching degree between a macroscopic equivalent heat conduction tensor and a theoretical heat conduction tensor at the central position of the design unit by adopting an inverse homogenization method; and assembling the microstructures of the design units to obtain the deck structure with the corresponding thermal metamaterial heat flow control function.
2. The thermal metamaterial-based satellite component layout-deck structure integrated optimization design method according to claim 1, wherein the geometric description of the regular-geometry two-dimensional component based on the parameterized level set function is determined by the following formula: ; Wherein, the Representing a level set function describing the shape of the component, And Representing half of the component length and width, respectively; Representing the geometric center coordinates of the satellite component, Indicating the rotation angle of the satellite assembly, positive in a counterclockwise direction from the horizontal, And The placement position of the satellite components in the layout area is determined together, Representing the position coordinates of any point in the plane, Is an even number of times, Parameters (parameters) The geometry of the assembly is determined and, Representing the component center as the origin and the long axis direction Relative position coordinates in the component local coordinate system of the shaft; Wherein, the The determination is made by the following formula: 。
3. The thermal metamaterial-based satellite component layout-deck structure integrated optimization design method as claimed in claim 2, wherein the Heaviside function adopts a regularized Heaviside function, and the regularized Heaviside function is expressed as: ; Wherein, the Representing a regularized Heaviside function, Representing the argument of the regularized Heaviside function, Is a constant value, and is used for the treatment of the skin, The half width of the transition interval of the Heaviside function 0-1 is shown.
4. The thermal metamaterial-based satellite component layout-deck structure integrated optimization design method according to claim 3, wherein the interference calculation between the satellite components is performed by: Constructing a two-dimensional projection of a three-dimensional shape of the satellite component using a Heaviside function, where Personal assembly The area occupied by the projection is expressed as: ; Wherein, the Represent the first Personal assembly Is provided with a two-dimensional projection area, Representing the region of space in which the component is located, Representation of Is a projection of the Heaviside function of (c), Representation description component A function of the level set of the shape, Representing the infinitesimal area as a component on the satellite deck With another component When overlapping occurs, the overlapping spatial region is determined by the following formula: ; Wherein, the Representing the size of the spatial area where the two components overlap, And Representing components separately And assembly The size of the area of space occupied, And Representing description components, respectively And assembly A level set function of the shape; when two satellite assemblies overlap on the deck, the area of the overlapping area of the two satellite assemblies is determined by the following formula: ; representing the area of the overlapping area of the two satellite components.
5. The thermal metamaterial-based satellite component layout-deck structure integrated optimization design method according to claim 4, wherein a plane four-node rectangular unit discrete design domain is selected based on a steady-state heat conduction equilibrium equation, and an interpolation relation for representing a satellite component temperature field as a node temperature is represented by the following way: ; Indicating the intensity of the heat source of the unit, Representing the constant heat source intensity of the unit area of a certain component, when four nodes of the unit are all inside the component, the corresponding heat source intensity of the unit is 1 。
6. The thermal metamaterial-based satellite component layout-deck structure integrated optimization design method according to claim 5, wherein the optimization list is expressed as: ; Wherein: Represent the first The position vector of the individual components is calculated, ; Representing design variables The design space range to be satisfied, the design variable of each component comprises the position coordinates of the reference point And its rotation angle , , The representation is based on a temperature field An objective function represented; Defining a temperature index according to requirements, selecting the maximum temperature of a layout area, and using KS function approximation as an objective function, wherein the objective function is shown in the following formula: ; Wherein, the The function of KS is represented by a function, Which represents the adjustment parameters of the device, Represent the first The temperature of the individual nodes is determined, Representing the number of nodes of the finite element mesh, Indicating the maximum temperature.
7. The thermal metamaterial-based satellite component layout-deck structure integrated optimization design method according to claim 1, wherein when the thermal metamaterial function type is determined and the local deck design domain is divided, evaluation and classification are carried out according to the thermal characteristics and the heat transfer requirements of the components, the difference of different satellite components in the type and degree of the deck structure heat flow control is distinguished, and according to the classification condition, the deck structure thermal metamaterial design scheme meeting the heat flow control requirements is matched for the satellite components and the local deck design domain is divided.
8. The thermal metamaterial-based satellite component layout-deck structure integrated optimal design method according to claim 7, wherein the discretizing the design domain to obtain a plurality of design units and calculating the theoretical thermal conduction tensor value at the center position of each design unit expected based on transformation thermal, comprises: based on the division result of the design domain, discretizing the design domain with a specific size by adopting a square grid to obtain a plurality of design units; determining the boundary function of the thermal metamaterial design domain and the position of the center of each design unit under a local coordinate system constructed by taking the center of the component as the origin; according to transformation heat, the form of a heat conduction equation before and after coordinate transformation is unchanged, and the physical parameters of the material are equivalent to space; The thermal streamline distortion corresponds to the space deformation through coordinate transformation, and a one-to-one correspondence relation between physical parameters of materials and the space change is established; Converting the original space into a transformation space according to a certain rule, determining heat conduction tensor distribution in the transformation space based on a corresponding relation, and calculating a theoretical heat conduction tensor value at the central position of each design unit, wherein the theoretical heat conduction tensor value is used as a target for subsequent structural optimization; Wherein the heat conduction equation in the transformation space is expressed as: ; Wherein, the Representing the temperature distribution in the transformation space, Representing the heat transfer tensor within the transformation space, Representing a gradient operation; The determination is calculated by the following formula: ; jacobian matrix representing the partial derivative conversion of coordinates between the original space and the transformed space, Representing the heat transfer tensor of the original space, Representing jacobian matrix Is used for the transposition operation of (a), Representing a function for calculating a matrix determinant.
9. The thermal metamaterial-based satellite component layout-deck structure integrated optimization design method according to claim 7, wherein the topology optimization design is performed on the design unit by the following manner: Defining an optimization target, determining a topological optimization model based on the defined optimization target, and setting microscopic initial design parameters; Performing numerical simulation on the heat conduction problem, determining a finite element model, and predefining finite element analysis parameters; initializing design variables and starting iterative optimization; substituting the design variables, and calculating the microstructure equivalent heat conduction tensor by using a homogenization method; calculating values of an objective function and a constraint function based on the calculated equivalent heat transfer tensor; analyzing and filtering the sensitivity, and updating design variables according to the filtered sensitivity information; Judging whether the design unit meets the convergence condition or not every time the updating of the design variable is completed; stopping optimization if the convergence condition is met, and obtaining an optimal topological structure meeting the requirement of the target heat conduction tensor; if the convergence condition is not met, substituting the updated design variable into the steps of homogenizing calculation, sensitivity analysis and design variable updating, and continuing iterative optimization until the design unit meets the convergence condition.
10. The thermal metamaterial-based satellite component layout-deck structure integrated optimal design method according to claim 1, wherein each design unit is discretized by: discretizing each design cell into base cells having a particular resolution, pseudo-density of base cells In order to optimize the design variables in the design, ; When the structure is composed of two materials, the SIMP interpolation model treats each base unit as an isotropic material with a specific thermal conductivity, and the thermal conductivity value of the base unit is expressed as: ; Wherein, the Representing the thermal conductivity of the base unit, And Representing the thermal conductivity coefficients of the two materials respectively, The time-representative heat conduction coefficient is Is composed of a material of (a) and (b), The time-representative heat conduction coefficient is Is composed of a material of (a) and (b), Representing penalty coefficients.

Description

Satellite assembly layout-cabin plate structure integrated optimization design method based on thermal metamaterial Technical Field The invention relates to the technical field of satellite thermal management, in particular to a satellite component layout-cabin plate structure integrated optimization design method based on thermal meta-materials. Background The thermal management (or thermal control) is a subsystem for managing the internal and external heat exchange process of the satellite, ensuring that all parts of the satellite and the satellite-borne instrument are in a normal working temperature range during the whole task period, and realizing the requirements of normal temperature, low temperature, constant temperature, temperature uniformity control and the like. Because solar irradiation alternates with earth shielding, and the influence of solar radiation, earth albedo, earth infrared radiation and the like, the thermal load effect inside and outside the satellite cabin is greatly different, and the satellite can experience high and low temperature environments in the in-orbit flight process, the thermal management subsystem is equivalent to 'skin and clothes' for heat dissipation and heat preservation of the satellite, and plays a vital role in ensuring the normal work of the satellite. Currently, the design trend of satellites is moving towards ultra-large, microminiaturization and high efficiency, the application of high power load is increased, the integration of satellite-borne equipment causes the continuous increase of load power density, and the heat flow of the whole system is continuously improved, so that the requirements on the heat transfer and dissipation capacity, the system integration level, the light weight and the reliability of the satellite thermal management subsystem are increasingly increased. Therefore, a lightweight and efficient thermal management design must be employed to effectively meet the heat dissipation requirements. Thermal management of conventional satellites is divided into two categories, passive thermal management and active thermal management. The passive thermal management has the advantages of simplicity, reliability, long service life, low cost and the like, and is typically realized by developing the layout optimization design of the heating components in the satellite cabin in the prior art. However, the thermal management flexibility of the component layout optimization is poor, the functions are single and limited, the overall temperature field distribution management at the global level is mainly realized, the finer local thermal management requirements of some special precision equipment existing in a satellite cabin cannot be met, for example, devices such as atomic clocks with temperature uniformity requirements, satellite-borne processors and the like are sensitive to the temperature gradient, and devices such as high-precision cameras and spectrometers sensitive to the temperature gradient direction in the component cannot be finely regulated and controlled by the component layout optimization, and the local thermal management requirements of the precision equipment and high-precision instruments with temperature requirements cannot be met. The active heat management method has strong and various functions and high flexibility and precision of heat management, but the device equipment of the heat management is generally larger in volume and energy consumption, lower in reliability and shorter in service life. Disclosure of Invention In order to solve part or all of the technical problems in the prior art, the invention provides a satellite component layout-cabin plate structure integrated optimization design method based on thermal meta-materials, which can improve the service life of a satellite and the on-orbit time of the satellite, has good flexibility and comprehensive functions, and can simultaneously realize global thermal management of a satellite cabin and finer local thermal management aiming at special precise instruments and equipment and the like. The technical scheme of the invention is as follows: The utility model provides a satellite component layout-cabin board structure integrated optimization design method based on thermal metamaterial, which comprises the following steps: geometrically describing a two-dimensional component with a regular geometric shape based on a parameterized level set function, constructing a two-dimensional projection of a three-dimensional shape of the satellite component by using a Heaviside function, and performing interference calculation between the satellite components; selecting a plane four-node rectangular unit discrete design domain based on a steady-state heat conduction balance equation, and representing a satellite component temperature field as an interpolation relation of node temperatures; Encrypting and refining grids of the satellite assembly boundary by utilizing a multi-resolutio