Background heat flow numerical analysis method and device

Abstract

The embodiment of the present specification provides a background heat flow numerical analysis method and device, wherein the background heat flow numerical analysis method comprises: performing grid discretization processing on the environment simulation container model, the test tooling model and the spacecraft model to obtain a plurality of system nodes and a plurality of spacecraft nodes; after performing a thermal balance test, calculating the temperature of each system node; after performing a radiation energy propagation test, calculating the relative angular coefficient of the system node, and calculating the relative radiation coefficient of the system node according to the relative angular coefficient; according to the temperature and the relative radiation coefficient of each system node, calculating the background heat flow value of each system node, and calculating the total density of the background heat flow. The embodiment of the present specification integrates multi-dimensional thermal control parameters and intelligent algorithms, and significantly improves the integrity of the complex system thermal environment simulation and the temperature prediction accuracy.

Description

Technical Field

[0001] The embodiments in this specification relate to the field of spacecraft thermal balance test technology, and in particular to methods and apparatus for numerical analysis of background heat flux. Background Technology

[0002] Spacecraft need to maintain a stable operating temperature in the vacuum and cryogenic radiation environment of outer space. Thermal balance testing is a crucial step in verifying the correctness of the spacecraft's thermal design. The external heat flow in thermal balance testing is usually simulated based on the spacecraft's on-orbit heat flow. However, devices such as the ring mold container and test fixtures introduce background heat flow, causing a certain deviation between the external heat flow experienced by the spacecraft during ground testing and the actual on-orbit heat flow, thus affecting the effectiveness of thermal test performance evaluation.

[0003] In thermal equilibrium test systems, devices such as the ring mold container and test fixtures introduce background heat flux, causing a certain deviation between the external heat flux experienced by the spacecraft during ground tests and the actual on-orbit heat flux, thus affecting the effectiveness of thermal test performance evaluation. Existing test and simulation methods for obtaining background heat flux in test systems have limitations, only providing the total value of background heat flux. This makes it impossible to accurately determine the background heat flux values ​​for each device and part, hindering further thermal equilibrium tests. Summary of the Invention

[0004] In view of this, embodiments of this specification provide a method for numerical analysis of background heat flux. One or more embodiments of this specification also relate to a background heat flux numerical analysis apparatus, a computing device, a computer-readable storage medium, and a computer program, to address the technical deficiencies existing in the prior art.

[0005] According to a first aspect of the embodiments of this specification, a method for numerical analysis of background heat flux is provided. The method is applied to a thermal balance test system in virtual space, the system including an environmental simulation container model, a test fixture model, and a spacecraft model. The method includes:

[0006] The environmental simulation container model, the test fixture model, and the spacecraft model are discretized into a grid to obtain multiple system nodes and multiple spacecraft nodes. The system nodes include multiple container model nodes and multiple fixture model nodes. The container model nodes correspond one-to-one with the spacecraft nodes, and the fixture model nodes correspond one-to-one with the spacecraft nodes.

[0007] After performing the thermal balance test, the temperature of each system node is calculated;

[0008] After conducting the radiation energy propagation experiment, the relative angle coefficients of the system nodes are calculated, and the relative radiation coefficients of the system nodes are calculated based on the relative angle coefficients.

[0009] Based on the temperature and relative emissivity of each system node, calculate the background heat flux value and the total background heat flux density of each system node.

[0010] In some embodiments, the step of mesh discretization processing for the environmental simulation container model, the test fixture model, and the spacecraft model includes:

[0011] Perform structured discretization on spacecraft models and experimental tooling models;

[0012] Perform unstructured discretization on the environment simulation container model.

[0013] In some embodiments, the thermal balance test is performed on each part of each model based on preset thermal parameters, optical parameters, thermal boundary parameters, and insulation parameters, and the temperature of each system node is calculated, including:

[0014] Obtain the thermal parameters, optical parameters, thermal boundary parameters, and thermal insulation parameters of each system node, and calculate the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass;

[0015] Calculate the temperature of each system node based on the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass.

[0016] In some embodiments, the calculation steps for the relative angle coefficient include:

[0017] Obtain the propagation paths of multiple radiation rays in the radiation propagation experiment;

[0018] Determine the first ray number of the target ray emitted from the mesh surface of each system node, and the first ray number of the target ray received by each system node;

[0019] Calculate the relative angle coefficient of each system node based on the number of the first ray and the number of the second ray.

[0020] In some embodiments, the steps for calculating the relative radiation coefficient include:

[0021] Obtain the emissivity and grid area of ​​the grid corresponding to each node, as well as the reflectivity of the radiating nodes involved in the radiation path of each node, wherein the sum of the emissivity and reflectivity of the grid corresponding to each node is 1;

[0022] The grayscale coefficient of each system node is calculated based on the relative angle coefficient of each system node, the reflectivity of the radiation node, and the emissivity of the corresponding grid of the spacecraft node corresponding to each system node.

[0023] The relative emissivity of each system node is calculated based on the emissivity, grid area, and grayscale coefficient of the corresponding grid.

[0024] In some embodiments, the calculation steps for the background heat flux value of each system node include:

[0025] Obtain the preset cosmic background temperature;

[0026] Based on the preset Stefan constant, cosmic background temperature, and the temperature and relative emissivity of each system node, the background heat flux value of each system node is calculated.

[0027] In some embodiments, the calculation step of the background total heat flux density includes:

[0028] Obtain the background heat flux value and grid area of ​​each system node;

[0029] Calculate the total heat flux, which represents the sum of the background heat flux values ​​of all system nodes;

[0030] Calculate the total area representing the sum of the grid areas of all system nodes;

[0031] The total background heat flux density is obtained by calculating the quotient of the total heat flux to the total area.

[0032] According to a second aspect of the embodiments of this specification, a background heat flux numerical analysis apparatus is provided, comprising:

[0033] The mesh discretization module is configured to perform mesh discretization on the environmental simulation container model, the test fixture model, and the spacecraft model to obtain multiple system nodes and multiple spacecraft nodes. The system nodes include multiple container model nodes and multiple fixture model nodes. The container model nodes correspond one-to-one with the spacecraft nodes, and the fixture model nodes correspond one-to-one with the spacecraft nodes.

[0034] The first calculation module is configured to calculate the temperature of each system node after performing a thermal balance test.

[0035] The second calculation module is configured to calculate the relative angle coefficients of the system nodes after performing the radiation energy propagation experiment, and to calculate the relative radiation coefficients of the system nodes based on the relative angle coefficients.

[0036] The third calculation module is configured to calculate the background heat flux value and the total background heat flux density of each system node based on the temperature and relative emissivity of each system node.

[0037] In some embodiments, the step of mesh discretization processing for the environmental simulation container model, the test fixture model, and the spacecraft model includes:

[0038] Perform structured discretization on spacecraft models and experimental tooling models;

[0039] Perform unstructured discretization on the environment simulation container model.

[0040] In some embodiments, the thermal balance test is performed on each part of each model based on preset thermal parameters, optical parameters, thermal boundary parameters, and insulation parameters, and the temperature of each system node is calculated, including:

[0041] Obtain the thermal parameters, optical parameters, thermal boundary parameters, and thermal insulation parameters of each system node, and calculate the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass;

[0042] Calculate the temperature of each system node based on the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass.

[0043] In some embodiments, the calculation steps for the relative angle coefficient include:

[0044] Obtain the propagation paths of multiple radiation rays in the radiation propagation experiment;

[0045] Determine the first ray number of the target ray emitted from the mesh surface of each system node, and the first ray number of the target ray received by each system node;

[0046] Calculate the relative angle coefficient of each system node based on the number of the first ray and the number of the second ray.

[0047] In some embodiments, the steps for calculating the relative radiation coefficient include:

[0048] Obtain the emissivity and grid area of ​​the grid corresponding to each node, as well as the reflectivity of the radiating nodes involved in the radiation path of each node, wherein the sum of the emissivity and reflectivity of the grid corresponding to each node is 1;

[0049] The grayscale coefficient of each system node is calculated based on the relative angle coefficient of each system node, the reflectivity of the radiation node, and the emissivity of the corresponding grid of the spacecraft node corresponding to each system node.

[0050] The relative emissivity of each system node is calculated based on the emissivity, grid area, and grayscale coefficient of the corresponding grid.

[0051] In some embodiments, the calculation steps for the background heat flux value of each system node include:

[0052] Obtain the preset cosmic background temperature;

[0053] Based on the preset Stefan constant, cosmic background temperature, and the temperature and relative emissivity of each system node, the background heat flux value of each system node is calculated.

[0054] In some embodiments, the calculation step of the background total heat flux density includes:

[0055] Obtain the background heat flux value and grid area of ​​each system node;

[0056] Calculate the total heat flux, which represents the sum of the background heat flux values ​​of all system nodes;

[0057] Calculate the total area representing the sum of the grid areas of all system nodes;

[0058] The total background heat flux density is obtained by calculating the quotient of the total heat flux to the total area.

[0059] According to a third aspect of the embodiments of this specification, a computing device is provided, comprising:

[0060] Memory and processor;

[0061] The memory is used to store computer-executable instructions, and the processor is used to execute the computer-executable instructions. When the computer-executable instructions are executed by the processor, they implement the steps of the above-described background heat flux numerical analysis method.

[0062] According to a fourth aspect of the embodiments of this specification, a computer-readable storage medium is provided that stores computer-executable instructions that, when executed by a processor, implement the steps of the above-described background heat flux numerical analysis method.

[0063] According to a fifth aspect of the embodiments of this specification, a computer program is provided, wherein when the computer program is executed in a computer, it causes the computer to perform the steps of the above-described background heat flux numerical analysis method.

[0064] At least one embodiment in the examples of this specification significantly improves the completeness of thermal environment simulation and temperature prediction accuracy of complex systems by integrating multi-dimensional thermal control parameters and intelligent algorithms. Attached Figure Description

[0065] Figure 1 This is a flowchart of some embodiments of a background heat flux numerical analysis method provided in some embodiments of this specification;

[0066] Figure 2 These are schematic diagrams of some embodiments of a thermal balance test system provided in this specification;

[0067] Figure 3 This specification provides some embodiments of a thermal balance test system, with each model targeting the background heat flux density distribution on a spacecraft grid surface;

[0068] Figure 4 This is a background total heat flux density distribution in a thermal equilibrium test system provided in some embodiments of this specification;

[0069] Figure 5This is a flowchart of some embodiments of a background heat flux numerical analysis method provided in some embodiments of this specification;

[0070] Figure 6 This is a simplified structural diagram of a background heat flux numerical analysis device provided in some embodiments of this specification;

[0071] Figure 7 This is a structural block diagram of a computing device provided in some embodiments of this specification.

[0072] The reference numerals in the figures include:

[0073] 100. Environmental simulation container model; 1001. Main container model; 1002. Auxiliary container model; 200. Spacecraft model; 300. Test fixture model; 3001. Docking basket model; 3002. Test support model. Detailed Implementation

[0074] Many specific details are set forth in the following description to provide a full understanding of this specification. However, this specification can be implemented in many other ways than those described herein, and those skilled in the art can make similar extensions without departing from the spirit of this specification. Therefore, this specification is not limited to the specific implementations disclosed below.

[0075] The terminology used in one or more embodiments of this specification is for the purpose of describing particular embodiments only and is not intended to limit the scope of the one or more embodiments of this specification. The singular forms “a” and “the” as used in one or more embodiments of this specification and the appended claims are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term “and / or” as used in one or more embodiments of this specification refers to and includes any or all possible combinations of one or more associated listed items. The modifications “a” and “a plurality” as used in this disclosure are illustrative and not restrictive, and those skilled in the art will understand that they should be understood as “one or more” unless the context clearly indicates otherwise.

[0076] It should be understood that although the terms first, second, etc., may be used to describe various information in one or more embodiments of this specification, such information should not be limited to these terms. These terms are only used to distinguish information of the same type from one another. For example, first may also be referred to as second without departing from the scope of one or more embodiments of this specification, and similarly, second may also be referred to as first. Depending on the context, the word "if" as used herein may be interpreted as "when," "when," or "in response to a determination."

[0077] See Figure 1 and Figure 2 , Figure 1 A flowchart of a background heat flux numerical analysis method provided according to some embodiments of this specification is shown. Figure 2 A simplified schematic diagram of the environmental simulation container model 100, the test fixture model 300, and the spacecraft model 200 is shown. The method specifically includes the following steps.

[0078] Step 101: Perform mesh discretization on the environmental simulation container model 100, the test fixture model 300, and the spacecraft model 200 to obtain multiple system nodes and multiple spacecraft nodes.

[0079] In some embodiments, the execution entity of the background heat flux numerical analysis method (such as a preset computing device) can be connected to the target device via a wired or wireless connection. Then, the environmental simulation container model 100, the experimental fixture model 300, and the spacecraft model 200 are discretized into a mesh, resulting in multiple system nodes and multiple spacecraft nodes. The system nodes include multiple container model nodes and multiple fixture model nodes, with each container model node corresponding one-to-one with a spacecraft node, and each fixture model node corresponding one-to-one with a spacecraft node. The aforementioned wireless connection methods may include, but are not limited to, 3G / 4G / 5G / 6G connections, WiFi connections, Bluetooth connections, WiMAX connections, Zigbee connections, UWB (ultra-wideband) connections, and other currently known or future-developed wireless connection methods.

[0080] The environmental simulation container model 100 can refer to a digital model of a sealed cavity used to reproduce the thermal environment of a spacecraft during its on-orbit operation, capable of simulating space thermal boundary conditions such as a vacuum cold black background, solar radiation, and infrared radiation. The test fixture model 300 can refer to a digital model of an auxiliary device supporting the positioning and installation of the spacecraft within the environmental simulation container, possessing functions such as heat conduction and thermal isolation, used to precisely control the heat exchange path between the spacecraft and the container. The spacecraft model 200 can refer to a three-dimensional parametric model containing the spacecraft body and components, such as satellites / spacecraft. Mesh discretization refers to the process of decomposing a continuous three-dimensional geometric model (such as the environmental simulation container, test fixture, and spacecraft model 200) into discrete mesh elements and nodes. Container model nodes can refer to the nodes obtained by mesh discretization of the environmental simulation container model 100. Fixture model nodes can refer to the nodes obtained by mesh discretization of the test fixture model 300. Spacecraft nodes can refer to the nodes obtained by mesh discretization of the spacecraft model 200. System nodes can refer to both container model nodes and tooling model nodes for the sake of subsequent description.

[0081] In some alternative implementations, the steps of mesh discretizing the environment simulation container model 100, the test fixture model 300, and the spacecraft model 200 include: performing structured discretization on the spacecraft model 200 and the test fixture model 300; and performing unstructured discretization on the environment simulation container model 100.

[0082] Structured discretization refers to dividing a geometric model using regularly arranged mesh elements (such as hexahedrons and quadrilaterals), achieving an ordered arrangement of nodes and elements through pre-defined topological relationships. Unstructured discretization refers to a technique that adaptively divides complex geometry using irregular mesh elements (such as tetrahedrons and pyramids), dynamically adjusting element size and shape to fit the surface contour. It should be noted that although different mesh discretization methods are used, the final number of meshes generated for each model is the same, and each model node corresponds one-to-one.

[0083] Step 102: After performing the thermal balance test, calculate the temperature of each system node.

[0084] Performing a thermal equilibrium test requires setting parameters. For example, before conducting the test, the thermophysical properties of materials in different parts of different models can be pre-set, including thermal conductivity, density, and specific heat capacity at constant pressure. Optical parameters, such as solar absorptivity, infrared emissivity, and transmittance, can also be set for different parts of different models. Furthermore, thermal boundary parameters and insulation parameters can be set for different parts of different models. After the thermal equilibrium test is performed, the thermal, optical, thermal boundary, and insulation parameters at each node are collected.

[0085] In some optional implementations, the temperature of each system node is calculated, including: obtaining the thermal parameters, optical parameters, thermal boundary parameters, and insulation parameters of each system node; calculating the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass; and calculating the temperature of each system node based on the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass.

[0086] Specifically, the steps for calculating the temperature of each system node based on the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass include:

[0087] The first step is to obtain the thermal conductivity, density, and specific heat capacity at constant pressure of each system node, the solar absorptivity, infrared emissivity, and transmittance of each system node, the multiple temperature setpoints of each system node's thermal boundary parameters, and the insulation factor and contact thermal resistance factor of each system node's insulation parameters.

[0088] The second step is to calculate the thermal conductivity coefficient based on the temperature setpoint, thermal conductivity, density, specific heat capacity at constant pressure, insulation factor, and contact thermal resistance factor.

[0089] The third step is to calculate the thermal radiation coefficient based on the temperature setpoint, solar absorptivity, infrared emissivity, transmittance, and insulation factor.

[0090] The fourth step is to calculate the node quality based on the grid area and density.

[0091] The fifth step is to determine the total number of nodes as the number of nodes in the heat conduction network.

[0092] The sixth step is to determine the number of thermal contact nodes corresponding to any node set as the number of nodes in the thermal radiation network.

[0093] Step 7: Calculate the temperature of each system node based on the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass.

[0094] The thermal insulation factor refers to a dimensionless parameter characterizing the ability of multi-layer thermal insulation components (such as multi-layer thermal insulation felt in spacecraft, and thermal insulation sleeves for tooling supports) to prevent heat transfer. The contact thermal resistance factor refers to a parameter describing the additional thermal resistance at the contact interface of an assembly (such as the connection between a spacecraft support and a tooling slot, or the mounting surface of an instrument or equipment) due to surface roughness and preload. The thermal conductivity coefficient refers to a comprehensive parameter describing the overall thermal conductivity of a material and its contact interface. The thermal radiation coefficient refers to a parameter characterizing the ability of an object's surface to transfer heat through electromagnetic radiation. The number of nodes in the thermal conduction network refers to the total number of mesh nodes participating in the heat transfer calculation, i.e., the sum of the number of nodes in the container model, tooling model, and spacecraft. The number of nodes in the thermal radiation network refers to the number of nodes participating in the radiative heat transfer calculation, including only surface nodes with direct radiative visibility (such as the outer surface of a spacecraft, the inner wall of a container heat sink, etc.). This number can be obtained from system calculations and will not be described in detail here.

[0095] These specification examples, by integrating multi-dimensional thermal control parameters and intelligent algorithms, significantly improve the completeness of thermal environment simulation and temperature prediction accuracy for complex systems.

[0096] In some optional implementations, the temperature of each system node is calculated based on a preset first calculation formula, as well as the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass. The first calculation formula includes:

[0097]

[0098] Where i represents the i-th system node, j represents the j-th spacecraft node, and c i Let M be the specific heat capacity of node i. i For the mass of node i, Dji It is the heat conduction network coefficient between nodes, E ji is the thermal radiation network coefficient between nodes, T is the node temperature, t is the relative time of the experiment, L is the number of nodes in the heat conduction network, and M is the number of nodes in the thermal radiation network.

[0099] Step 103: After performing the radiation energy propagation test, calculate the relative angle coefficient of the system nodes, and calculate the relative radiation coefficient of the system nodes based on the relative angle coefficient.

[0100] The relative angle coefficient can refer to a dimensionless parameter representing the geometric relationship of radiative energy transfer between two nodal surfaces. The relative emissivity can refer to a comprehensive parameter of radiative heat transfer capacity based on the relative angle coefficient and dynamically corrected material optical parameters, reflecting the actual radiative heat flow transfer efficiency between nodes.

[0101] In some embodiments, the calculation steps of the relative angle coefficient include: obtaining the propagation paths of multiple radiation rays in a radiation propagation experiment; determining the first ray number of the target ray emitted from the grid surface of each system node, and the first ray number of the target ray received by each system node; and calculating the relative angle coefficient of each system node based on the first ray number and the second ray number. Specifically, the Monte Carlo method can be used to calculate the angle coefficient between nodes, and the share of radiation energy emitted by one node reaching another node can be evaluated by randomly simulating a large number of radiation ray propagation paths.

[0102] In some optional implementations, the relative angle coefficient of each system node can be calculated by combining the first ray number and the second ray number using a preset second calculation formula, wherein the second calculation formula includes:

[0103]

[0104] Where N is the number of first rays emitted from the mesh surface of node a, n is the number of second rays reaching the mesh surface of node b, and FF ab is the relative angle coefficient from node a to node b.

[0105] In some optional implementations, the steps for calculating the relative emissivity include: obtaining the emissivity, reflectivity, and grid area of ​​the grid corresponding to each node, wherein the sum of the emissivity and reflectivity of the grid corresponding to each node is 1; calculating the grayscale coefficient of each system node based on the relative angle coefficient of each system node, the reflectivity of the radiating node, and the emissivity of the grid corresponding to the spacecraft node of each system node; and calculating the relative emissivity of each system node based on the emissivity, grid area, and grayscale coefficient of the grid corresponding to each system node.

[0106] In some optional implementations, the grayscale coefficient of each system node is calculated by using a preset third calculation formula, combined with the relative angle coefficient of each system node and the emissivity of the corresponding spacecraft node grid. The third calculation formula includes:

[0107]

[0108] Where i is the i-th system node, j is the j-th spacecraft node, and B ij N is the grayscale coefficient. S For the number of nodes in the object heat transfer network, FF jk ε is the relative angle coefficient between spacecraft node j and radiation node k. j The emissivity of the grid corresponding to the spacecraft node, k is the radiating node number, 1-ε k Let be the reflectivity of the k-th radiating node.

[0109] In some optional implementations, a pre-defined fourth calculation formula is used to calculate the relative emissivity of each system node based on the emissivity, grid area, and grayscale coefficient of the corresponding grid. The fourth calculation formula includes:

[0110] (G rad ) ij =ε i A i B ij

[0111] Where i is the i-th system node, j is the j-th spacecraft node, (G rad ) ij Let ε be the relative radiation coefficient between the i-th system node and the j-th spacecraft node. i Let A be the emission rate of the i-th system node. i Let be the emission rate area of ​​the i-th system node.

[0112] By combining radiation energy propagation experiments with parameter coupling calculations, multi-dimensional and accurate modeling of radiation heat transfer in complex systems was achieved, thereby greatly improving the calculation accuracy.

[0113] Step 104: Calculate the background heat flux value and total background heat flux density for each system node based on its temperature and relative emissivity. The background heat flux value refers to the heat flux intensity per unit area calculated for a single system node under steady-state thermal conditions, based on its temperature parameters and relative emissivity. The total background heat flux density refers to the spatial superposition of background heat flux values ​​for all nodes within the system, reflecting the comprehensive effect of multi-node thermal radiation interactions.

[0114] In some optional implementations, the calculation steps for the background heat flux value of each system node include: obtaining a preset cosmic background temperature; and calculating the background heat flux value of each system node based on the preset Stefan constant, the cosmic background temperature, and the temperature and relative emissivity of each system node.

[0115] In some optional implementations, the environmental simulation container model 100 includes a main container model 1001 and an auxiliary container model 1002. The test fixture model 300 includes a docking basket model 3001 and a test support model 3002. The main container node, the auxiliary container node corresponding to the auxiliary container model 1002, the docking basket node corresponding to the docking basket model 3001, and the test support node corresponding to the test support model 3002 can be selected from the background heat flux values ​​of each system node for precise processing.

[0116] Reference Figure 3 The diagram illustrates the background heat flux density distribution of various models on a spacecraft mesh surface in some embodiments of the present invention.

[0117] In some alternative implementations, the steps for calculating the total background heat flux density include: obtaining the background heat flux value and grid area of ​​each system node; calculating the total heat flux value representing the sum of the background heat flux values ​​of all system nodes; calculating the total area value representing the sum of the grid areas of all system nodes; and calculating the quotient of the total heat flux value and the total area value to obtain the total background heat flux density.

[0118] Reference Figure 4 The background total heat flux density distribution is shown in some embodiments of the present invention.

[0119] The beneficial effects of one of the embodiments in this specification include at least the following: by integrating multi-dimensional thermal control parameters and intelligent algorithms, the integrity of thermal environment simulation of complex systems and the accuracy of temperature prediction are significantly improved.

[0120] The following is in conjunction with the appendix Figure 5 The diagram illustrates a process flow chart of a background heat flux numerical analysis method provided in some other embodiments of this specification, which specifically includes the following steps.

[0121] Step 201: Perform mesh discretization on the environmental simulation container model 100, the test fixture model 300, and the spacecraft model 200 to obtain multiple system nodes and multiple spacecraft nodes.

[0122] Step 202: After performing the thermal balance test, calculate the temperature of each system node.

[0123] Step 203: After performing the radiation energy propagation experiment, obtain the propagation paths of multiple radiation energy rays in the radiation energy propagation experiment.

[0124] Step 204: Determine the first number of target rays emitted from the mesh surface of each system node, and the first number of target rays received by each system node.

[0125] Step 205: Calculate the relative angle coefficient of each system node based on the number of the first ray and the number of the second ray.

[0126] Step 206: Obtain the emissivity and grid area of ​​the corresponding grid for each node, as well as the reflectivity of the radiation nodes involved in the radiation path of each node.

[0127] Step 207: Calculate the grayscale coefficient of each system node based on the relative angle coefficient of each system node, the reflectivity of the radiation node, and the emissivity of the corresponding grid of the spacecraft node corresponding to each system node.

[0128] Step 208: Calculate the relative emissivity of each system node based on the emissivity, grid area, and grayscale coefficient of the corresponding grid.

[0129] Step 209: Calculate the background heat flux value and the total background heat flux density of each system node based on the temperature and relative emissivity of each system node.

[0130] In some embodiments, steps 201-209 are related to Figure 1 The specific implementation of the corresponding steps in those embodiments and the resulting technical effects can be found in the following references. Figure 1 The steps involved will not be elaborated upon here.

[0131] Corresponding to the above method embodiments, this specification also provides embodiments of a background heat flux numerical analysis device. Figure 6 A schematic diagram of the structure of a background heat flux numerical analysis apparatus provided in some embodiments of this specification is shown. For example... Figure 6 As shown, the device includes:

[0132] The mesh discretization module 301 is configured to perform mesh discretization processing on the environmental simulation container model 100, the test fixture model 300, and the spacecraft model 200 to obtain multiple system nodes and multiple spacecraft nodes. The system nodes include multiple container model nodes and multiple fixture model nodes. The container model nodes correspond one-to-one with the spacecraft nodes, and the fixture model nodes correspond one-to-one with the spacecraft nodes.

[0133] The first calculation module 302 is configured to calculate the temperature of each system node after performing a thermal balance test.

[0134] The second calculation module 303 is configured to calculate the relative angle coefficient of the system nodes after performing the radiation energy propagation experiment, and to calculate the relative radiation coefficient of the system nodes based on the relative angle coefficient.

[0135] The third calculation module 304 is configured to calculate the background heat flux value and the total background heat flux density of each system node based on the temperature and relative emissivity of each system node.

[0136] In some alternative implementations, module 301 is also configured as follows:

[0137] In some embodiments, the step of mesh discretization processing for the environmental simulation container model 100, the test fixture model 300, and the spacecraft model 200 includes:

[0138] Structured discretization was performed on spacecraft model 200 and experimental tooling model 300;

[0139] Unstructured discretization is performed on the environment simulation container model 100.

[0140] In some embodiments, the thermal balance test is performed on each part of each model based on preset thermal parameters, optical parameters, thermal boundary parameters, and insulation parameters, and the temperature of each system node is calculated, including:

[0141] Obtain the thermal parameters, optical parameters, thermal boundary parameters, and thermal insulation parameters of each system node, and calculate the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass;

[0142] Calculate the temperature of each system node based on the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass.

[0143] In some embodiments, the calculation steps for the relative angle coefficient include:

[0144] Obtain the propagation paths of multiple radiation rays in the radiation propagation experiment;

[0145] Determine the first ray number of the target ray emitted from the mesh surface of each system node, and the first ray number of the target ray received by each system node;

[0146] Calculate the relative angle coefficient of each system node based on the number of the first ray and the number of the second ray.

[0147] In some embodiments, the steps for calculating the relative radiation coefficient include:

[0148] Obtain the emissivity and grid area of ​​the grid corresponding to each node, as well as the reflectivity of the radiating nodes involved in the radiation path of each node, wherein the sum of the emissivity and reflectivity of the grid corresponding to each node is 1;

[0149] The grayscale coefficient of each system node is calculated based on the relative angle coefficient of each system node, the reflectivity of the radiation node, and the emissivity of the corresponding grid of the spacecraft node corresponding to each system node.

[0150] The relative emissivity of each system node is calculated based on the emissivity, grid area, and grayscale coefficient of the corresponding grid.

[0151] In some embodiments, the calculation steps for the background heat flux value of each system node include:

[0152] Obtain the preset cosmic background temperature;

[0153] Based on the preset Stefan constant, cosmic background temperature, and the temperature and relative emissivity of each system node, the background heat flux value of each system node is calculated.

[0154] In some embodiments, the calculation step of the background total heat flux density includes:

[0155] Obtain the background heat flux value and grid area of ​​each system node;

[0156] Calculate the total heat flux, which represents the sum of the background heat flux values ​​of all system nodes;

[0157] Calculate the total area representing the sum of the grid areas of all system nodes;

[0158] The total background heat flux density is obtained by calculating the quotient of the total heat flux to the total area.

[0159] The above is a schematic scheme of a background heat flux numerical analysis device according to this embodiment. It should be noted that the technical solution of this background heat flux numerical analysis device and the technical solution of the background heat flux numerical analysis method described above belong to the same concept. For details not described in detail in the technical solution of the background heat flux numerical analysis device, please refer to the description of the technical solution of the background heat flux numerical analysis method described above.

[0160] Figure 7 A structural block diagram of a computing device according to some embodiments of this specification is shown. Components of the computing device include, but are not limited to, a memory 401 and a processor 402. The processor 402 is connected to the memory 401 via a bus 403, and a database 405 is used to store data.

[0161] The computing device also includes an access device 404 that enables the computing device to communicate via one or more networks 406. Examples of such networks include Public Switched Telephone Network (PSTN), Local Area Network (LAN), Wide Area Network (WAN), Personal Area Network (PAN), or combinations of communication networks such as the Internet. Access device 404 may include one or more of any type of wired or wireless network interface (e.g., network interface controller (NIC)), such as an IEEE 802.11 Wireless Local Area Network (WLAN) wireless interface, Wi-MAX (Worldwide Interoperability for Microwave Access) interface, Ethernet interface, Universal Serial Bus (USB) interface, cellular network interface, Bluetooth interface, and Near Field Communication (NFC).

[0162] In one embodiment of this specification, the above-described components of the computing device and Figure 7 Other components, not shown, can also be connected to each other, for example, via a bus. It should be understood that... Figure 7 The block diagram of the computing device shown is for illustrative purposes only and is not intended to limit the scope of this specification. Those skilled in the art can add or replace other components as needed.

[0163] Computing devices can be any type of stationary or mobile computing device, including mobile computers or mobile computing devices (e.g., tablet computers, personal digital assistants, laptop computers, notebook computers, netbooks, etc.), mobile phones (e.g., smartphones), wearable computing devices (e.g., smartwatches, smart glasses, etc.) or other types of mobile devices, or stationary computing devices such as desktop computers or personal computers (PCs). Computing devices can also be mobile or stationary servers.

[0164] The processor 402 executes computer-executable instructions, which, when executed by the processor, implement the steps of the aforementioned background heat flux numerical analysis method. The above is an illustrative scheme of a computing device according to this embodiment. It should be noted that the technical solution of this computing device and the technical solution of the aforementioned background heat flux numerical analysis method belong to the same concept. Details not described in detail in the technical solution of the computing device can be found in the description of the technical solution of the aforementioned background heat flux numerical analysis method.

[0165] An embodiment of this specification also provides a computer-readable storage medium storing computer-executable instructions that, when executed by a processor, implement the steps of the above-described background heat flux numerical analysis method.

[0166] The above is an illustrative scheme of a computer-readable storage medium according to this embodiment. It should be noted that the technical solution of this storage medium belongs to the same concept as the technical solution of the background heat flux numerical analysis method described above. For details not described in detail in the technical solution of the storage medium, please refer to the description of the technical solution of the background heat flux numerical analysis method described above.

[0167] An embodiment of this specification also provides a computer program, wherein when the computer program is executed in a computer, it causes the computer to perform the steps of the above-described background heat flux numerical analysis method.

[0168] The above is an illustrative example of a computer program according to this embodiment. It should be noted that the technical solution of this computer program and the technical solution of the aforementioned background heat flux numerical analysis method belong to the same concept. Details not described in detail in the computer program's technical solution can be found in the description of the aforementioned background heat flux numerical analysis method's technical solution.

[0169] The foregoing has described specific embodiments of this specification. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recited in the claims may be performed in a different order than that shown in the embodiments and may still achieve the desired result. Furthermore, the processes depicted in the drawings do not necessarily require the specific or sequential order shown to achieve the desired result. In some embodiments, multitasking and parallel processing are possible or may be advantageous.

[0170] Computer instructions include computer program code, which can be in the form of source code, object code, executable files, or certain intermediate forms. Computer-readable media can include: any entity or device capable of carrying computer program code, recording media, USB flash drives, portable hard drives, magnetic disks, optical disks, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signals, telecommunication signals, and software distribution media, etc. It should be noted that the content included in computer-readable media can be appropriately added to or removed according to the requirements of legislation and patent practice in a jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, computer-readable media do not include electrical carrier signals and telecommunication signals.

[0171] It should be noted that, for the sake of simplicity, the foregoing method embodiments are all described as a series of actions. However, those skilled in the art should understand that the embodiments in this specification are not limited to the described order of actions, because according to the embodiments in this specification, some steps can be performed in other orders or simultaneously. Furthermore, those skilled in the art should also understand that the embodiments described in this specification are all preferred embodiments, and the actions and modules involved are not necessarily essential to the embodiments in this specification.

[0172] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0173] The preferred embodiments disclosed above are merely illustrative of this specification. The optional embodiments do not exhaustively describe all details, nor do they limit the invention to specific implementations. Clearly, many modifications and variations can be made based on the embodiments described in this specification. These embodiments are selected and specifically described in this specification to better explain the principles and practical applications of the embodiments, thereby enabling those skilled in the art to better understand and utilize this specification. This specification is limited only by the claims and their full scope and equivalents.

Claims

1. A numerical analysis method for background heat flux, characterized in that, The method is applied to a thermal equilibrium test system in virtual space, the system including an environmental simulation container model, a test fixture model, and a spacecraft model, and the method includes: The environmental simulation container model, the test fixture model, and the spacecraft model are discretized into a grid to obtain multiple system nodes and multiple spacecraft nodes. The system nodes include multiple container model nodes and multiple fixture model nodes. The container model nodes and the spacecraft nodes are in one-to-one correspondence. After performing the thermal balance test, the temperature of each system node is calculated; After performing the radiation energy propagation test, the relative angle coefficient of the system node is calculated, and the relative radiation coefficient of the system node is calculated based on the relative angle coefficient; Based on the temperature and relative emissivity of each system node, calculate the background heat flux value of each system node, as well as the total background heat flux density; Wherein, the relative angle coefficient refers to the dimensionless parameter of the geometric relationship of radiative energy transfer between the surfaces of two nodes; the relative radiation coefficient refers to the comprehensive parameter of radiative heat transfer capacity based on the relative angle coefficient and the material optical parameters, which are dynamically corrected. The steps for calculating the relative angle coefficient include: Obtain the propagation paths of multiple radiation rays in the radiation propagation experiment; Determine the first number of target rays emitted from the mesh surface of each system node, and the second number of target rays received by each system node; Calculate the relative angle coefficient of each system node based on the first ray number and the second ray number; The steps for calculating the relative emissivity include: Obtain the emissivity and grid area of ​​the grid corresponding to each node, as well as the reflectivity of the radiating nodes involved in the radiation path of each node, wherein the sum of the emissivity and reflectivity of the grid corresponding to each node is 1; The grayscale coefficient of each system node is calculated based on the relative angle coefficient of each system node, the reflectivity of the radiation node, and the emissivity of the corresponding grid of the spacecraft node corresponding to each system node. The relative emissivity of each system node is calculated based on the emissivity, grid area, and grayscale coefficient of the corresponding grid.

2. The method according to claim 1, characterized in that, The steps for mesh discretization of the environmental simulation container model, experimental tooling model, and spacecraft model include: The spacecraft model and the test fixture model were subjected to structured discretization; Unstructured discretization is performed on the environment simulation container model.

3. The method according to claim 1, characterized in that, The thermal balance test is performed on each part of each model based on preset thermal parameters, optical parameters, thermal boundary parameters, and insulation parameters. The calculation of the temperature of each system node includes: Obtain the thermal parameters, optical parameters, thermal boundary parameters, and thermal insulation parameters of each system node, and calculate the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass; The temperature of each system node is calculated based on the thermal conductivity coefficient, thermal radiation coefficient, number of nodes in the thermal conduction network, number of nodes in the thermal radiation network, and node mass.

4. The method according to claim 1, characterized in that, The calculation steps for the background heat flux values ​​of each system node include: Obtain the preset cosmic background temperature; Based on the preset Stefan constant, the cosmic background temperature, and the temperature and relative emissivity of each system node, the background heat flux value of each system node is calculated.

5. The method according to claim 1, characterized in that, The calculation steps for the total background heat flux density include: Obtain the background heat flux value and grid area of ​​each system node; Calculate the total heat flux, which represents the sum of the background heat flux values ​​of all system nodes; Calculate the total area representing the sum of the grid areas of all system nodes; The total background heat flux density is obtained by calculating the quotient of the total heat flux value to the total area value.

6. A background heat flux numerical analysis device, characterized in that, The device is applied to a thermal equilibrium test system in virtual space. The system includes an environmental simulation container model, a test fixture model, and a spacecraft model. The device includes: The mesh discretization module is configured to perform mesh discretization processing on the environmental simulation container model, the test fixture model, and the spacecraft model to obtain multiple system nodes and multiple spacecraft nodes. The system nodes include multiple container model nodes and multiple fixture model nodes, with each container model node corresponding to a spacecraft node and each fixture model node corresponding to a spacecraft node. The first calculation module is configured to calculate the temperature of each system node after performing a thermal balance test; The second calculation module is configured to calculate the relative angle coefficient of the system node after performing the radiation energy propagation experiment, and calculate the relative radiation coefficient of the system node based on the relative angle coefficient; The third calculation module is configured to calculate the background heat flux value and the total background heat flux density of each system node based on the temperature and relative emissivity of each system node. Wherein, the relative angle coefficient refers to the dimensionless parameter of the geometric relationship of radiative energy transfer between the surfaces of two nodes; the relative radiation coefficient refers to the comprehensive parameter of radiative heat transfer capacity based on the relative angle coefficient and the material optical parameters, which are dynamically corrected. The steps for calculating the relative angle coefficient include: Obtain the propagation paths of multiple radiation rays in the radiation propagation experiment; Determine the first number of target rays emitted from the mesh surface of each system node, and the second number of target rays received by each system node; Calculate the relative angle coefficient of each system node based on the first ray number and the second ray number; The steps for calculating the relative emissivity include: Obtain the emissivity and grid area of ​​the grid corresponding to each node, as well as the reflectivity of the radiating nodes involved in the radiation path of each node, wherein the sum of the emissivity and reflectivity of the grid corresponding to each node is 1; The grayscale coefficient of each system node is calculated based on the relative angle coefficient of each system node, the reflectivity of the radiation node, and the emissivity of the corresponding grid of the spacecraft node corresponding to each system node. The relative emissivity of each system node is calculated based on the emissivity, grid area, and grayscale coefficient of the corresponding grid.

7. A computing device, characterized in that, include: Memory and processor; The memory is used to store computer-executable instructions, and the processor is used to execute the computer-executable instructions, which, when executed by the processor, implement the steps of the background heat flux numerical analysis method according to any one of claims 1 to 5.

8. A computer-readable storage medium storing computer-executable instructions, characterized in that, When the computer-executable instructions are executed by the processor, they implement the steps of the background heat flux numerical analysis method according to any one of claims 1 to 5.

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