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CN-122020961-A - Numerical simulation rapid calculation method for satellite antenna device temperature field

CN122020961ACN 122020961 ACN122020961 ACN 122020961ACN-122020961-A

Abstract

The invention provides a numerical simulation rapid calculation method of a satellite antenna device temperature field, which comprises the steps of S1 inputting the size and thermal parameters of all parts of the satellite antenna device, the temperature T1 of the outer surface of a heat insulation material and the temperature T2 of the lower surface of a flanging of an antenna base, S2 establishing a one-dimensional heat transfer model of an antenna housing, calculating the back temperature T1 'of the antenna housing according to the temperature T1 of the outer surface of the heat insulation material, S3 establishing a two-dimensional heat transfer model of the antenna base, calculating the temperature T2' of the antenna patch of the antenna base according to the temperature T2 of the lower surface of the flanging of the antenna base, S4 establishing an integral one-dimensional heat transfer model formed by the antenna patch and a circuit board, calculating the radiation heat exchange quantity qf 0‑1 of the antenna patch and the antenna housing according to the back temperature T1 'of the antenna housing and the radiation heat exchange principle, and calculating the temperature distribution of the integral parts according to the radiation heat exchange quantity qf 0‑1 and T2'. The calculation method can effectively improve the working efficiency of subsequent thermal design on the premise of ensuring the calculation accuracy.

Inventors

  • HAO JIATIAN
  • YANG CHENXI
  • WENG LEI
  • ZHU ZEXU
  • TIAN QINGZHU

Assignees

  • 北京自动化控制设备研究所

Dates

Publication Date
20260512
Application Date
20251224

Claims (7)

  1. 1. The numerical simulation rapid calculation method of the temperature field of the satellite antenna device comprises a heat insulation material, an antenna housing, an antenna base, an antenna patch and a circuit board, and is characterized by comprising the following steps of: S1, inputting the size and thermal parameters of each part of the satellite antenna device, and the temperature T1 of the outer surface of a heat insulation material and the temperature T2 of the lower surface of the flanging of an antenna base; S2, establishing a one-dimensional heat transfer model of the radome, and calculating the back temperature T1' of the radome according to the temperature T1 of the outer surface of the heat insulation material; Step S3, a two-dimensional heat transfer model of the antenna base is established, and the temperature T2' of the antenna patch of the antenna base is calculated according to the temperature T2 of the lower surface of the flanging of the antenna base; And S4, establishing a one-dimensional heat transfer model of the integral component formed by the antenna patch and the circuit board, calculating according to the back temperature T1 'of the antenna housing and a radiation heat exchange principle to obtain the radiation heat exchange quantity qf 0-1 of the antenna patch and the antenna housing, and calculating the temperature distribution of the integral component according to the radiation heat exchange quantity qf 0-1 and T2'.
  2. 2. The method for quickly calculating the numerical simulation of the temperature field of the satellite antenna device according to claim 1, wherein the process of calculating the temperature field simulation of the component in the two-dimensional heat transfer model is as follows: Dividing a component for carrying out temperature field simulation calculation into a plurality of grid cells, enabling the grid cell for calculating the temperature to be P, wherein four grid cells adjacent to the grid cell P are respectively a grid cell W, a grid cell E, a grid cell N and a grid cell S, the grid cell W and the grid cell E are respectively positioned on two lateral sides of the grid cell P, and the grid cell N and the grid cell S are respectively positioned on two longitudinal sides of the grid cell P; The calculation formula of the increase of the thermal energy in the process of the grid cell P from time 0 to time 1 under the two-dimensional non-heat source condition is as follows according to the law of conservation of energy: Wherein c is the specific heat capacity of the component, ρ is the density of the component, k is the thermal conductivity of the component, T is the temperature of the grid cell, the lower right corner mark indicates the specific grid cell, the upper right corner mark 0 represents the temperature at time 0, and 1 represents the temperature at time 1; Δx is the lateral dimension of grid cell P, Δy is the longitudinal dimension of grid cell P, Δt is the time step, and δx e δx w δy n δy s is the distance between the center of grid cell P and the center of grid cell E, W, N, S, respectively; The left side of the formula (1) is the thermal energy change of the grid cell P, and the right side two terms are the input heat of the grid cell in the E, W direction to the grid cell P and the input heat of the grid cell in the N, S direction to the grid cell P respectively.
  3. 3. The method for rapidly calculating the numerical simulation of the temperature field of the satellite antenna device according to claim 1, wherein in the step S1, the data are processed by performing parameterization treatment on the size and the thermal parameters of each component of the satellite antenna device after sorting and sorting, and performing treatment on the heat input conditions of the external environment so that the time intervals of the heat input conditions are consistent, wherein the thermal parameters comprise the density, the specific heat capacity and the thermal conductivity of the materials used by each component.
  4. 4. The method for quickly calculating the numerical simulation of the temperature field of the satellite antenna device according to claim 2, wherein in the step S2, the back temperature T1' of the radome is calculated as follows: The two-dimensional heat transfer model is simplified into a one-dimensional heat transfer model, the integral structure formed by the heat insulation material and the radome is divided into grid cells P1, two grid cells adjacent to the grid cell P1 are respectively grid cell N1 and grid cell S1 along the direction of unidirectional heat conduction of the heat insulation material to the radome, and according to the law of conservation of energy, under the condition of one-dimensional no heat source, the calculation formula of the increase of heat energy in the process from time 0 to time 1 of the grid cell P1 is as follows: Wherein c 1 is the specific heat capacity of the heat insulating material or the radome, ρ 1 is the density of the heat insulating material or the radome, k 1 is the heat conductivity of the heat insulating material or the radome, T is the temperature of the grid unit, the lower right corner mark indicates a specific grid unit, the upper right corner mark 0 indicates the temperature at the moment 0, and 1 indicates the temperature at the moment 1; Δy is the dimension of grid cell P1 in the heat transfer direction, Δt is the time step, dy n and dy s are the distances between the center of grid cell P1 and the centers of grid cells N1, S1, respectively; the left side of the formula (2) is the heat energy change of the grid cell P1, and the right side is the input heat of the grid cell in the N, S direction to the grid cell P1; therefore, the temperature of the grid unit P1 is sequentially and iteratively calculated along the direction of unidirectional heat conduction of the heat insulation material to the radome, and finally the back temperature T1' of the radome can be obtained in an iterative manner; At the beginning of the iteration, one side of the grid cell P1 is a temperature/heat flow boundary, at this time, the input heat of the side is changed to the heat corresponding to T1, and the formula (2) is deformed into the formula (3): At the end of the iteration, one side of the grid cell P1 is an adiabatic boundary, and at this time, the input heat of the side is 0, and the formula (2) is deformed into the formula (4):
  5. 5. the method for quickly calculating the numerical simulation of the temperature field of the satellite antenna device according to claim 2, wherein in step S3, the temperature T2' of the antenna patch of the antenna base is calculated as follows: Dividing the antenna base into grid cells by adopting a two-dimensional heat transfer model, wherein the grid cells are P2, four grid cells adjacent to the grid cell P2 are respectively a grid cell W2, a grid cell E2, a grid cell N2 and a grid cell S2, the grid cell W2 and the grid cell E2 are respectively positioned at the two lateral sides of the grid cell P2, and the grid cell N2 and the grid cell S2 are respectively positioned at the two longitudinal sides of the grid cell P2; The calculation formula of the increase amount of thermal energy in the course of the grid cell P2 from time 0 to time 1 according to the law of conservation of energy is as follows: Wherein c 2 is the specific heat capacity of the antenna base, ρ 2 is the density of the antenna base, k 2 is the thermal conductivity of the antenna base, T is the temperature of the grid cell, the lower right corner mark indicates the specific grid cell, the upper right corner mark 0 indicates the temperature at time 0, and 1 indicates the temperature at time 1; Δx is the lateral dimension of grid cell P2, Δy is the longitudinal dimension of grid cell P2, Δt is the time step, δx e δx w δy n δy s is the distance between the center of grid cell P2 and the centers of grid cells E2, W2, N2, S2, respectively; the left side of the formula (5) is the heat energy change of the grid cell P2, and the right side two terms are the input heat of the grid cell in the E, W direction to the grid cell P2 and the input heat of the grid cell in the N, S direction to the grid cell P2 respectively; therefore, the temperature of the grid unit P2 is sequentially and iteratively calculated along the directions of the transverse and longitudinal heat conduction respectively, and finally the temperature T2' of the antenna patch of the antenna base can be obtained in an iterative manner; At the beginning of the iteration, one side or two sides of the grid cell P2 is a temperature boundary, at this time, the side view is adjacent to a special cell with a cell size of 0, the temperature value T2 of the temperature boundary is the temperature of the special cell, and the formula (5) is deformed into the formula (6) and the formula (7): One side is a temperature boundary: temperature boundaries are on both sides:
  6. 6. the method of claim 1, wherein in step S4, the calculation formula of the radiation heat exchanging amount qf 0-1 between the antenna patch and the radome in the time of 0 to 1 is as follows: Wherein ε S is the emissivity of the heat exchange system formed by the antenna patch and the antenna housing, T 0 Patch is the temperature of the upper surface of the antenna patch 4 to be solved at 0 time, T 0 Antenna housing is the temperature of T1' of the antenna housing 2 at 0 time, A1 and A2 are the upper surface area of the antenna patch and the lower surface area of the antenna housing in the mounting cavity, ε 1 and ε 2 are the emissivity of the antenna patch and the emissivity of the antenna housing, respectively, and C 0 is the blackbody emissivity.
  7. 7. The method for quickly calculating the numerical simulation of the temperature field of the satellite antenna device according to claim 2, wherein in step S4, the calculation process of the temperature distribution of the whole component is as follows: Grid cell division is carried out on the integral component formed by the antenna patch and the circuit board, the grid cell is P3, two grid cells which are adjacent to the grid cell P3 along the direction perpendicular to the plane of the antenna patch are respectively grid cell N3 and grid cell S3, and according to the law of conservation of energy, under the condition of one-dimensional no heat source, the calculation formula of the increase of heat energy in the process from 0 moment to 1 moment of the grid cell P3 is as follows: Wherein c 3 is the specific heat capacity of the antenna patch or the circuit board, ρ 3 is the density of the antenna patch or the circuit board, k 3 is the heat conductivity of the antenna patch or the circuit board, T is the temperature of the grid unit, the lower right corner mark indicates a specific grid unit, the upper right corner mark 0 indicates the temperature at the moment 0, and 1 indicates the temperature at the moment 1, wherein c 3 and ρ 3 respectively select the corresponding values of the components where the grid unit P3 is located; Δx is the lateral dimension of grid cell P3, Δy is the longitudinal dimension of grid cell P3, Δt is the time step, dy n and dy s are the distances between the center of grid cell P3 and the centers of grid cells N3, S3, respectively; the left side of the formula (9) is the heat energy change of the grid cell P3, and the right side is the input heat of the grid cell in the N, S direction to the grid cell P3; therefore, the temperature of the grid unit P3 is sequentially and iteratively calculated along the direction of unidirectional heat conduction from the antenna patch to the circuit board and the direction of unidirectional heat conduction from the circuit board to the antenna patch, and finally the temperature distribution of the integral component formed by the antenna patch and the circuit board can be obtained in an iterative manner; When, at the beginning of the iteration, one side of the grid cell P3 is a radiation boundary, at this time, the input heat of that side is changed to the radiation heat exchange amount qf 0-1 , and the formula (9) is deformed into the formula (10): When one side of the grid cell P1 is a heat conduction boundary, at this time, the input heat of the side is the heat corresponding to T2', and the formula (9) is deformed into the formula (11): Wherein T2'0 is the temperature of the circuit board at time 0 under the boundary condition of T2'.

Description

Numerical simulation rapid calculation method for satellite antenna device temperature field Technical Field The invention belongs to the technical field of temperature field simulation calculation, and relates to a numerical simulation rapid calculation method for a satellite antenna device temperature field. Background The satellite antenna device is a device for information interaction with satellites, and is applied to a satellite antenna device on a high-speed aircraft and faces a severe thermal environment. The internal heat source of the device is negligible, so that the temperature field distribution is mainly influenced by the input of the external environment and the structural design of the device. When the satellite antenna device is designed in structure, the thermal protection requirement cannot be accurately judged due to complex thermal environment conditions. This results in the fact that the thermal design is found to have "over-design" or "under-design" problems after the thermal simulation is completed in the later stages of the structural design flow. After the thermal simulation identifies such problems, the design of the partial structure needs to be updated, which increases work repetition and reduces work efficiency. Disclosure of Invention The present invention aims to solve at least one of the problems of the prior art. Therefore, the invention provides a numerical simulation rapid calculation method for a temperature field of a satellite antenna device, which can effectively improve the working efficiency of subsequent thermal design on the premise of ensuring the calculation accuracy. The technical scheme of the invention is as follows: the numerical simulation rapid calculation method of the temperature field of the satellite antenna device comprises the following steps of: S1, inputting the size and thermal parameters of each part of the satellite antenna device, and the temperature T1 of the outer surface of a heat insulation material and the temperature T2 of the lower surface of the flanging of an antenna base; S2, establishing a one-dimensional heat transfer model of the radome, and calculating the back temperature T1' of the radome according to the temperature T1 of the outer surface of the heat insulation material; Step S3, a two-dimensional heat transfer model of the antenna base is established, and the temperature T2' of the antenna patch of the antenna base is calculated according to the temperature T2 of the lower surface of the flanging of the antenna base; And S4, establishing a one-dimensional heat transfer model of the integral component formed by the antenna patch and the circuit board, calculating according to the back temperature T1 'of the antenna housing and a radiation heat exchange principle to obtain the radiation heat exchange quantity qf 0-1 of the antenna patch and the antenna housing, and calculating the temperature distribution of the integral component according to the radiation heat exchange quantity qf 0-1 and T2'. Further, in the two-dimensional heat transfer model, the process of the simulation calculation of the temperature field of the component is as follows: Dividing a component for carrying out temperature field simulation calculation into a plurality of grid cells, enabling the grid cell for calculating the temperature to be P, wherein four grid cells adjacent to the grid cell P are respectively a grid cell W, a grid cell E, a grid cell N and a grid cell S, the grid cell W and the grid cell E are respectively positioned on two lateral sides of the grid cell P, and the grid cell N and the grid cell S are respectively positioned on two longitudinal sides of the grid cell P; The calculation formula of the increase of the thermal energy in the process of the grid cell P from time 0 to time 1 under the two-dimensional non-heat source condition is as follows according to the law of conservation of energy: Wherein c is the specific heat capacity of the component, ρ is the density of the component, k is the thermal conductivity of the component, T is the temperature of the grid cell, the lower right corner mark indicates the specific grid cell, the upper right corner mark 0 represents the temperature at time 0, and 1 represents the temperature at time 1; Δx is the lateral dimension of grid cell P, Δy is the longitudinal dimension of grid cell P, Δt is the time step, and δx eδxwδynδys is the distance between the center of grid cell P and the center of grid cell E, W, N, S, respectively; The left side of the formula (1) is the thermal energy change of the grid cell P, and the right side two terms are the input heat of the grid cell in the E, W direction to the grid cell P and the input heat of the grid cell in the N, S direction to the grid cell P respectively. Further, in step S1, the data is processed by classifying and sorting the sizes and thermal parameters of each component of the satellite antenna device, and then parameterizing the data, and