CN112560316B - Correction method for surface temperature field of space target - Google Patents

Correction method for surface temperature field of space target Download PDF

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CN112560316B
CN112560316B CN202011520886.4A CN202011520886A CN112560316B CN 112560316 B CN112560316 B CN 112560316B CN 202011520886 A CN202011520886 A CN 202011520886A CN 112560316 B CN112560316 B CN 112560316B
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张建伟
姜超
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Abstract

The invention discloses a correction method of a surface temperature field of a space target, and belongs to the technical field of spaceflight. Firstly, selecting a target in a space radiation environment as an example, and carrying out grid division on the example; and then establishing a thermal balance differential equation corresponding to each grid unit by using a finite volume method for the divided grid units and carrying out deformation operation. And respectively multiplying four function terms in the deformed thermal balance differential equation by correction coefficients to obtain a correction equation. Finally, optimizing the correction equation by using a genetic optimization algorithm to obtain an optimal correction coefficient; and substituting the optimal correction coefficient value into the correction equation to be used as a thermal balance differential equation of the new grid unit. And (4) carrying out finite volume method calculation by using a new thermal balance differential equation of the grid unit to obtain the corrected temperature field of each grid unit of the space target, and further obtaining the temperature field of the whole target. The invention has higher universality, improves the correction precision and simultaneously can not reduce the correction speed.

Description

Correction method for surface temperature field of space target
Technical Field
The invention belongs to the technical field of spaceflight, and relates to a correction method of a temperature field of a surface of a space target, which is mainly applied to accurate calculation of the temperature field in the field of space infrared detection and identification.
Background
The method for obtaining the infrared radiation intensity of the target in the prior art comprises two methods of direct measurement and simulation calculation. If the distance between the target and the detector is too far during direct measurement, the accuracy is difficult to guarantee, the measurement difficulty is high, the simulation calculation is relatively easy, the result meeting the accuracy requirement can be obtained, and the economy is better. For simulation calculation, the infrared radiation intensity is mostly calculated from a temperature field, and the precision of the temperature field plays a crucial role in the accuracy of infrared radiation calculation.
In actual engineering, temperature measurement can be carried out at a plurality of positions on the surface of a space target to obtain instantaneous temperature values of the designated positions. Therefore, the surface temperature field of the space target is calculated, the temperature field is corrected by using the measured data, the accuracy of the distribution of the temperature field can be improved, and the temperature field is closer to an actual value, so that the method has important significance in the field of infrared detection and identification when the surface temperature field of the space target is corrected.
Because the space target makes inertial flight outside the atmosphere, the density of air is extremely thin, the influence of thermal convection on the distribution of the surface temperature field of the target can be ignored, and only the radiation heat exchange between the target and the external space is considered during temperature calculation; except the sun and the earth, other stars and radiative heat transfer between the space and the target are ignored. Therefore, the temperature field of the target is calculated by using a finite volume method, and a transient heat balance differential equation is established for each unit, wherein the transient heat balance differential equation comprises the radiation energy of each external space received by the surface of the target and the radiation energy of the interior of the target; and then substituting the calculation equation of each part of energy into a unit heat balance differential equation, adopting a Taylor formula to carry out linearization, arranging into a form only containing a first-order term, and adopting a forward difference method to carry out linearization on a derivative term. Due to the fact that multiple factors such as volume approximation, parameter measurement errors, parameter value errors and the like are directly used for iterative calculation through a linearized equation, the obtained temperature field distribution result is often different from an actual value, and for a space target with surface temperature measuring points, the temperature field obtained through calculation needs to be corrected through the temperature measured value, and the temperature field distribution result which is closer to a real on-orbit state is obtained.
In engineering practice, a few temperature measuring points are usually arranged on the surface of a space target, but because the number of the measuring points is small, a complete temperature field cannot be acquired through measured temperature data.
Disclosure of Invention
In order to solve the problem that the traditional finite volume method cannot accurately obtain a space target temperature field, the invention provides a correction method of the space target surface temperature field, which corrects a thermal balance differential equation in a mathematical sense.
The method for correcting the surface temperature field of the space target comprises the following specific steps:
selecting a target in a space radiation environment as an example, and carrying out grid division on the example;
obtaining a plurality of grid units after grid division;
step two, establishing a heat balance differential equation corresponding to each grid unit by using a finite volume method for the divided grid units and performing deformation operation;
firstly, calculating the temperature field of the target by using a finite volume method, and establishing a transient heat balance differential equation for each grid unit as follows:
Q1+Q2+Q3+Q4+Q5＝Q6+Q7 (1)
wherein Q is1Direct radiant energy of the sun received for the target surface; q2The earth and earth's atmosphere radiant energy received for the target surface; q3Albedo solar radiation energy for the earth received at the target surface; q4Calculating heat conduction energy between adjacent computing units; q5Radiant energy generated by heating of instruments inside the structure; q6Radiant energy to an external space for the target surface; q7Is the energy in the target cell.
Then, the thermal equilibrium differential equation for the ith grid cell is modified as follows:
Figure BDA0002849420840000021
wherein the content of the first and second substances,
Figure BDA0002849420840000022
A1as a function term related to the outward radiation of the grid cells, A2As a function term related to the energy changes within the cells of the grid, A3As a function of the heat transfer between the cells of the grid, A4Is a function term consisting of solar radiation, earth radiation and earth reflected radiation.
In the formula, i is the number of the current grid unit, and j is the number of the adjacent grid unit of the grid unit i; t isiIs the instantaneous temperature of grid cell i; t is a calculation time point; Δ t is the time step of iterative computation; epsiloniIs the thermal radiation emissivity of the grid cell i; σ is Stefan Boltzmann constant; a. theiIs the radiation area of grid cell i; giIs the quality of grid cell i；ciIs the specific heat capacity of grid cell i; a. theijIs the contact area between adjacent grid cells i and j; Δ is the center distance of adjacent grid cells i and j; k is the material thermal conductivity; alpha is alphaiIs the absorptivity of the grid cell i; siExternal heat source term for grid cell i, including Q1、Q2And Q3。
Step three, multiplying four function items in the deformed thermal balance differential equation by correction coefficients respectively to obtain a correction equation;
the method specifically comprises the following steps: for function term A1、A2、A3Are respectively multiplied by correction coefficients a1、a2、a3(ii) a For function term A4Are respectively multiplied by a coefficient a4、a5、a6。
Starting iteration at a step length delta t from the time t equal to 0, and obtaining a correction equation at the time t as follows:
Figure BDA0002849420840000023
Figure BDA0002849420840000031
a1correction coefficients for outward radiation of the grid cells; a is2A correction coefficient of the internal energy change of the grid unit body; a is3A correction factor for the thermal conduction between the grid cells; a is4Is the correction factor for solar radiation; a is5Correction coefficients for the earth radiation; a is6Is the correction factor for the radiation reflected by the earth.
Optimizing the correction equation by using a genetic optimization algorithm to obtain an optimal correction coefficient;
the specific process is as follows:
step 401, randomly selecting a group of correction coefficient values and substituting the correction coefficient values into a correction equation;
step 402, randomly selecting n measuring points in a grid unit, obtaining a temperature calculation value of each measuring point at the t-th moment by using a correction equation, and measuring a temperature actual measurement value of each measuring point;
step 403, calculating the least square P of the target function by using the temperature calculated values and the measured values of all the measuring points;
the objective function is:
Figure BDA0002849420840000032
in the formula, TmThe measured temperature value of the mth measuring point is obtained; t is a unit ofm0The temperature calculation value of the m measuring point is obtained.
Step 404, judging whether the least square P of the target function is smaller than a set precision threshold Q (Q is larger than 0), if so, finishing the optimization algorithm and outputting an optimal correction coefficient value; otherwise, returning to the third step, repeating the temperature iteration from 0 to t to obtain a correction equation at t, then reselecting a group of correction coefficients, and repeating the above process until P is less than Q.
And step five, substituting the optimal correction coefficient value into the correction equation to be used as a new heat balance differential equation of the grid unit.
And step six, calculating by using a new heat balance differential equation of the grid unit through a finite volume method to obtain the corrected temperature field of each grid unit of the space target, and further obtaining the temperature field of the whole target.
The invention has the advantages and positive effects that:
1. a correction method of a surface temperature field of a space target improves the calculation precision of the surface temperature field of the space target, and the distribution of the temperature field obtained by calculation is closer to the actual on-track state;
2. a correction method of a surface temperature field of a space target is characterized in that a mathematical method is used for carrying out linear correction on a function term in a heat balance differential equation, and the method is suitable for space targets in the same environment and has higher universality;
3. when an optimization algorithm is used for iterative calculation, the correction is not carried out aiming at a specific temperature time point, but the iteration is carried out on the temperature calculation process in the whole time period, so that the corrected temperature field distribution obtained by calculation is more reasonable from the integral angle;
4. a correction method of the temperature field of the surface of a space target, because the objective function is the least square of the measured value and calculated value of the temperature, calculate through the way of square sum of error between different measuring points, so this method is effective to a few measuring points too;
5. a method for correcting the surface temp field of space target features that under the condition of more temp measuring points, the correcting precision is increased, but the correcting speed is not decreased.
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FIG. 1 is a schematic overall flow chart of a method for correcting a temperature field of a surface of a space target according to the present invention;
FIG. 2 is a temperature field profile of an uncorrected target selected by an embodiment of the present invention;
FIG. 3 is a flow chart of a method of optimizing correction coefficients according to the present invention;
FIG. 4 is a graph of the variation of the objective function value in the calculation process of the genetic optimization algorithm in the embodiment of the present invention;
FIG. 5 is a target corrected temperature field profile selected by an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
In the prior art, the correction of the temperature field is mainly divided into mathematical and physical corrections. The correction in a physical sense is more difficult and cannot be completely simulated, for example, the radiation of the atmosphere changing along with time is considered, the calculation amount is larger, the real-time performance is reduced, and the correction method has no universality for correction objects in different environments. Therefore, the invention corrects the thermal balance differential equation in the mathematical sense, provides a correction method of the temperature field of the surface of the space target, combines the linear correction method with the genetic optimization algorithm, and corrects the temperature field calculated by the finite volume method by utilizing the actually measured temperature data, so that the temperature field calculated by the finite volume method is closer to the actual on-orbit state, thereby realizing the process of reversely deducing the complete temperature field by a few temperature measuring point data. The invention solves the problem that the traditional finite volume method can not accurately obtain the temperature field of the space target, and the distribution of the surface temperature field of the space target is closer to the actual on-orbit state.
A method for correcting a temperature field of a surface of a space target, as shown in FIG. 1, comprises the following steps:
selecting a target in a space radiation environment as an example, and carrying out grid division on the example;
in the embodiment, the grid units obtained after the selected target arithmetic example is subjected to grid division and the distribution of the temperature field when the temperature field is not corrected are shown in fig. 2;
step two, establishing a heat balance differential equation corresponding to each grid unit by using a finite volume method for the divided grid units, and performing deformation operation;
firstly, the temperature field of the target is calculated by using a finite volume method, and a transient heat balance differential equation is established for each grid unit as follows:
Q1+Q2+Q3+Q4+Q5＝Q6+Q7 (1)
wherein Q is1Direct radiant energy of the sun received for the target surface; q2The earth and earth's atmosphere radiant energy received for the target surface; q3Albedo solar radiation energy for the earth received at the target surface; q4Calculating heat conduction energy between adjacent computing units; q5Radiant energy generated by heating of instruments inside the structure; q6Radiant energy to an external space for the target surface; q7Is the energy in the target cell.
Then, the thermal equilibrium differential equation for the ith grid cell is modified as follows:
Figure BDA0002849420840000041
wherein the content of the first and second substances,
Figure BDA0002849420840000051
A1as a function term related to the outward radiation of the grid cells, A2As a function term related to the energy changes within the cells of the grid, A3As a function of the heat transfer between the cells of the grid, A4Is a function term consisting of solar radiation, earth radiation and earth reflected radiation.
In the formula, i is the number of the current grid unit, and j is the number of the adjacent grid unit of the grid unit i; t isiIs the instantaneous temperature of grid cell i; t is a calculation time point; delta t is the time step of iterative computation; epsiloniIs the thermal radiation emissivity of the grid cell i; σ is Stefan Boltzmann constant; a. theiIs the radiation area of grid cell i; giIs the quality of grid cell i; c. CiIs the specific heat capacity of grid cell i; a. theijIs the contact area between adjacent grid cells i and j; Δ is the center distance of adjacent grid cells i and j; k is the material thermal conductivity; alpha is alphaiIs the absorptivity of the grid cell i; siExternal heat source term for grid cell i, including Q1、Q2And Q3。
Step three, multiplying four function items in the deformed thermal balance differential equation by correction coefficients respectively to obtain a correction equation;
A1possible sources of error are the emissivity of the material, multiplied by a factor a1And (6) correcting. A. the2The possible error is the approximation of the unit volume during the grid division, and for a certain unit body with the same area shape, the error proportion is the same because the volume calculation method is the same, and the error proportion is multiplied by the coefficient a2And (6) correcting. A. the3The error is caused by piecewise linear interpolation, taking into account the error in thermal conductivity, so for A3Multiplying by a coefficient a3And (6) correcting. To A4Multiplying the three parts by a coefficient a respectively4、a5、a6And (6) correcting.
Starting iteration with the step Δ t from the time when t is 0, the correction equation at the time t is obtained as follows:
Figure BDA0002849420840000052
step four: optimizing the correction equation by using a genetic optimization algorithm to obtain an optimal correction coefficient;
in this embodiment, three measuring points are randomly selected in the temperature field shown in fig. 2, and a least square method of measured values and calculated values of the temperature of the measuring points is used as an optimization criterion to optimize the temperature calculation iterative process in the whole time period;
the specific process of the genetic optimization algorithm is shown in fig. 3 and is illustrated as follows:
step 401, a genetic optimization algorithm randomly selects a group of correction coefficient values and substitutes the correction coefficient values into a correction equation to obtain a calculation formula of a temperature calculation value;
step 402, calculating a least square P of temperature calculation values and actual measurement values of three measurement points at the t-th moment through an objective function;
the objective function is:
Figure BDA0002849420840000053
in the formula, m is a measuring point number; n is the total number of measuring points, and n is 3 in the embodiment; t ismThe measured temperature value of the mth measuring point is obtained; t ism0The temperature calculation value of the m measuring point is obtained.
Step 403, setting a precision threshold Q (Q >0), judging whether the objective function value P is smaller than Q, if so, completing the optimization algorithm, and outputting a result to obtain an optimized correction coefficient value; if not, returning to the third step, repeating the temperature iteration from 0 to t to obtain a correction equation at t, then reselecting a group of correction coefficients by the genetic optimization algorithm, optimizing, and performing circular operation until P is less than Q.
The variation of the objective function value in the calculation process of the genetic optimization algorithm is shown in fig. 4, and it can be seen that the sum of the squares of errors between the calculated temperature value and the measured temperature value of the optimized temperature field at the measuring point is reduced to be within 0.05K.
In this embodiment, the result of the optimization obtained is: a is1＝1.4556，a2＝0.9938，a3＝1.0038，a4＝1.4963，a5＝0.946，a6＝0.8804。
Substituting the optimization result of the correction coefficient into a correction equation to obtain a new unit heat balance differential equation;
the new differential equation for the cell thermal equilibrium is:
Figure BDA0002849420840000061
step six: performing finite volume method calculation by using a new unit thermal balance differential equation (10) to obtain a temperature field after space target correction, as shown in fig. 5;
comparing fig. 5 with fig. 2, it can be seen that the distribution of the whole temperature field is basically unchanged, but the surface temperature value changes after being corrected, which is closer to the actual state, and meets the actual requirement of the engineering on the temperature field correction.

Claims (2)

1. A method for correcting a surface temperature field of a space target is characterized by comprising the following specific steps:
selecting a target in a space radiation environment as an example, and carrying out grid division on the example;
obtaining a plurality of grid units after grid division;
step two, establishing a heat balance differential equation corresponding to each grid unit by using a finite volume method for the divided grid units and performing deformation operation;
the differential equation for the thermal equilibrium for the ith grid cell is modified as follows:
Figure FDA0002849420830000011
wherein the content of the first and second substances,
Figure FDA0002849420830000012
A1as a function term related to the outward radiation of the grid cells, A2As a function term related to the energy changes within the cells of the grid, A3As a function of the heat transfer between the cells of the grid, A4Is a function term consisting of solar radiation, earth radiation and earth reflected radiation;
in the formula, i is the number of the current grid unit, and j is the number of the adjacent grid unit of the grid unit i; t isiIs the instantaneous temperature of grid cell i; t is a calculation time point; delta t is the time step of iterative computation; epsiloniIs the thermal radiation emissivity of the grid cell i; σ is Stefan Boltzmann constant; a. theiIs the radiation area of grid cell i; giIs the quality of grid cell i; c. CiIs the specific heat capacity of grid cell i; a. theijIs the contact area between adjacent grid cells i and j; Δ is the center distance of adjacent grid cells i and j; k is the material thermal conductivity; alpha is alphaiIs the absorptivity of the grid cell i; siExternal heat source term for grid cell i, including Q1、Q2And Q3；
Step three, multiplying four function items in the deformed thermal balance differential equation by correction coefficients respectively to obtain a correction equation;
the method specifically comprises the following steps: for function term A1、A2、A3Are respectively multiplied by correction coefficients a1、a2、a3(ii) a For function term A4Are respectively multiplied by a coefficient a4、a5、a6；
Starting iteration with the step Δ t from the time when t is 0, the correction equation at the time t is obtained as follows:
Figure FDA0002849420830000013
a1correction coefficients for outward radiation of the grid cells; a is2Correction system for internal energy variation of grid unit bodyCounting; a is a3A correction factor for the thermal conduction between the grid cells; a is4A correction factor for solar radiation; a is5Correction coefficients for the earth radiation; a is6A correction factor for the earth's reflected radiation;
optimizing the correction equation by using a genetic optimization algorithm to obtain an optimal correction coefficient;
the specific process is as follows:
step 401, randomly selecting a group of correction coefficient values and substituting the correction coefficient values into a correction equation;
step 402, randomly selecting n measuring points in a grid unit, obtaining a temperature calculation value of each measuring point at the t-th moment by using a correction equation, and measuring a temperature actual measurement value of each measuring point;
step 403, calculating the least square P of the target function by using the temperature calculated values and the measured values of all the measuring points;
the objective function is:
Figure FDA0002849420830000021
in the formula, TmThe measured temperature value of the mth measuring point is obtained; t ism0Calculating the temperature of the mth measuring point;
step 404, judging whether the least square P of the target function is smaller than a set precision threshold Q (Q >0), if so, finishing the optimization algorithm and outputting an optimal correction coefficient value; otherwise, returning to the third step, repeating the temperature iteration at the time from 0 to t to obtain a correction equation at the time t, then reselecting a group of correction coefficients, and repeating the process until P is less than Q;
substituting the optimal correction coefficient value into a correction equation to serve as a new heat balance differential equation of the grid unit;
and step six, calculating by using a new heat balance differential equation of the grid unit through a finite volume method to obtain the corrected temperature field of each grid unit of the space target, and further obtaining the temperature field of the whole target.
2. The method for correcting the surface temperature field of the space target according to claim 1, wherein in the second step, the temperature field of the target is calculated by using a finite volume method, and a transient heat balance differential equation is established for each grid cell as follows:
Q1+Q2+Q3+Q4+Q5＝Q6+Q7 (1)
wherein Q is1Direct radiant energy of the sun received for the target surface; q2The earth and earth's atmosphere radiant energy received for the target surface; q3Albedo solar radiation energy for the earth received at the target surface; q4Calculating heat conduction energy between adjacent computing units; q5Radiant energy generated by heating of instruments within the structure; q6Radiant energy to an external space for the target surface; q7Is the energy in the target cell.
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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012109378A2 (en) * 2011-02-08 2012-08-16 Indiana University Research And Technology Corporation Ion mobility spectrometry and the use of the sequential elimination technique
CN104121992A (en) * 2014-07-10 2014-10-29 上海宇航系统工程研究所 Method for infrared radiation full-task airspace dynamic characteristics analysis of space target
CN109580698A (en) * 2018-12-27 2019-04-05 北京航天长征飞行器研究所 Target heat radiation analysis method in space-environment simulator

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012109378A2 (en) * 2011-02-08 2012-08-16 Indiana University Research And Technology Corporation Ion mobility spectrometry and the use of the sequential elimination technique
CN104121992A (en) * 2014-07-10 2014-10-29 上海宇航系统工程研究所 Method for infrared radiation full-task airspace dynamic characteristics analysis of space target
CN109580698A (en) * 2018-12-27 2019-04-05 北京航天长征飞行器研究所 Target heat radiation analysis method in space-environment simulator

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
空间目标表面温度场分布模型研究;张志勇 等;《计算机仿真》;20100615(第06期);全文 *

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