CN109492236B - External heat flow analysis method for spacecraft - Google Patents
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- CN109492236B CN109492236B CN201710812561.5A CN201710812561A CN109492236B CN 109492236 B CN109492236 B CN 109492236B CN 201710812561 A CN201710812561 A CN 201710812561A CN 109492236 B CN109492236 B CN 109492236B
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Abstract
The invention discloses an external heat flow analysis method of a spacecraft, and provides a novel indirect analysis method aiming at the difficulty and trouble of external heat flow analysis, which comprises the following steps: the temperature field is used for calculating the thermal analysis model of the same aircraft, a specially-constructed temperature measuring sheet (2) with a simple model is added, and the temperature of the temperature measuring sheet (2) obtained in the calculation result is converted into the total external heat flow actually absorbed by the surface (1) of the aircraft. The method not only improves the efficiency and the precision of the external heat flow analysis, but also is suitable for space aircrafts with various complex configurations.
Description
Technical Field
The invention relates to an external heat flow analysis method, in particular to an external heat flow analysis method of a space vehicle.
Background
External heat flow analysis is an important link in spacecraft thermal analysis. The external heat flow analysis usually adopts a direct method, namely, the external heat flow data is directly extracted from the result of the same aircraft thermal analysis model calculated based on the temperature field of the spacecraft. However, the method is difficult, and for example, when the thermal configuration of a certain surface of the aircraft and the meshing strategy may not be representative, or an external heat flow condition in a specific angle direction at a specific position needs to be obtained, the flexibility of the method is not enough. Yet another approach is to reconstruct a generally more regular and simplified thermal model of the aircraft surface for specific use in external heat flow analysis. The method can well acquire the external heat flows from the sun and the earth in the total external heat flow, but the simplified model cannot acquire the infrared radiation heat flow from the surface of the peripheral aircraft because the real temperature field is not solved. Therefore, there are currently a series of difficulties or inconveniences in the analysis of the external heat flow of a spacecraft.
Disclosure of Invention
The invention aims to provide an external heat flow analysis method of a space vehicle, which solves the problems that the flexibility of acquiring external heat flow at any position and from any direction is not enough, the defect that infrared radiation heat flow parts from the surfaces of peripheral vehicles cannot be acquired simultaneously exists, and the difficulty or trouble is brought to the external heat flow analysis work in the conventional method.
The method for analyzing the external heat flow of the spacecraft comprises the following specific steps:
first step construction of thermal model of temperature measuring sheet
The temperature measuring sheet takes a planar form. The area of the temperature measuring sheet is smaller than the corresponding surface area of the aircraft, and the relative area is smaller than or equal to 5%. The physical thickness of the temperature measuring sheet is zero. The heat capacity of the temperature measuring sheet is zero. Only one side of the temperature measuring sheet participates in heat radiation and heat transfer, and the solar absorptivity and the infrared hemispherical emissivity of the single side are consistent with those of the corresponding aircraft surface.
Position of the temperature measuring sheet: is positioned at the side of the normal line of the corresponding aircraft surface and is less than or equal to 1cm away from the aircraft surface without interference.
The outer heat flow consistency of the aircraft surface is good: the surface area is a plane and only receives the heat flow outside the sun or the heat flow outside the earth, and the infrared heat flow of other surfaces does not exist, or the infrared heat flow of other surfaces is neglected, or the infrared heat flow of other surfaces is uniformly distributed; the surface area faces the cosmic cold black background, does not receive heat flow outside the sun and heat flow outside the earth, and does not have infrared heat flow of other surfaces, or infrared heat flow of other surfaces is neglected, or infrared heat flow of other surfaces is uniformly distributed.
The number of the temperature measuring pieces is as follows: when the consistency of the external heat flow on the surface of the aircraft is good, only 1 temperature measuring piece is used, and the temperature measuring piece is placed at the geometric center of the surface of the aircraft; when the consistency of the external heat flow on the surface of the aircraft is poor or the consistency of the external heat flow is analyzed, a plurality of temperature measuring sheets are used, and the temperature measuring sheets are uniformly distributed on the surface area of the aircraft.
Posture of the temperature measuring sheet: the normal direction of the surface of the temperature measuring piece participating in heat radiation and heat transfer is consistent with the direction of external heat flow to be analyzed.
Second step to determine the total external heat flux density of the temperature measuring sheet
A temperature measuring sheet is arranged on the surface of an aircraft of the original thermal model of the aircraft. According to the energy balance principle and the thermal radiation fourth power law, at any position at any time, the total external heat flow absorbed by one side participating in thermal radiation heat transfer is equal to the external infrared radiation heat flow, and the thermal balance equation is as follows:
q all ＝q 1 +q 2 +q 3 +q 4 ＝ε h ×σ×T 4 (1)
in the formula (1), q all The total external heat flow density absorbed by the unit area of the temperature measuring sheet; q. q.s 1 The density of the heat flow of the direct solar radiation absorbed by the unit area of the temperature measuring sheet; q. q.s 2 The solar back-illuminated radiation heat flow density absorbed by the unit area of the temperature measuring sheet; q. q.s 3 The earth infrared radiation heat flux density absorbed by the unit area of the temperature measuring sheet; q. q.s 4 The infrared radiation heat flux density from the peripheral component absorbed by the unit area of the temperature measuring sheet; epsilon h The surface infrared hemispherical emissivity of the normal direction of one surface of the temperature measuring piece participating in heat radiation and heat transfer; sigma is the black body radiation constant; t is the thermodynamic temperature.
Thirdly, obtaining the analysis result of external heat flow
According to a normal thermal simulation process, the temperature field calculation of the spacecraft in the mission period is completed by the original aircraft thermal model with the temperature measuring pieces, and the thermal balance temperature T of the temperature measuring pieces at any time in the mission period is obtained while the temperature field of the original aircraft thermal model is obtained. Due to epsilon h And sigma is a known constant, and the total external heat flow absorbed by the temperature measuring sheet at any time, at any position and in the attitude direction is obtained according to the formula (1).
For the condition that only 1 temperature measuring sheet is distributed in the surface area of the aircraft, the calculation result aiming at the temperature measuring sheet is the total external heat flow absorbed by the surface of the corresponding aircraft; and for the condition that a plurality of temperature measuring sheets are uniformly distributed in the surface area of the aircraft, carrying out arithmetic mean on the total external heat flow absorbed by all the temperature measuring sheets to obtain the corresponding total external heat flow absorbed by the surface of the aircraft.
Thus, the spacecraft external heat flow analysis is completed.
The invention is easy to obtain the external heat flow from any direction at any position on the surface of a certain aircraft, improves the efficiency of external heat flow analysis and has stronger engineering practicability.
Drawings
FIG. 1 is a schematic diagram of the arrangement of a temperature measuring chip in the method for analyzing the external heat flow of a spacecraft.
1. Aircraft surface 2 temperature measuring sheet
Detailed Description
The method for analyzing the external heat flow of the spacecraft comprises the following specific steps:
first step construction of a thermal model of a temperature measuring chip 2
The temperature measuring chip 2 takes a planar form. The area of the temperature measuring sheet 2 is smaller than the area of the corresponding aircraft surface 1, and the relative area is less than or equal to 5%. The physical thickness of the temperature measuring piece 2 is zero. The heat capacity of the temperature measuring piece 2 is zero. Only one surface of the temperature measuring sheet 2 participates in heat radiation and heat transfer, and the solar absorptivity and the infrared hemispherical emissivity of the single surface are consistent with those of the corresponding aircraft surface 1.
Position of the temperature measuring piece 2: is located on the side of the normal line of the corresponding aircraft surface 1 and is less than or equal to 1cm away from the aircraft surface 1 without interference.
The external heat flow consistency of the aircraft surface 1 is good: the surface area is a plane and only receives the heat flow outside the sun or the heat flow outside the earth, and the infrared heat flow of other surfaces does not exist, or the infrared heat flow of other surfaces is neglected, or the infrared heat flow of other surfaces is uniformly distributed; the surface area faces the cosmic cold black background and does not receive heat flow outside the sun and heat flow outside the earth, and infrared heat flow of other surfaces does not exist, or the infrared heat flow of other surfaces is neglected, or the infrared heat flow of other surfaces is uniformly distributed.
Number of temperature measurement pieces 2: when the consistency of the external heat flow on the surface 1 of the aircraft is good, only 1 temperature measuring piece 2 is used, and the temperature measuring piece 2 is placed at the geometric center of the surface 1 of the aircraft; when the consistency of the external heat flow on the surface 1 of the aircraft is not good or the consistency of the external heat flow is analyzed, a plurality of temperature measuring pieces 2 are used, and the temperature measuring pieces 2 are uniformly distributed on the area of the surface 1 of the aircraft.
2 postures of the temperature measuring sheet: the normal direction of the side of the temperature measuring sheet 2 participating in heat radiation and transferring heat is consistent with the direction of the external heat flow to be analyzed.
Second step, determining total external heat flow density of temperature measuring chip 2
A temperature measuring sheet 2 is arranged on the surface 1 of the aircraft of the prior thermal model of the aircraft. According to the energy balance principle and the thermal radiation fourth power law, at any position at any time, the total external heat flow absorbed by one side participating in thermal radiation heat transfer is equal to the external infrared radiation heat flow, and the thermal balance equation is as follows:
q all ＝q 1 +q 2 +q 3 +q 4 ＝ε h ×σ×T 4 (1)
in the formula (1), q all The total external heat flow density absorbed by the temperature measuring piece 2 in unit area; q. q.s 1 The density of the heat flow of the direct solar radiation absorbed by the temperature measuring sheet 2 in unit area; q. q of 2 The density of the solar albedo radiation heat flow absorbed by the temperature measuring sheet 2 in unit area; q. q.s 3 The density of the infrared radiation heat flow of the earth absorbed by the temperature measuring piece 2 in unit area; q. q.s 4 The infrared radiation heat flux density from the peripheral component absorbed by the temperature measuring sheet 2 in unit area; epsilon h The surface infrared hemispherical emissivity of the normal direction of one surface of the temperature measuring piece 2 participating in heat radiation and heat transfer; sigma is the black body radiation constant; t is the thermodynamic temperature.
Thirdly, obtaining the analysis result of external heat flow
According to a normal thermal simulation process, the temperature field calculation of the spacecraft in the mission period is completed by the original spacecraft thermal model with the temperature measuring pieces 2, and the thermal balance temperature T of the temperature measuring pieces 2 at any time in the mission period is obtained while the temperature field of the original spacecraft thermal model is obtained. Due to epsilon h And sigma is a known constant, and the total external heat flow absorbed by the temperature measuring piece 2 at any time, at any position and in the attitude direction is obtained according to the formula 1.
For the condition that only 1 temperature measuring piece 2 is distributed in the area of the surface 1 of the aircraft, the calculation result aiming at the temperature measuring piece 2 is the total external heat flow absorbed by the corresponding surface 1 of the aircraft; for the condition that a plurality of temperature measuring sheets 2 are uniformly distributed in the area of the aircraft surface 1, the total external heat flow absorbed by all the temperature measuring sheets 2 is subjected to arithmetic mean to obtain the corresponding total external heat flow absorbed by a certain aircraft surface 1.
Thus, the spacecraft external heat flow analysis is completed.
Claims (1)
1. An external heat flow analysis method of a spacecraft is characterized by comprising the following specific steps:
first step construction of a thermal model of a temperature measuring plate (2)
The temperature measuring sheet (2) is in a plane form; the area of the temperature measuring sheet (2) is smaller than the area of the corresponding aircraft surface (1), and the relative area is less than or equal to 5%; the physical thickness of the temperature measuring sheet (2) is zero; the heat capacity of the temperature measuring sheet (2) is zero; only one side of the temperature measuring sheet (2) participates in heat radiation and heat transfer, and the solar absorptivity and the infrared hemisphere emissivity of the single side are consistent with those of the corresponding aircraft surface (1);
the position of the temperature measuring sheet (2): is positioned at the side of the normal line of the corresponding aircraft surface (1) and is less than or equal to 1cm away from the aircraft surface (1) under the condition of no interference;
the external heat flow consistency of the aircraft surface (1) is good: the surface area is a plane and only receives the heat flow outside the sun or the heat flow outside the earth, and the infrared heat flow of other surfaces does not exist, or the infrared heat flow of other surfaces is neglected, or the infrared heat flow of other surfaces is uniformly distributed; the surface area faces to the cosmic cold black background, does not receive heat flow outside the sun and heat flow outside the earth, does not have infrared heat flow of other surfaces, or ignores the infrared heat flow of other surfaces, or has uniform distribution of the infrared heat flow of other surfaces;
the number of the temperature measuring pieces (2) is as follows: when the consistency of the external heat flow on the surface (1) of the aircraft is good, only 1 temperature measuring piece (2) is used, and the temperature measuring piece (2) is placed at the geometric center of the surface (1) of the aircraft; when the consistency of the external heat flow on the surface (1) of the aircraft is not good or the consistency of the external heat flow is analyzed, a plurality of temperature measuring sheets (2) are used, and the temperature measuring sheets (2) are uniformly distributed in the area of the surface (1) of the aircraft;
the posture of the temperature measuring sheet (2): the normal direction of the surface of the temperature measuring sheet (2) participating in heat radiation and heat transfer is consistent with the direction of external heat flow to be analyzed;
secondly, determining the total external heat flow density of the temperature measuring sheet (2)
Arranging a temperature measuring sheet (2) on the surface (1) of the aircraft of the original thermal model of the aircraft; according to the energy balance principle and the thermal radiation fourth power law, at any position at any time, the total external heat flow absorbed by one side participating in thermal radiation heat transfer is equal to the external infrared radiation heat flow of the side, and the thermal balance equation is as follows:
q all ＝q 1 +q 2 +q 3 +q 4 ＝ε h ×σ×T 4 (1)
in the formula (1), q all Absorbed by the thermometric strip (2) per unit areaTotal external heat flux density; q. q.s 1 The density of the heat flow of the direct solar radiation absorbed by the temperature measuring sheet (2) in unit area; q. q.s 2 The density of solar back-illuminated radiation heat flow absorbed by the temperature measuring sheet (2) in unit area; q. q.s 3 The density of the terrestrial infrared radiation heat flow absorbed by the temperature measuring sheet (2) in unit area; q. q of 4 The infrared radiation heat flux density from the peripheral component absorbed by the temperature measuring sheet (2) in unit area; epsilon h The surface infrared hemispherical emissivity of the normal direction of one surface of the temperature measuring sheet (2) participating in heat radiation heat transfer is adopted; sigma is the black body radiation constant; t is the thermal equilibrium temperature;
thirdly, obtaining the analysis result of external heat flow
According to a normal thermal simulation process, the temperature field calculation of the original aircraft thermal model with the additionally distributed temperature measuring pieces (2) during the mission of the space aircraft is completed, and the thermal balance temperature T of the temperature measuring pieces (2) at any time during the mission is obtained while the temperature field of the original aircraft thermal model is obtained; due to epsilon h And sigma is a known constant, and the total external heat flow absorbed by the temperature measuring sheet (2) at any time, at any position and in the attitude direction is obtained according to the formula (1);
for the condition that only 1 temperature measuring sheet (2) is arranged in the area of the aircraft surface (1), the calculation result aiming at the temperature measuring sheets (2) is the total external heat flow absorbed by the corresponding aircraft surface (1); for the condition that a plurality of temperature measuring sheets (2) are uniformly distributed in the area of the aircraft surface (1), carrying out arithmetic mean on the total external heat flow absorbed by all the temperature measuring sheets (2) to obtain the corresponding total external heat flow absorbed by the aircraft surface (1);
thus, the spacecraft external heat flow analysis is completed.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002334120A (en) * | 2001-05-10 | 2002-11-22 | Mitsubishi Heavy Ind Ltd | Method and device for calculating heat response |
| CN105740594A (en) * | 2014-12-09 | 2016-07-06 | 上海宇航***工程研究所 | Method for computing infrared radiation and reflection radiation heat flows on surface of lunar orbit spacecraft |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002334120A (en) * | 2001-05-10 | 2002-11-22 | Mitsubishi Heavy Ind Ltd | Method and device for calculating heat response |
| CN105740594A (en) * | 2014-12-09 | 2016-07-06 | 上海宇航***工程研究所 | Method for computing infrared radiation and reflection radiation heat flows on surface of lunar orbit spacecraft |
Non-Patent Citations (2)
| Title |
|---|
| "空间可展桁架结构的设计与热分析";张淑杰;《中国博士学位论文全文数据库》;20020615;全文 * |
| 高速飞行器外热流模拟试验装置研究;杨祺等;《真空与低温》;20160228(第01期);全文 * |
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