Spacecraft external heat flow simulation device and method based on photo-thermal fusion

Abstract

The invention provides a spacecraft external heat flow simulation device and method based on photo-thermal fusion. The external heat flow device comprises an infrared lamp heating system and a halogen lamp system. The infrared lamp heating system is used for heating the surface of the spacecraft to an examination temperature, and the halogen lamp system is used for illumination reaction of the surface of the spacecraft. The infrared lamp heating system and the halogen lamp illumination alternating system are arranged on the front face of the cell panel. The two sets of lamp assemblies utilize reflecting surface structures in a parabola form, so that the radiation quantity of a heat source and light in the infrared lamp assembly to a space environment heat sink is reduced, and the heating efficiency of the heat source and the illumination efficiency of the light source are improved; the overall envelope size of the two sets of lamp assemblies is larger than the surface size of a test object cell panel. The problem of low conversion from light energy to electric energy during a solar panel thermal vacuum test is solved, the illumination intensity of the external heat flow device and the current output of the panel during the test are improved, and the functional assessment of the panel is enhanced.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft environment simulation, and in particular, relates to a spacecraft external heat flow simulation device and method based on photothermal fusion. Background Art

[0002] Solar panels are an important part of the power subsystem and are responsible for the energy supply of spacecraft. Solar panels are directly exposed to outer space. When they enter the light area from the shadow area or the shadow area from the light area, the surface components are subjected to alternating stress caused by the rapid temperature change due to the parallel irradiation of sunlight or the cold background radiation of space. Therefore, in order to verify that they meet the requirements of the on-orbit environment, the panels must first be screened for thermal vacuum environmental stress on the ground, thereby exposing the potential defects of the panels, eliminating early product failures, and improving their reliability in orbit.

[0003] In the ground thermal vacuum test of existing spacecraft solar panels, the surface temperature of the panels has always been the focus of the assessment, and the power generation of the cells is often ignored. Infrared lamps are used as a way to simulate external heat flow. Their spectrum is mainly concentrated in the infrared range and is mainly used to heat the surface temperature of the panels. Infrared lamps have a small visible light band, and the amount of electricity generated during the thermal vacuum test of solar panels accounts for about 4% of the design value. In this scenario, the thermal vacuum test cannot cover the assessment of the function of the cells.

[0004] Patent document CN103600851A provides a high heat flux simulator for vacuum thermal testing of spacecraft, which mainly includes an infrared lamp array, a high-temperature insulation component unit, a mobile unit, a temperature measurement unit and a temperature control unit, wherein the infrared lamp tubes in the infrared lamp array are provided with a reflection screen, and a plurality of infrared lamps are arranged and combined into an infrared lamp array according to the requirements of heat flux density and uniformity. The infrared lamp array is surrounded by baffles, and a high-temperature multi-layer insulation component is installed between the infrared lamp and the mounting base plate and the baffle, so as to limit the high-temperature area to the area surrounded by the illuminated surface of the specimen and the high-temperature insulation component of the infrared lamp array.

[0005] Therefore, in order to take into account the assessment of the power generation function of the solar cells during the vacuum test of the spacecraft solar panels, it is necessary to design a set of photothermal fusion external heat flow simulation devices, which can not only meet the temperature assessment requirements during the thermal vacuum test of the solar panels, but also enable the solar panels to generate electricity close to the design value. Summary of the invention

[0006] In view of the defects in the prior art, the purpose of the present invention is to provide a spacecraft external heat flow simulation device and method based on photothermal fusion.

[0007] According to the present invention, a spacecraft external heat flow simulation device based on photothermal fusion includes: an infrared lamp array, a halogen tungsten lamp array;

[0008] The infrared lamp array and the halogen tungsten lamp array are installed in parallel on the front of the solar panel to form an array arrangement;

[0009] The infrared lamp array heats the surface of the solar panel to the test temperature;

[0010] An array of tungsten halogen lamps is used to react to light on the surface of the solar panel.

[0011] Preferably, the outer envelopes of the infrared lamp array and the halogen tungsten lamp array are both beyond the boundaries of the surface size of the test object solar panel.

[0012] Preferably, the single infrared lamps and the single halogen tungsten lamps are arranged in equal rows and columns;

[0013] The number of rows of light arrays is odd, infrared light arrays and halogen lights are arranged alternately, equidistant from top to bottom, and infrared light arrays are arranged in the first row

[0014] Preferably, each infrared lamp and halogen tungsten lamp have the same or similar shape and size, wherein "similar" means that the length difference is within 2 cm;

[0015] The infrared lamp and the halogen tungsten lamp are installed on a parabolic lampshade lamp assembly of the same size, with the back of the lamp tube facing the parabolic lampshade and the reflective surface of the parabolic lampshade facing the front of the solar panel;

[0016] The axis of the lamp tube is located at the focus of the reflective surface of the parabolic lampshade. The parabolic lampshade is used to parallelly reflect the electromagnetic waves from the back of the infrared lamp and the halogen tungsten lamp to the solar panel. The inner and outer surfaces of the parabolic lampshade are affixed with polyimide aluminum-plated secondary surface reflectors, and the reflectivity of the parabolic lampshade is greater than 0.9.

[0017] Preferably, during the thermal vacuum test, the light radiated by the halogen tungsten lamp onto the parabolic lampshade is reflected onto the surface of the spacecraft in the form of parallel light; the power of a single halogen tungsten lamp is determined before the test, and the test is carried out according to the layout of the halogen tungsten lamp array, the standard battery cell is placed where the battery panel is located, the halogen tungsten lamp array is turned on, and the power of the halogen tungsten lamp is adjusted so that the current of the standard battery cell reaches the target value, which corresponds to a heat flux of 1410W / m 2 , obtain the power of a single halogen tungsten lamp.

[0018] Preferably, during the thermal vacuum test, the heat flux radiated by the infrared lamp to the parabolic lampshade is reflected to the surface of the spacecraft in the form of parallel light; the infrared lamp array controls the solar panels in partitions, and a temperature-controlled thermocouple is arranged in each partition to heat or cool the temperature-controlled thermocouple to the target temperature in stages.

[0019] According to the present invention, a method for manufacturing a spacecraft external heat flow simulation device based on photothermal fusion includes:

[0020] The optical simulation software is used to simulate the illumination uniformity of the sorted halogen tungsten lamp array, determine the horizontal and vertical spacing of the halogen tungsten lamp array and the spacing to the front of the solar panel, and obtain the preliminary layout of the halogen lamp array;

[0021] After the preliminary layout, the halogen tungsten lamp array uses a standard cell to measure the light intensity close to the front of the solar panel, confirming that the light intensity reaching the front of the solar panel is 1410W / m 2 Among them, a standard cell is placed at a certain distance from the halogen tungsten lamp array, that is, where the front of the solar panel is located during the thermal vacuum test. The standard cell has a calibrated light intensity of 1410W / m 2 Determine the wattage of the tungsten-halogen lamp.

[0022] Determine the light intensity obtained. If it is 1410W / m 2 If the lamp is within the set range nearby, it is determined that the layout of the halogen tungsten lamp array meets the design requirements, and the power of a single lamp in the halogen tungsten lamp array is recorded.

[0023] Preferably, the infrared lamp array after sorting is simulated for illumination uniformity and illumination area confirmation using optical simulation software, the rationality of the horizontal and vertical spacing of the infrared lamp array is checked, and the horizontal and vertical spacing of the infrared lamp array and the spacing to the front of the solar panel are determined;

[0024] Thermal vacuum test or thermal simulation of solar panels is carried out according to the layout of infrared lamp array to explore the heating capacity of infrared lamp array and confirm that the maximum temperature value and temperature uniformity of the front of solar panels are less than 0.5℃; the infrared lamp array and halogen lamp array are arranged on the front of solar panels, the infrared lamps are arranged in odd rows, and the halogen tungsten lamps are arranged in even rows;

[0025] The highest temperature value obtained is determined. If it is greater than 135°C or other set values ​​and the temperature uniformity is less than 0.5°C, it is determined that the infrared lamp array layout meets the design requirements.

[0026] A method for using the spacecraft external heat flow simulation device based on photothermal fusion provided by the present invention comprises:

[0027] Step 1: Turn on all the halogen tungsten lamp arrays during the thermal vacuum heating stage, and the infrared lamp array heats up the solar panel according to the set method;

[0028] Step 2: Turn off all halogen tungsten lamp arrays at the beginning of thermal vacuum cooling, and the infrared lamp array cools the solar panel according to the set method.

[0029] Preferably, before the test, the halogen tungsten lamp array uses a standard battery cell to calibrate the light intensity to determine the applied power of each halogen tungsten lamp during the test condition.

[0030] Compared with the prior art, the present invention has the following beneficial effects:

[0031] 1. The present invention increases the intensity of light reaching the solar panel during the thermal vacuum test by adding a halogen tungsten lamp array, increases the amount of electricity generated by the battery cell, assesses the function of the battery cell during the thermal vacuum test, and solves the problem of low power generation of the battery cell during the thermal vacuum test of the existing solar panel.

[0032] 2. The present invention has been verified through experiments that the layout of the solidified infrared lamp array and the halogen tungsten lamp array is suitable for different types of battery panel sizes and working conditions, achieving the purpose of de-modeling and generalization.

[0033] 3. The two sets of lamp assemblies provided by the infrared lamp heating system and halogen lamp system of the present invention utilize a parabolic reflective surface structure to reduce the radiation amount of the heat source and light in the infrared lamp assembly to the heat sink of the space environment, thereby improving the heating efficiency of the heat source and the lighting efficiency of the light source.

[0034] 4. The present invention solves the problem of low conversion of light energy into electrical energy during thermal vacuum testing of solar panels, improves the light intensity of the external heat flux device and the current output of the solar panel during the test, and strengthens the functional assessment of the solar panel. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0036] Figure 1 This is a schematic diagram of the light array layout;

[0037] Figure 2 This is a schematic diagram of the simulation of the uniformity of illumination of the lamp array;

[0038] Figure 3 This is the working flow chart of infrared light array.

[0039] The figure shows:

[0040] DETAILED DESCRIPTION

[0041] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0042] The present invention relates to the technical field of spacecraft environment simulation, and discloses a photothermal fusion spacecraft thermal test external heat flow device, the external heat flow device comprising an infrared lamp heating system and a halogen lamp system. The infrared lamp heating system is used to heat the surface of the spacecraft to the test temperature, and the halogen lamp system is used for the light reaction of the surface of the spacecraft. The infrared lamp heating system and the halogen lamp system are arranged on the front of the solar panel. The two sets of lamp assemblies provided by the infrared lamp heating system and the halogen lamp system utilize a parabolic reflective surface structure to reduce the radiation amount of the heat source and light in the infrared lamp assembly to the heat sink of the space environment, thereby improving the heating efficiency of the heat source and the lighting efficiency of the light source; the overall envelope size of the two sets of lamp assemblies is larger than the surface size of the test object solar panel. The present invention solves the problem of low conversion of light energy into electrical energy during the thermal vacuum test of solar panels, improves the light intensity of the external heat flow device and the current output of the solar panel during the test, and strengthens the functional assessment of the solar panel.

[0043] A photothermal fusion spacecraft thermal test external heat flow device provided by the present invention includes: an infrared lamp array and a halogen tungsten lamp array.

[0044] The infrared lamp array and halogen tungsten lamp array are installed in parallel to the front of the solar panel. The infrared lamp array is used to heat the surface of the solar panel, and the halogen tungsten lamp array is used to generate electricity for the solar panel and standard cells (before the test, the halogen tungsten lamp array uses standard cells to calibrate the light intensity to determine the applied power of each halogen tungsten lamp during the test conditions. Specifically, the halogen tungsten lamp array after sorting uses standard cells to measure the light intensity close to the front of the solar panel to confirm that the light intensity reaching the front of the solar panel is 1410W / m 2 That is, a certain number of standard cells are placed at a certain distance from the halogen tungsten lamp array, that is, where the front of the solar panel is located during the thermal vacuum test. The standard cells are calibrated to have a light intensity of 1410W / m 2 Determine the power of the halogen tungsten lamp). The halogen tungsten lamp array is based on the light intensity reaching 1410W / m 2 Designed to be turned on during the heating and high temperature holding stages of thermal vacuum testing.

[0045] The infrared lamp array and the halogen lamp array are arranged in arrays, and the individual infrared lamps and halogen tungsten lamps are arranged in equal rows and columns. The outer envelope of the infrared lamp array and the halogen tungsten lamp array exceeds the boundary of the surface size of the test object solar panel to compensate for the phenomenon of low temperature and weak light at the edge of the solar panel. In the preferred example, the number of rows of the lamp array is an odd number of rows, and the infrared lamp array and the halogen lamp are arranged alternately, equidistant from top to bottom, and the infrared lamp array is arranged in the first row.

[0046] Each infrared lamp and halogen tungsten lamp in the infrared lamp array have the same or similar shape and size, and the length difference between the infrared quartz lamp and the halogen tungsten lamp is within 2 cm. They are installed on parabolic lampshade lamp assemblies of the same size, which are infrared lampshades and halogen tungsten lampshades respectively. The backs of the infrared quartz and halogen tungsten lamp tubes face the parabolic lampshade, and the reflecting surface of the parabolic lampshade faces the front of the solar panel to improve the uniformity of heat flow and illumination.

[0047] The axis of the lamp tube is located at the focus of the parabolic lampshade reflective surface. The parabolic lampshade is used to parallel reflect the electromagnetic waves from the back of the infrared quartz lamp and the halogen tungsten lamp to the solar panel. The inner and outer surfaces of the parabolic lampshade are affixed with polyimide aluminum-plated secondary surface reflectors, and the reflectivity of the parabolic lampshade is greater than 0.9.

[0048] The infrared quartz lamp is Philips 13169X / 98 infrared quartz lamp, and the halogen tungsten lamp is Philips double-ended halogen tungsten lamp.

[0049] Each temperature control zone formed by the infrared light array corresponds to a temperature control sensor on the surface of the spacecraft.

[0050] In the infrared lamp array, the 300mm×250mm (horizontal×vertical) infrared lamp array layout heats the front of the solar panel to 135°C, meeting the high temperature requirements of the existing conventional solar panel thermal vacuum test on orbit. In the halogen tungsten lamp array, the 300mm×250mm (horizontal×vertical) halogen tungsten lamp array layout can meet the light arrival intensity of 1410W / m 2 Require.

[0051] The present invention will be described in more detail below.

[0052] The first purpose of the present invention is to increase the power generation of the solar panel during the heating and high temperature maintenance stages of the solar panel thermal vacuum test. The second purpose of the present invention is to heat the solar cells on the front of the solar panel to above 135°C to meet the conventional solar panel thermal vacuum temperature assessment. The third purpose of the present invention is to determine the power of the halogen tungsten lamp and the use of the two sets of lamp arrays during the thermal vacuum test.

[0053] In order to achieve the first purpose of the present invention, the power generation of the solar panel during the heating and high temperature maintenance stages of the thermal vacuum test of the solar panel is improved. The present invention adopts a halogen tungsten lamp array. During the thermal vacuum test, the light radiated by the halogen tungsten lamp onto the parabolic lampshade is reflected to the surface of the spacecraft in the form of parallel light.

[0054] The power of a single halogen lamp is determined before the test. The standard cell is placed where the solar panel is located according to the layout of the halogen lamp array. The halogen lamp array is turned on and the power of the halogen lamp is adjusted so that the current of the standard cell reaches the target value (corresponding to a heat flow of 1410W / m 2 ) to obtain the power of a single halogen tungsten lamp.

[0055] The inner and outer surfaces of the parabolic lampshade 5 are affixed with polyimide aluminum-plated secondary surface reflectors with a reflectivity greater than 0.9, which improves the reflection effect of the parabolic lampshade 2 and reduces the radiation heat of the outer side of the parabolic lampshade 5 to the space environment heat sink.

[0056] The 300mm×250mm (horizontal×vertical) halogen tungsten lamp array layout can increase the front light intensity of the solar panel 6 to 1410W / m 2 .

[0057] To achieve the first object of the present invention, the following manufacturing steps are included:

[0058] The first step: designing the parabolic lampshade and its appearance; pasting a polyimide aluminum-plated secondary surface reflector on the surface of the parabolic lampshade.

[0059] Step 2: Arrange the single halogen tungsten lamp assemblies at fixed intervals in the horizontal and vertical directions to form an orderly halogen tungsten lamp array, wherein the outer envelope of the halogen tungsten lamp array is larger than the size of the test object solar panel; wherein the outer envelope width of the halogen tungsten lamp array is larger than the surface width of the test object solar panel, and the outer envelope height is close to the surface height of the test object solar panel;

[0060] Step 3: Using optical simulation software to simulate the illumination uniformity of the sorted halogen tungsten lamp array, determine the horizontal and vertical spacing of the halogen tungsten lamp array and the spacing to the front of the solar panel, and obtain a preliminary layout of the halogen lamp array;

[0061] Step 4: Use standard cells to measure the light intensity close to the front of the solar panel in the sorted halogen tungsten lamp array to confirm that the light intensity reaching the front of the solar panel is 1410W / m 2 Specifically, a certain number of standard cells were placed at a certain distance from the halogen tungsten lamp array (where the front of the cell panel is located during the thermal vacuum test), and the standard cells were calibrated to have a light intensity of 1410 W / m 2 Determine the wattage of the tungsten-halogen lamp.

[0062] Step 5: Determine the light intensity. If it is 1410W / m 2 If the value is near or other set values, it is determined that the halogen tungsten lamp array layout meets the design requirements, and the design requirements can be met.

[0063] Step 6: Record the power of a single lamp in the halogen tungsten lamp array.

[0064] When the illumination intensity of the halogen tungsten lamp array reaches the required level, steps 1 to 6 are repeated until the requirements are met.

[0065] To achieve the second purpose of the present invention, the front battery cell of the solar panel is heated to above 135°C to meet the thermal vacuum temperature test of the conventional solar panel. The present invention adopts an infrared lamp array. During the thermal vacuum test, the heat flux radiated by the infrared lamp to the parabolic lampshade is reflected to the surface of the spacecraft in the form of parallel light.

[0066] The infrared light array controls the solar panel in sections, and a temperature-controlled thermocouple is arranged in each section to heat or cool the temperature-controlled thermocouple to the target temperature in stages.

[0067] The inner and outer surfaces of the parabolic lampshade are affixed with polyimide aluminum-plated secondary surface reflectors with a reflectivity greater than 0.9, which improves the reflection effect of the parabolic lampshade and reduces the radiation heat of the outer side of the parabolic lampshade to the space environment heat sink.

[0068] The 300mm×250mm (horizontal×vertical) infrared lamp array layout can heat the front of the solar panel to 135°C, meeting the high temperature requirements of existing conventional on-orbit solar panel thermal vacuum tests.

[0069] To achieve the second object of the present invention, the following manufacturing steps are included:

[0070] The first step: designing the parabolic lampshade and its appearance; pasting a polyimide aluminum-plated secondary surface reflector on the surface of the parabolic lampshade.

[0071] Step 2: Arrange the single infrared lamp assemblies at fixed intervals in the horizontal and vertical directions to form an orderly infrared lamp array, and the outer envelope of the infrared lamp array is larger than the size of the solar panel of the test object; specifically, arrange multiple infrared lamp assemblies in an array to form an infrared lamp array in the same horizontal and vertical arrangement as the halogen lamp; the outer envelope of the infrared lamp array is larger than the surface size of the solar panel of the test object, and the width direction is flush with the halogen tungsten lamp array;

[0072] Step 3: Use optical simulation software to simulate the illumination uniformity and confirm the illumination area of ​​the infrared lamp array after sorting, check the rationality of the horizontal and vertical spacing of the infrared lamp array, and determine the horizontal and vertical spacing of the infrared lamp array and the spacing to the front of the solar panel;

[0073] Step 4: Conduct thermal vacuum test or thermal simulation of solar panels according to the infrared lamp array layout to explore the heating capacity of the infrared lamp array and confirm that the maximum temperature value and temperature uniformity of the front of the solar panel are less than 0.5°C. Specifically, the infrared lamp array and the halogen lamp array are arranged on the front of the panel, with the infrared lamps arranged in odd rows and the halogen tungsten lamps arranged in even rows;

[0074] Step 5: Determine the highest temperature value obtained. If it is greater than 135°C or other set values ​​and the temperature uniformity is less than 0.5°C, it is determined that the infrared lamp array layout meets the design requirements.

[0075] If the heating capacity of the infrared lamp array does not meet the high temperature design requirements, repeat steps 1 to 5 until the requirements are met.

[0076] In order to achieve the third purpose of the present invention, the method of using the two sets of lamp arrays during the thermal vacuum test is determined. In the initial stage of heating up the thermal vacuum test of the solar panel, the halogen tungsten lamp array is turned on according to the calibrated power, and the infrared lamp array is heated in a set manner. The halogen tungsten lamp array is completely turned off after the high temperature is maintained, and the infrared lamp array is cooled in a set manner. In the heating stage of the thermal vacuum test, the halogen lamp array is turned on synchronously according to the power determined above, and continues until the high temperature is maintained. The infrared lamp array heats the front of the solar panel to the test temperature and maintains it in accordance with its own control method.

[0077] The present invention solves the problem of low power generation of solar panels during thermal vacuum tests. By adding a halogen tungsten lamp array, the light intensity during the test is improved. The infrared lamp array and the halogen tungsten lamp array are arranged in a 300mm×250mm (horizontal×vertical) layout, which not only meets the high temperature assessment requirements of existing conventional thermal vacuum tests for solar panels, but also enables the power generation of the solar panels to approach the designed amount.

[0078] The present invention will be described in more detail below in conjunction with more preferred examples.

[0079] See also Figure 1 , the infrared lamp array and the halogen tungsten lamp array are arranged on the front of the solar panel in a certain layout, and the same type of lamps are in the same row. The infrared lamp and the halogen tungsten lamp are of the same or similar size (the length difference is within 2cm), and are assembled with the same lampshade. The lamp array has the same width and the rows are flush. The light intensity of the halogen tungsten lamp array is calibrated by the standard solar cell, and the infrared lamp array controls the temperature on the front of the solar panel in different areas.

[0080] See also Figure 2 , the simulation result of the halogen lamp array radiation illumination on the front of the solar panel, the area in the square virtual frame is the area of ​​the corresponding solar panel. The radiation illumination of each point in the square virtual frame is relatively close, which means that the uniformity of the light radiation illumination on the front of the solar panel is good. The light radiation illumination is simulated by computer, and the variables are the horizontal and vertical spacing of the halogen lamp array. By changing the horizontal and vertical spacing of the halogen tungsten lamp array, the optimal light radiation illumination uniformity value is obtained, and the arrangement of the light radiation illumination is determined. The area outside the square virtual frame exceeds the space of the solar panel, and the radiation illumination is small, which ensures that the halogen tungsten lamp illumination design on the solar panel is reasonable.

[0081] See also Figure 3 , an idea for the manufacturing method of an external heat flow device for spacecraft thermal tests based on photothermal fusion.

[0082] The present invention also provides a method for using the photothermal fusion spacecraft thermal test external heat flow device, comprising the following steps:

[0083] The first step: the halogen tungsten lamp arrays are all turned on during the thermal vacuum heating stage, and the infrared lamp array heats the solar panel according to the set method.

[0084] Step 2: The halogen tungsten lamp array is completely turned off at the beginning of thermal vacuum cooling, and the infrared lamp array is used to cool the solar panel according to the set method.

[0085] In summary, the present invention relates to the technical field of spacecraft environment simulation, and discloses a photothermal fusion spacecraft thermal test external heat flow device, the external heat flow device comprising an infrared lamp heating system and a halogen lamp system. The infrared lamp heating system is used to heat the surface of the spacecraft to the test temperature, and the halogen lamp system is used for the light reaction of the spacecraft surface. The infrared lamp heating system and the halogen lamp system are arranged on the front of the solar panel. The two sets of lamp assemblies provided by the infrared lamp heating system and the halogen lamp system utilize a parabolic reflective surface structure to reduce the radiation of the heat source and light in the infrared lamp assembly to the heat sink of the space environment, thereby improving the heating efficiency of the heat source and the lighting efficiency of the light source; the overall envelope size of the two sets of lamp assemblies is larger than the surface size of the test object solar panel. The present invention solves the problem of low conversion of light energy into electrical energy during the thermal vacuum test of solar panels, improves the light intensity of the external heat flow device and the current output of the solar panel during the test, and strengthens the functional assessment of the solar panel.

[0086] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0087] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A spacecraft external heat flow simulation device based on photothermal fusion, characterized in that: include: Infrared lamp array, halogen tungsten lamp array; The infrared lamp array and the halogen tungsten lamp array are installed in parallel on the front of the solar panel to form an array arrangement; The infrared lamp array heats the surface of the solar panel to the test temperature; An array of tungsten halogen lamps is used to react to light on the surface of the solar panel.

2. The spacecraft external heat flow simulation device based on photothermal fusion according to claim 1 is characterized in that: The outer envelopes of the infrared lamp array and the halogen tungsten lamp array both exceed the boundaries of the surface size of the test object solar panel.

3. The spacecraft external heat flow simulation device based on photothermal fusion according to claim 1 is characterized in that: Single infrared lamps and single halogen tungsten lamps are arranged in equal rows and columns; The number of rows of light arrays is an odd number, and the infrared light arrays and halogen lamps are arranged alternately, equidistant up and down, with the infrared light array in the first row.

4. The spacecraft external heat flow simulation device based on photothermal fusion according to claim 3 is characterized in that: The shape and size of each infrared lamp and halogen tungsten lamp are the same or close, where close means the length difference is within 2cm; The infrared lamp and the halogen tungsten lamp are installed on a parabolic lampshade lamp assembly of the same size, with the back of the lamp tube facing the parabolic lampshade and the reflective surface of the parabolic lampshade facing the front of the solar panel; The axis of the lamp tube is located at the focus of the reflective surface of the parabolic lampshade. The parabolic lampshade is used to parallelly reflect the electromagnetic waves from the back of the infrared lamp and the halogen tungsten lamp to the solar panel. The inner and outer surfaces of the parabolic lampshade are affixed with polyimide aluminum-plated secondary surface reflectors, and the reflectivity of the parabolic lampshade is greater than 0.

9.

5. The spacecraft external heat flow simulation device based on photothermal fusion according to claim 4 is characterized in that: During the thermal vacuum test, the light radiated by the halogen lamp onto the parabolic lampshade is reflected to the surface of the spacecraft in the form of parallel light. The power of a single halogen lamp is determined before the test. According to the layout of the halogen lamp array, the standard cell is placed where the solar panel is located, the halogen lamp array is turned on, and the power of the halogen lamp is adjusted so that the current of the standard cell reaches the target value, which corresponds to a heat flux of 1410W / m 2 , obtain the power of a single halogen tungsten lamp.

6. The spacecraft external heat flow simulation device based on photothermal fusion according to claim 5 is characterized in that: During the thermal vacuum test, the heat flux radiated by the infrared lamp to the parabolic lampshade is reflected to the surface of the spacecraft in the form of parallel light; the infrared lamp array controls the solar panels in partitions, and a temperature-controlled thermocouple is arranged in each partition to heat or cool the temperature-controlled thermocouple to the target temperature in stages.

7. A method for manufacturing a spacecraft external heat flow simulation device based on photothermal fusion according to claim 1, characterized in that: include: The optical simulation software is used to simulate the illumination uniformity of the sorted halogen tungsten lamp array, determine the horizontal and vertical spacing of the halogen tungsten lamp array and the spacing to the front of the solar panel, and obtain the preliminary layout of the halogen lamp array; After the preliminary layout, the halogen tungsten lamp array uses a standard cell to measure the light intensity close to the front of the solar panel, confirming that the light intensity reaching the front of the solar panel is 1410W / m 2 Among them, a standard cell is placed at a certain distance from the halogen tungsten lamp array, that is, where the front of the solar panel is located during the thermal vacuum test. The standard cell has a calibrated light intensity of 1410W / m 2 Determine the wattage of the tungsten-halogen lamp. Determine the light intensity obtained. If it is 1410W / m 2 If the lamp is within the set range nearby, it is determined that the layout of the halogen tungsten lamp array meets the design requirements, and the power of a single lamp in the halogen tungsten lamp array is recorded.

8. The method for manufacturing a spacecraft external heat flow simulation device based on photothermal fusion according to claim 7, characterized in that: After the infrared light array is sorted, the optical simulation software is used to simulate the illumination uniformity and confirm the illumination area, check the rationality of the horizontal and vertical spacing of the infrared light array, and determine the horizontal and vertical spacing of the infrared light array and the spacing to the front of the solar panel; Thermal vacuum test or thermal simulation of solar panels is carried out according to the layout of infrared lamp array to explore the heating capacity of infrared lamp array and confirm that the maximum temperature value and temperature uniformity of the front of solar panels are less than 0.5℃; the infrared lamp array and halogen lamp array are arranged on the front of solar panels, the infrared lamps are arranged in odd rows, and the halogen tungsten lamps are arranged in even rows; The highest temperature value obtained is determined. If it is greater than 135°C or other set values ​​and the temperature uniformity is less than 0.5°C, it is determined that the infrared lamp array layout meets the design requirements.

9. A method for using the spacecraft external heat flow simulation device based on photothermal fusion according to any one of claims 1 to 6, characterized in that: include: Step 1: Turn on all the halogen tungsten lamp arrays during the thermal vacuum heating stage, and the infrared lamp array heats the solar panel according to the set method; Step 2: Turn off all halogen tungsten lamp arrays at the beginning of thermal vacuum cooling, and the infrared lamp array cools the solar panel according to the set method.

10. The method for using the spacecraft external heat flow simulation device based on photothermal fusion according to claim 9, characterized in that: Before the test, the halogen lamp array is calibrated with standard cells to determine the power applied to each halogen lamp during the test conditions.

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